Thor

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Thor

Thor IRBM
Credit: © Thomas Kladiva - Thomas Kladiva

American liquid propellant intermediate range ballistic missile, developed by Douglas in 1956-1958. 60 deployed to Britain in 1958-1962. The basis for a family of Thor and Delta space launch vehicles, remaining in production into the 2010's.

AKA: B-75;Mk. 2;PGM-17;PGM-17A;PTM-17A;SM-75;W49. Payload: 1,000 kg (2,200 lb). Thrust: 666.00 kN (149,722 lbf). Gross mass: 50,000 kg (110,000 lb). Height: 19.82 m (65.02 ft). Diameter: 2.44 m (8.00 ft). Span: 2.74 m (8.98 ft).

In 1954 the USAF realized that the Soviet Union – and perhaps more worryingly, the US Army – was developing intermediate range ballistic missiles which would be deployed several years before the Air Force's Atlas ICBM. The result was Thor, a crash December 1955 program to produce an Air Force intermediate range ballistic missile with the same range as the Army's Jupiter. USAF Missile Czar General Bernard Schriever dictated that the missile would be air-transportable in a C-124 Globemaster, use the inertial guidance, re-entry vehicle, and nuclear warhead being developed for Atlas. A single Rocketdyne 150,000 lb (68-metric-ton) thrust lox/kerosene engine would power the missile. This was to have been used as the sustainer engine for Atlas when the requirement was to launch a 2700 kg thermonuclear warhead over an intercontinental range. When it became apparent that the warhead could be reduced to less than half that weight, Atlas was downsized, and the large sustainer motor was no longer required. But the design was a perfect fit for Thor (related designs from Rocketdyne with the same thrust were under development for the Navaho cruise missile and the Jupiter).

Douglas was selected as prime contractor in December 1955 for one of the most accelerated crash programs in history. 'Chief Designer' of the Thor was Jack Bromberg, hired by Donald Douglas in the 1930's. Although not educated formally as an engineer, he was smart and dynamic, and a major influence in Douglas' winning bid to the USAF. Bromberg managed to fly a first prototype only thirteen months after go-ahead. In September 1958 the first of sixty Thors were deployed to missile sites in Great Britain under Project Emily. Deployment to four bases was completed in 1960, but at the end of 1962 the Thors were withdrawn from Britain as part of the secret codicil of Kennedy's deal to end the Cuban Missile Crisis. A few continued in an offensive military role as a nuclear-tipped anti-satellite system, based on Johnson Atoll in the Pacific, until the 1970's. Surplus Thors were used for a variety of suborbital re-entry vehicle tests. However Thor remained in production as a space launch vehicle, with a variety of upper stages. Dubbed the Delta by NASA, with solid rocket boosters, upgrades to the main engine, stretches to the first stage, and improvements to the upper stage, it became a workhorse of the American space program. Still in production in the 2010's, Jack Bromberg's stop-gap design became America's most reliable, most economical, and longest-lived launch vehicle.

Development Cost $: 500.000 million. Recurring Price $: 6.250 million in 1958 dollars. Flyaway Unit Cost$: 0.750 million in 1958 dollars. Maximum range: 2,400 km (1,400 mi). Number Standard Warheads: 1. Standard RV: Mk. 2. Standard warhead: W49. Warhead yield: 1,440 KT. CEP: 0.97 km (0.60 mi). Boost Propulsion: Liquid rocket, Lox/Kerosene. Maximum speed: 17,740 kph (11,020 mph). Initial Operational Capability: 1958. Total Number Built: 224. Total Development Built: 64. Total Production Built: 160.

More at: Thor.

Subtopics

Barbarian MDD American heavy-lift orbital launch vehicle. Proposed launch vehicle for large SDI 'Star Wars' payloads. Expected to cost $ 400-500 million, the Barbarian could place the Zenith-Star chemical laser into low earth orbit. It would consist of 3 Shuttle SRM's, attached around a ring of six Delta RS-27 first stage boosters, which in turn clustered around a single Delta first stage booster that was the last stage of the launch vehicle.

Delta American orbital launch vehicle. The Delta launch vehicle was America's longest-lived, most reliable, and lowest-cost space launch vehicle. Delta began as Thor, a crash December 1955 program to produce an intermediate range ballistic missile using existing components, which flew thirteen months after go-ahead. Fifteen months after that, a space launch version flew, using an existing upper stage. The addition of solid rocket boosters allowed the Thor core and Able/Delta upper stages to be stretched. Costs were kept down by using first and second-stage rocket engines surplus to the Apollo program in the 1970's. Continuous introduction of new 'existing' technology over the years resulted in an incredible evolution - the payload into a geosynchronous transfer orbit increasing from 68 kg in 1962 to 3810 kg by 2002. Delta survived innumerable attempts to kill the program and replace it with 'more rationale' alternatives. By 2008 nearly 1,000 boosters had flown over a fifty-year career, and cancellation was again announced.

Delta 0100 American orbital launch vehicle. The military Thor-Delta vehicles were developed into the first of a series of commercial satellite launch vehicles. The Delta 0100 series featured Castor 2 solid propellant strap-ons and a Long Tank Thor core with MB-3 engine.

Delta 0300 American orbital launch vehicle. Three stage vehicle consisting of 3 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x DSV-3N-4

Delta 0900 American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x DSV-3N-4

Delta 1000 American orbital launch vehicle. The Delta 1000 series used Castor 2 strap-ons and the Extended Long Tank core with MB-3 engine.

Delta 1410 American orbital launch vehicle. Three stage vehicle consisting of 4 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201

Delta 1604 American orbital launch vehicle. Four stage vehicle consisting of 6 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta F + 1 x Star 37C

Delta 1900 American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta F

Delta 1910 American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201

Delta 1913 American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201 + 1 x Star 37D

Delta 1914 American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201 + 1 x Star 37C

Delta 2 6000 American orbital launch vehicle. The Delta 6000 series used the Castor 4A strap-ons with the ultimate Extra Extended Long Tank core with RS-27 engine.

Delta 2 7000 American orbital launch vehicle. The Delta 7000 series used GEM-40 strap-ons with the Extra Extended Long Tank core, further upgraded with the RS-27A engine.

Delta 2000 American orbital launch vehicle. The Delta 2000 series used Castor 2 strap-ons together with an Extended Long Tank core equipped with the more powerful RS-27 engine. This engine was derived from surplus H-1 engines intended for the Saturn IB booster of the Apollo program. The Delta P upper stage was built by Douglas and used surplus Apollo lunar module engines from TRW.

Delta 2310 American orbital launch vehicle. Three stage vehicle consisting of 3 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201

Delta 2313 American orbital launch vehicle. Three stage vehicle consisting of 3 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37D

Delta 2910 American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201

Delta 2913 American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37D

Delta 2914 American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37E

Delta 3000 American orbital launch vehicle. The Delta 3000 series upgraded the boosters to Castor 4 solid propellant strap-ons, while retaining the Extended Long Tank core with RS-27 engine. The 3910 series used the TRW Lunar Module engine in the second stage, while the 3920 series reintroduced the Aerojet AJ110 Delta engine.

Delta 3910 American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201

Delta 3910/PAM American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4 + 1 x ELT Thor/RS-27 + 1 x Delta P + 1 x Star 48B

Delta 3913 American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37N

Delta 3914 American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37E

Delta 3920 American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K

Delta 3920/PAM American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K + 1 x Star 48B

Delta 3920-8 American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K

Delta 3924 American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K + 1 x Star 37E

Delta 3925 American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K + 1 x Star 48B

Delta 4000 American orbital launch vehicle. The Delta 4000 series used more powerful Castor 4A strap-ons, but the old Extended Long Tank core with MB-3 engine. Only two of these were launched.

Delta 4925-8 American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor /MB-3 + 1 x Delta K + 1 x Star 48B with 2.4 m (8 foot) diameter fairing)

Delta 5000 American orbital launch vehicle. The Delta 5000 series used the more powerful Castor 4A strap-ons but with the Extended Long Tank core with RS-27 engine. Only one was launched.

Delta 5920-8 American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K with 2.4 m (8 foot) diameter fairing)

Delta 6000 American orbital launch vehicle. The Delta 6000 series used the Castor 4A strap-ons with the ultimate Extra Extended Long Tank core with RS-27 engine.

Delta 6920-10 Three stage vehicle consisting of 9 x Castor 4A + 1 x EELT Thor/RS-27+ 1 x Delta K with 3.05 m (10 foot) diameter fairing

Delta 6920-8 American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4A + 1 x EELT Thor/RS-27+ 1 x Delta K with 2.4 m (8 foot) diameter fairing)

Delta 6925 American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x EELT Thor/RS-27+ 1 x Delta K + 1 x Star 48B

Delta 6925-8 American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x EELT Thor/RS-27+ 1 x Delta K + 1 x Star 48B with 2.4 m (8 foot) diameter fairing)

Delta 7000 American orbital launch vehicle. The Delta 7000 series used GEM-40 strap-ons with the Extra Extended Long Tank core, further upgraded with the RS-27A engine.

Delta 7000H American launch vehicle. Version of Delta 7000 using much larger GEM 46 solid rocket motors originally developed for the Delta 3.

Delta 7320-10 American orbital launch vehicle. Three stage vehicle consisting of 3 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K

Delta 7320-10C American orbital launch vehicle. 3 stage vehicle consisting of 3 x GEM-40 + 1 x EELT Thor + 1 x Delta/0020.

Delta 7326-9.5 American orbital launch vehicle. Four stage vehicle consisting of 3 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 37FM with 2.9 m (9.5 foot) diameter fairing)

Delta 7420-10 American orbital launch vehicle.

Delta 7420-10C Three stage vehicle consisting of 4 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 3.05 m (10 foot) diameter composite fairing

Delta 7425-10 American orbital launch vehicle. Four stage vehicle consisting of 4 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 3.05 m (10 foot) diameter fairing

Delta 7425-9.5 American orbital launch vehicle. Four stage vehicle consisting of 4 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 2.9 m (9.5 foot) diameter fairing)

Delta 7426-9.5 American orbital launch vehicle. Four stage vehicle consisting of 4 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 37FM with 2.9 m (9.5 foot) diameter fairing)

Delta 7920-10 Three stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 3.05 m (10 foot) diameter fairing

Delta 7920-10C Three stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 3.05 m (10 foot) diameter composite fairing

Delta 7920-10L American orbital launch vehicle. Three stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 3.05 m (10 foot) diameter long fairing

Delta 7920-8 American orbital launch vehicle. Three stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 2.4 m (8 foot) diameter fairing)

Delta 7920H American orbital launch vehicle. Version of Delta 7000 using much larger GEM 46 solid rocket motors originally developed for the Delta 3.

Delta 7925 American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B

Delta 7925-10 American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 3.05 m (10 foot) diameter fairing

Delta 7925-10C American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor + 1 x Delta/0020 + 1 x Star 48B.

Delta 7925-10L American orbital launch vehicle. Version of 7925-10C with long fairing.

Delta 7925-8 American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 2.4 m (8 foot) diameter fairing)

Delta 7925-9.5 American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 2.9 m (9.5 foot) diameter fairing)

Delta 7925H American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-46 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B

Delta 8930 American orbital launch vehicle. Delta 3 was an attempt by the manufacturer to provide the ultimate development of the original Delta booster. The core vehicle was beefed-up to accommodate much larger solid rocket boosters and a new cryogenic upper stage. However problems were incurred during development, resulting in the first two launches being failures. Meanwhile the satellite launch market crashed and the new vehicle was left without customers. The venerable Delta 7925 soldiered on for NASA, and the new Delta 4 series captured the USAF EELV requirement.

Delta C American orbital launch vehicle. Unaugmented Thor with Delta D and solid propellant upper stages.

H-1 Japanese license-built version of Delta launch vehicle, with Japanese-developed upper stages. Three stage vesion with nine solid propellant booster motors.

H-1 (2) Japanese license-built version of Delta launch vehicle, with Japanese-developed upper stages. Three stage version consisting of 9 x Castor 2 + 1 x ELT Thor N + 1 x LE-5

H-1 6-3 Japanese license-built version of Delta launch vehicle, with Japanese-developed upper stages. Three stage vesion with six solid propellant booster motors.

H-1 6R Japanese license-built version of Delta launch vehicle, with Japanese-developed upper stages. Four stage version consisting of 6 x Castor 2 + 1 x ELT Thor N + 1 x LE-5 + 1 x UM129A

H-1 9-2 Japanese license-built version of Delta launch vehicle, with Japanese-developed upper stages. Two stage vesion with nine solid propellant booster motors.

N-1 Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle.

N-2 Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle.

N-2 (2) American orbital launch vehicle. Three stage version consisting of 9 x Castor 2 + 1 x ELT Thor N + 1 x AJ10-118FJ

Thor Able American orbital launch vehicle. Thor with Able stage derived from Vanguard second stage.

Thor Able I American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x Able 1/AJ10-41 + 1 x Altair

Thor Able II American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x Able 2/AJ10-42

Thor Able II M1 American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x Able 2/AJ10-42 + 1 x Altair

Thor Able III American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x Able 3/AJ10 + 1 x Altair

Thor Able IV American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x AJ10 + 1 x Altair

Thor Ablestar American orbital launch vehicle. As Thor Able but with enlarged Ablestar second stage with 2 1/2 x greater burn time.

Thor Ablestar 2 American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DSV-2A + 1 x Able-Star/AJ10-104D

Thor Agena A American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x Agena A

Thor Agena B American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-21 + 1 x Agena B

Thor Agena D American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-21 + 1 x Agena D

Thor Burner American orbital launch vehicle. Thor DM-18A with 'Burner' upper stage solid rocket packages used for launch of classified payloads.

Thor Burner 1 American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x FW4S

Thor Burner 2 American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x Star 37B

Thor Burner 2A American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-18A + 1 x Star 37B + 1 x Star 26B

Thor Delta American orbital launch vehicle. Commercial name for the military's Thor-Delta. The name of the Delta second stage eventually was applied to subsequent commercial follow-ons.

Thor Delta A American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-21 + 1 x AJ10-118 + 1 x Altair

Thor Delta B American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-21 + 1 x AJ10-118A + 1 x Altair

Thor Delta C American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DSV-2A + 1 x Delta D + 1 x Altair 2

Thor Delta C1 American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DSV-2A + 1 x Delta D + 1 x FW4D

Thor Delta D American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta D + 1 x Altair 2

Thor Delta E American orbital launch vehicle. Thor augmented with 3 x Castor 2 motors with Delta E and Altair 2 upper stage.

Thor Delta E1 American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta E + 1 x FW4D

Thor Delta G American orbital launch vehicle. Three stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta E

Thor Delta J American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta E + 1 x Star 37D

Thor Delta L American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor 2 + 1 x LT Thor DSV-2L-1B + 1 x Delta E + 1 x FW4D

Thor Delta M American orbital launch vehicle. Long Tank Thor augmented with 3 Castor 2 boosters and Delta E / Burner 2 (Star 37D) upper stages.

Thor Delta M6 American orbital launch vehicle. Four stage vehicle consisting of 6 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x Delta E + 1 x Star 37D

Thor Delta N American orbital launch vehicle. Long Tank Thor augmented with 3 Castor 2 boosters and Delta E upper stage.

Thor Delta N6 American orbital launch vehicle. Three stage vehicle consisting of 6 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x Delta E

Thor DM-18 American orbital launch vehicle. Single stage vehicle adapted from Thor IRBM with no upper stage.

Thor DM-18A American orbital launch vehicle. Single stage vehicle

Thor DM-18C American orbital launch vehicle. Single stage vehicle

Thor DSV-2D American orbital launch vehicle. Single stage vehicle.

Thor DSV-2E American orbital launch vehicle. Single stage vehicle.

Thor DSV-2F American orbital launch vehicle. Single stage vehicle.

Thor DSV-2G American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x AJ10-118

Thor DSV-2J American anti-ballistic missile. Single stage vehicle.

Thor DSV-2U American orbital launch vehicle. Single stage vehicle.

Thor Hydra American orbital launch vehicle. Thor with Hydra liquid oxygen/hydrogen pressure-fed upper stage. Never went beyond initial hardware testing. However such a stage would have vastly increased Thor-Ablestar performance, from 150 kg to over 1000 kg in a medium polar orbit.

Thor MG-18 American orbital launch vehicle. Two stage vehicle consisting of 1 x Thor DM-18A + 1 x MG-18

Thor SLV-2 Agena B Two stage vehicle consisting of 1 x Thor DSV-2A + 1 x Agena B

Thor SLV-2 Agena D Two stage vehicle consisting of 1 x Thor DSV-2A + 1 x Agena D

Thor SLV-2A Agena B Thor Agena B upgraded with addition of three Castor 1 strap-on motors.

Thor SLV-2A Agena D Thor Agena upgraded with addition of three Castor 1 strap-on motors.

Thorad SLV-2G Agena D Thor Agena upgraded with Extended Length Tank Thor stage. 3 stage vehicle.

Thorad SLV-2H Agena D Thor Agena upgraded with Long Tank Thor stage. Variant with straight tank from Delta was Thorad (Long Tank Augmented Thrust Thor Delta)

Thor-DSV2A Able-Star American orbital launch vehicle variant.

Thor-LV2F Burner-2 Star-13A American orbital launch vehicle variant.

Family: IRBM, pad-launched. Country: USA. Engines: LR79-7. Spacecraft: BCP-2000, Kepler, LEOStar-2, LM-300, Proteus, SAC-D, SMAP, STSS, Pioneer 0-1-2, KH-1, S-2, Transit, Midas, Pioneer 5, TIROS, GRAB, Echo, Courier, KH-2, KH-5, Lofti, P-14, Injun, EPE, KH-3, TRAAC, Oscar, Lofti 2, SECOR, SURCAL, Ferret, KH-4, OSO, Ariel, Anna, Telstar, ERS, Alouette, TAVE, Starfish, NRL ELINT, Relay, Syncom, KH-6, P 11, SSF, AE, RADOSE, KH-4A, LAMPO, IMP, GGSE, AFP-43, Echo 2, BE, Program 437, Starflash, Nimbus, OGO, Calsphere, Quill, DMSP Block 4A, DODECAPOLE, Intelsat 1, Tempsat, GEOS, DME, Pioneer 6-7-8-9-E, Pageos, TOS, Intelsat 2, Biosatellite, Timation, Aurora, KH-4B, TTS, RAE, Intelsat 3, HEOS, Isis, PAC, TETR, SOICAL, NATO 1, ITOS, SERT, DMSP Block 5A, TOPO, CEPE, SESP, DMSP Block 5B, ASTEX, NOSS, TD-1A, Landsat 1-2-3, HS 333, Skynet, SMS, DMSP Block 5C, Intasat, Symphonie, COS, Spacebus 100, ETS, GOES, AS 1000, CTS, Marisat, JISS, NATO 3, LAGEOS, DMSP Block 5D, ESA-Geos, Sirio, ECS/OTS, ISEE, Meteosat, CS-1, IUE, PIX, Yuri, CAMEO, Anik satellite, SCATHA, Ayame, SMM, HS 376, Insat 1, Dynamics Explorer, SME, SSTL-70, AS 3000, Landsat 4-5, IRAS, CS-2, Advanced Tiros N, Exosat, AMPTE, ASC, EGS, MABES, SDI, Marine Observation Satellite, CS-3, GPS Block 2 and 2A, COBE, HS 601, Debut, LACE, RME, ROSAT, Eurostar 1000, Losat, JERS, EUVE, DUVE, Geotail, SEDS, PMG, Wind, Radarsat, SURFSAT-1, XTE, NEAR, Polar, MSX, Mars Global Surveyor, Mars Pathfinder, GPS Block 2R, LM 700, ACE, Globalstar, Deep Space 1, SEDSAT, MCO, DS2 Microprobe, Mars Polar Lander, Stardust, ARGOS, Orsted, Sunsat, Landsat 7, FUSE, IMAGE, SA-200, EO-1, Munin, SAC-C, Mars Odyssey, GeoLITE, MAP, Genesis, Jason, TIMED, Aqua, Contour, CHIPSat, XSS, MER, Cubesat, SIRTF, Gravity Probe-B, Aura, Messenger, Swift, Deep Impact, Calipso, Mitex, Stereo, USA 193, Themis, RS-300, Cosmo-SkyMed, Phoenix, WorldView, Dawn. Launch Sites: Vandenberg. Agency: Douglas.

Photo Gallery

RAF Training Launch
Successful training launch by the Royal Air Force with the USAF 392nd Squadron acting as instructors. This launch was from the launch complex that consisted of launch pads 6, 7 and 8. During this time we were using all three launch pads for RAF training. This was the fourth RAF Thor training launch. Launch date was August 3, 1959.
Credit: Larry Rhoads

392nd Thor Squadron
Vandenberg 392nd Squadron Thor launch personnel, Vandenberg, 1962 or 1963.
Credit: Larry Rhoads

Thor
Credit: via Andreas Parsch

Thor Burner 2A
Thor Burner 2A - COSPAR 1975-043

Thor Burner
Thor-Burner 2 - COSPAR 1967-065

4300SS Thor Squadron
The USAF 392nd squadron trained the Royal Air Force with live launches. When the Thor missile was phased out in England, the 392nd become the 4300SS squadron with several 'all blue uniform' programs. This is a picture of the 4300SS squadron personnel taken sometime early 1964 or late 1963
Credit: Larry Rhoads

1954 April 9 - . LV Family: Atlas, Thor.

Ballistic missiles to move forward with all practicable speed. - .
In a memorandum to Secretary of the Air Force Harold E. Talbott, Deputy Secretary of Defense Roger M. Keyes stressed that the plans for the ballistic missile program "be formulated with a thoroughly realistic appraisal of the capabilities of our contractors to meet their commitments." He then emphasized that the program was to move forward "with all practicable speed."

1955 November 8 - . LV Family: Thor, Jupiter, .

Both Jupiter and Thor to be developed - .
Secretary of Defense Charles E. Wilson approved a compromise memorandum of the Joint Chiefs of Staff (JCS) recommending the concurrent development of two intermediate range ballistic missiles (IRBMs). IRBM Number 1 by the Air Force and Number 2 as a joint Army-Navy effort. The former program later became the Thor (XSM-75) program, and the latter became the Jupiter (XSM-78) program.

1955 November 18 - . Launch Vehicle: Thor.

ARDC to develop and deploy Thor - . Hq USAF assigned Hq ARDC the mission of developing IRBM Number 1 and also that of achieving initial operational capability (IOC) with the new missile weapon systems..

1955 Dec - . LV Family: Thor, Jupiter, . Launch Vehicle: Thor.

Thor major subsystem contractors ordered to proceed. - .
The Western Development Division notified certain of its subsystem contractors to redirect part of their efforts to the recently authorized IRBM program. North American Aviation was to provide the propulsion system, AC Spark Plug was to work on an all-inertial guidance system, and Bell Telephone Laboratories on a radio guidance system and General Electric would handle the nose cone effort.

1955 December 1 - . LV Family: Titan, Atlas, Thor, Jupiter, . Launch Vehicle: Titan I.

Highest priority for both ICBMs and IRBMs. - . Related Persons: , Eisenhower. President Eisenhower officially assigned highest and equal priority to the development of the Atlas and Titan ICBMs and the Thor and Jupiter IRBMs. This decision led to the resignation of ICBM program advocate Gardner..

1955 December 14 - . LV Family: Atlas, Thor.

Thor given second priority after Atlas. - . Related Persons: Power.
On the basis of the Hq USAF directive of 18 November, General Thomas S. Power, ARDC Commander, amended the Western Development Division's mission to include responsibility for ICBM initial operation capability (IOC) and for the development of IRBM Number 1 on a priority second only to that of the ICBM program.

1955 December 23 - . LV Family: Thor.

Douglas selected to build Thor IRBM. - . The WDD-SAPO Source Selection Board chose the Douglas Aircraft Company as the airframe and assembly contractor for Weapon System 315A - the Thor (XSM-75) intermediate range ballistic missile..

1955 December 27 - . LV Family: Thor.

Douglas contracted for the Thor IRBM. - .
Douglas Aircraft Company awarded contract for the development and fabrication of the airframe for the Thor IRBM. Following Hq USAF approval of its 23 December selection, the Western Development Division and SAPO awarded a contract to the Douglas Aircraft Company, Incorporated, for the development and fabrication of the airframe for the Thor IRBM (XSM-75) and assembly of the missile.

1956 January 23 - . LV Family: Thor.

Thor IRBM development program was given equal priority with the ICBM program. - .

1956 January 30 - . LV Family: Titan, Atlas, Thor, Jupiter, .

ICBM and IRBM equal priority. - . Headquarters ARDC directed WDD to treat the ICBM and IRBM with equal priority..

1956 February 10 - . LV Family: Titan, Atlas, Thor, Jupiter, .

Trevor Gardner resigned as Assistant Secretary of the Air Force. - .
Trevor Gardner, who was instrumental in the actions leading to the acceleration of the Air Force ballistic missile program two years earlier, resigned as Assistant Secretary of the Air Force. He protested the Pentagon's policies concerning missiles and lack of stronger emphasis on the programs.

1956 April 13 - . LV Family: Titan, Atlas, Thor, Jupiter, .

Production funding for guided missiles increased. - . As per authority of the Air Force Ballistic Missile Committee (AF/BMC), Procurement Authorization 56-GM-20 increased the production funding for guided missiles to $279.05 million..

1956 Jun - . LV Family: Thor.

First Thor engine delivered. - . The Rocketdyne Division of North American Aviation delivered the first 135,000-pound thrust, MB-1 Thor research and development engine to the Douglas Aircraft Company..

1956 August 27 - . Launch Site: Edwards. LV Family: Thor.

First static test firing of Thor engine. - . The first static test firing of a Thor engine was conducted at the rocket engine test facilities at the Air Force Flight Test Center (AFFTC), at Edwards AFB, California..

1956 Sep - . LV Family: Thor.

First Thor IRBM flight test missile assembled. - . The first Thor IRBM flight test missile was assembled in the Douglas plant in Santa Monica, California..

1956 September 1 - . Launch Site: Vandenberg. LV Family: Thor, Atlas.

Vandenberg chosen as location for USAF ICBM and IRBM operations and training. - . Related Persons: , Quarles. Secretary of the Air Force Donald Quarles approved the location of ICBM and IRBM operational and training facilities at Camp Cooke, California, contingent upon approval by higher authorities..

1956 Oct - . LV Family: Titan, Thor. Launch Vehicle: Titan I, Thor.

Radio inertial guidance system for Titan and Thor. - . WDD decided to eliminate the inertial platform from the Bell Telephone Laboratories (BTL) radio inertial guidance system for Titan and Thor..

1956 October 18 - . Launch Vehicle: Thor.

First Thor IRBM flight test missile delivered to Cape Canaveral. - . A Tactical Air Command (TAC) C-124 "Cargomaster" delivered the first Thor IRBM flight test missile, Number 101, to the Air Force Missile Test Center (AFMTC) at Patrick AFB, Florida..

1956 November 26 - . LV Family: Atlas, Titan, Thor, Jupiter, Redstone, Pershing.

All missiles over 200 miles range assigned to USAF. - .
Secretary of Defense Charles E. Wilson issued a memo to the Armed Forces Policy Council to end the argument between the Air Force and Army on responsibility for missile programs. In an effort to settle the areas of jurisdiction for the services, Secretary Wilson ruled that all long-range missiles, ICBMs as well as IRBMs, with a range of more than 200 miles, would be given to the Air Force.

1957 January 10 - . LV Family: Atlas, Titan, Thor, Jupiter, .

Highest priority for ICBM/IRBM contracts - . The Defense Department assigned the highest priority to ICBM/IRBM contracts and purchase orders to expedite the programs..

1957 January 26 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18. FAILURE: Lox contamination, led to a valve failure. Thrust decayed, the booster settled back through the thrust ring, causing an oxygen fire, followed by booster explosion.. Failed Stage: 1.

Series I research and development launch - . Nation: USA. Agency: USAF. Apogee: 0 km (0 mi). First attempted test flight of USAF Thor IRBM, only 13 months after first production contracts were signed, failed to launch. The first attempt failed when the vehicle lost thrust immediately after liftoff..

1957 April 20 - . 04:33 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18. FAILURE: Console wiring error resulted in erroneous tracking indication; destroyed by range safety.. Failed Stage: G.

Series I research and development launch - . Nation: USA. Agency: USAF. Apogee: 0 km (0 mi).
The second Thor flight test missile launched on the Atlantic Missile Range (AMR) was successful until the Range Safety Officer (RSO) accidentally destroyed the missile. Douglas Thor IRBM (XSM-75) was launched at Cape Canaveral, Fla., destroyed by range safety officer. The missile was actually on course throughout its flight. The console wiring error led the range safety officer to believe it was headed inland rather than out to sea, so he hit the destruct button.

1957 May 22 - . 03:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18.

Research and development Series I (padex) test - . Nation: USA. Agency: USAF. Apogee: 0 km (0 mi).

1957 August 1 - . LV Family: Titan, Atlas, Thor, Jupiter. Launch Vehicle: Titan I.

Ballistic missile programs reoriented. - .
The National Security Council approved a Defense Department recommendation to reorient and cut back the ballistic missile programs. Atlas retained its priority, but the Titan program was reduced to second priority. The Thor and Jupiter IRBM programs were to be combined and evaluated by a joint Office of the Secretary of Defense-Air Force-Army Committee that would choose between them for future development.

1957 August 9 - . LV Family: Titan, Atlas, Thor.

Missile production rates curtailed. - .
In an attempt to reduce program costs, Defense Secretary Charles E. Wilson curtailed the planned production rates for Atlas, Titan, and Thor missiles to four missile each per month for the ICBMs. He also requested a study of the effects of a monthly production rate of 2-2-2 for the three programs.

1957 August 30 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor DM-18. FAILURE: Failure. Failed Stage: 1.

Series I research and development launch - . Nation: USA. Agency: USAF. Apogee: 0 km (0 mi). The fourth Thor (#104) missile broke up and exploded 96 seconds into its flight. .

1957 September 11 - . LV Family: Titan, Atlas, Thor. Launch Vehicle: Atlas E, Titan I, Thor.

Air Force Ballistic Missile program cuts - .
The Air Force Ballistic Missile Committee reviewed the revised AFBMD FY 1958 program that resulted from OSD decisions and directives of August that cut the program from $1,135 billion to $944 million. A 4-4-2 monthly production rate was approved for Atlas, Titan, and Thor missiles, and program slippages were accepted in response to Secretary Wilson's guidance of 9 August. The program was later submitted to OSD/BMC and approved on 5 October 1957.

1957 September 20 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18.

Series I research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).
First fully successful test flight of Thor intermediate range ballistic missile. (AF Ballistic Missiles Program Status Report.) After four failures, the fifth Thor flight test missile (#105) successfully demonstrated all on-board systems. The engine operated 137 seconds to automatic shutdown, and missile impacted 1,300 nautical miles down range from Cape Canaveral. Complete USAF Thor IRBM first successfully launched from Cape Canaveral. Dummy Warhead sent to 1800 km range.

1957 October 3 - . 17:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor DM-18. FAILURE: Failure. Failed Stage: 1.

Series I research and development launch - . Nation: USA. Agency: USAF. Apogee: 0 km (0 mi).

1957 October 5 - . LV Family: Titan, Atlas, Thor, Jupiter.

Studies to accelerate missile programs. - . In anticipation of directives to revise the objectives of the United States missile programs in light of the Russian success with Sputnik, AFBMD began studies for accelerating its programs..

1957 October 5 - . LV Family: Titan, Atlas, Thor. Launch Vehicle: Atlas, Thor, Titan.

Approval of the revised AFBMD ballistic missile program. - .
Secretary of Defense Charles E. Wilson approved the revised AFBMD ballistic missile program submitted to the Air Force Ballistic Missile Committee on 12 September. A total of $991 million was approved; $437 million for Atlas, $335 million for Titan, and $148 million for Thor. AFBMD's original FY58 budget submission of October 1956 had requested $1,672 billion for the ballistic missile programs.

1957 October 11 - . 16:33 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18. FAILURE: Turbopump gearbox failure..

Series I research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi). The second successful Thor flight test missile was launched from Cape Canaveral, Florida, and attained its design range of 1,500 miles. Thor missile launched at Cape Canaveral, the second tested, achieved its designed 1,500-mile range..

1957 October 24 - . 16:32 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor DM-18.

Series I research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi). In its first long-range flight, a Thor missile launched from Cape Canaveral completed a 2,645-mile flight down the Atlantic Missile Range. Stripped down Thor long-range flight test successful from AMR, impacting 4400 km downrange..

1957 November 5 - . LV Family: Thor.

Thor to be used for early reconnaisance satellite tests. - . Spacecraft: WS-117.
The Air Force briefed the Armed Forces Policy Council on a reconnaissance satellite program and possible combinations of vehicles that could be used for "cold war and scientific programs. The Air Force recommended using the available intermediate range ballistic missile as a booster to hasten launching an orbital system as early as March 1958. If approved this program would require an additional six Thors and $12 million to cover additional costs. (Ltr, Co0 R. J. Nunzia.o, Asst for Spec Prog, DCS/Dev, Hq USAF, to SAFRD, 12 Nov 57, subj: Outer Space Vehicle.)

1957 November 5 - . LV Family: Thor, Minuteman.

Solid Ballistic Weapon System development begins. - . Colonel Edward N. Hall was relieved of his primary duty as Director, WS 315A (Thor), and assigned primary duty as Director for the Solid Ballistic Weapon System at Air Force Ballistic Missile Division.

1957 November 5 - . Launch Vehicle: Thor.

USAF briefed the Armed Forces Policy Council on a reconnaissance satellite program. - . Spacecraft: Man-In-Space-Soonest.
The Air Force briefed the Armed Forces Policy Council on a reconnaissance satellite program and possible combinations of vehicles that could be used for "cold war and scientific programs." The Air Force recommended using the available intermediate range ballistic missile as a booster to hasten launching an orbital system as early as March 1958. If approved this program would require an additional six Thors and $12 million to cover additional costs. (Ltr, Co0 R. J. Nunzia.o, Asst for Spec Prog, DCS/Dev, Hq USAF, to SAFRD, 12 Nov 57, subj: Outer Space Vehicle.)

1957 November 7 - . Launch Vehicle: Thor.

Three Thor IRBM's to be diverted for an early satellite capability. - . Spacecraft: Man-In-Space-Soonest.
Three Thor IRBM's to be diverted from the missile test program and used for an early satellite capability. In response to the nation's urgent need to demonstrate at least an early space vehicle capability it was suggested that three Thor boosters be made available from the missile test program and from these an early satellite or space capability could be obtained. Accordingly, Air Force headquarters requested Air Research and Development Command to conduct an engineering study which would " . . . provide sufficient information to this headquarters within the next 30 45 days on which a decision can be based as to the feasibility, capability and cost of such a program. " An immediate release of $100,000 enabled the command to fund preliminary design studies. (Msg, 11-033, ARDC to AFBMD, 13 Nov 57.)

1957 November 12 - . LV Family: Thor.

Thor to be used for early space launches. - .
Headquarters USAF asked the Defense Department to approve a space program that would provide an early demonstration of space capability and a developmental test vehicle for larger satellite systems. Three Thor IRBMs could be made available for use in such development programs provided they did not interfere with the IRBM program.

1957 November 12 - . Launch Vehicle: Thor.

Crash space program using the Thor IRBM as the booster. - . Spacecraft: Man-In-Space-Soonest.
USAF requested the Department of Defense approve a crash space program using the Thor IRBM as the booster. Assistant Secretary of the Air Force for Research and Development, R. E. Horner, requested the Department of Defense approve a space program that would furnish an early demonstration of space capability and "provide important development test vehicles leading to larger reconnaissance and scientific satellites." To hasten action three Thor missiles, 114,116 and 118 ". . could be made available in a relatively short period of time with minimum interference to the IRBM program. " These boosters could be used to orbit a recoverable animal satellite prior to 1 July 1958. Thor, it was also suggested, would be a practical vehicle to furnish the Air Force satellites with specific military capabilities. (Memo, Asst SAF (R&D), R. E. Homer, to SOD, 1Z Nov 57, subj: Outer Space Vehicle.)

1957 November 27 - . Launch Vehicle: Thor.

Thor and Jupiter IRBM's ordered into production. - . Nation: USA. Thor and Jupiter IRBM's ordered into production for ultimate deployment by the USAF..

1957 December 7 - . LV Family: Thor.

Both Jupiter and Thor to be deployed - . Mr. William M. Holaday, DoD Director of Guided Missiles, directed the Air Force to proceed with the operational deployment of four squadrons each of Thor and Jupiter IRBMs beginning in December 1958..

1957 December 7 - . 22:11 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18.

Research and development Series II test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1957 December 18 - . Launch Vehicle: Thor.

USAF proposes accelerated astronautics program for 1958-1959. - . Related Persons: Schriever. Spacecraft: Man-In-Space-Soonest.
Major General B. A. Schriever again offered a well defined astronautics program at an estimated cost of $16 million in fiscal 1958 and $112 million in 1959. In addition, $10 million in 1958 and $2O million in 1959 would be needed to procure Thor hardware and acquire a Thor space launch complex. Furthermore, said Schriever, although use of all resources qualified to participate in the program was endorsed it was ". . . imperative that the total Air Force effort in the ballistic missile and space field must be managed by one agency and that agency must be the Air Force Ballistic Missile Division. " Schriever also proposed creation of a research and development command committee, chaired by the missile division, to formulate and recommend technical development in space technology. "The committee would meet periodically and make recommendations to the commander, AFBMD, for formulation of the Air Force program." "(Ltr, Maj Gen B. A. Schriever, Qmdr AFBMD, to Lt Gen S. E. Anderson, Cmdr ARDC, 18 Dec 57, subj: Proposal for Future Air Force Ballistic Missile and Space Technology Development.)

1957 December 19 - . 20:12 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor DM-18.

Research and development Series II test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).
The eighth Thor flight test missile, the fourth success, completed the first fully-guided flight using an all-inertial guidance and control system. A Thor missile, the eighth tested and the fourth successfully, completed the first fully-guided Thor IRBM flight using an all-inertial guidance system.

1958 January 1 - . Launch Vehicle: Thor.

Thor put into operational service. - . Nation: USA. Strategic Air Command assigned responsibility for U.S. operational ICBM capability; while the 672nd Strategic Missile Squadron, first to be equipped with USAF Douglas Thor IRBM, was activated..

1958 January 3 - . Launch Vehicle: Thor.

USAF recommendation for a strong astronautics program, including animal and lunar flights. - . Spacecraft: Man-In-Space-Soonest.
Air Force Ballistic Missile Division's recommendation for a strong astronautics program, forwarded to Lt General D. L. Putt, Deputy Chief of Staff, Development, at Air Force headquarters, included the following specific proposals: (1) Thor plus a Vanguard second stage would be used as the basic booster to provide a vehicle with a recoverable data capsule: first orbital flight with telemetry only by September 1958, followed by four additional flights during the remainder of fiscal 1959. (2) Develop a recoverable animal carrying satellite using rhesus monkeys; four flights during fiscal 1959. (3) Lunar impact missions could be attempted with a high probability of success by adding a Vanguard third stage to the Thor and Vanguard second stage vehicle; four vehicles should be planned for this mission beginning during the last quarter of 1958, (4) Four vehicles should be assigned the mission of circumlunar flight. Total cost of these programs was estimated at $26.8 million during fiscal 1958, and $30.4 million in fiscal 1959 including ground equipment and Thor production would have to be increased by two units per, month if the entire astronautics program were adopted as proposed. (Msg, WDG-I -Z, Cmdr AFBMD, to Cmdr AIDC, 3 Jan 58.)

1958 January 3 - . LV Family: Thor, .

Thor-Able development recommended - . AFBMD recommended to Hq USAF that an early space capability be developed through use of a Thor booster and a modified Vanguard second stage. This combination was to become the Thor/Able booster..

1958 January 6 - . LV Family: Thor.

Tho-Agena use proposed to accelerate WS-117L spysat program. - . Spacecraft: WS-117. Lockheed proposed the acceleration of WS 117L by using Thor boosters and Agena upper stages..

1958 January 16 - . Launch Vehicle: Thor.

First draft plan for USAF space weapons. - . Spacecraft: Man-In-Space-Soonest.
The first rough draft of a development plan for the Air Force space weapons development and technology program was completed by the ballistic missile division. This was oriented to meet five basic requirements: reconnaissance, communications, manned space flight, technical development and experimental support. To accomplish these objectives it was necessary to make maximum use of Air Force missile hardware and pursue a "daring and bold merger of the aeronautics and manned aircraft experience of the last decade with the rocket and ballistic missile experience in recent years." The program' s fiscal 1958 funding needs were estimated to be as follows: astronautics, $16 million; additional Thor hardware and launch complex for the advanced astronautics program, $10 million. (Memo,. Col C. H. Terhune, Dep Cmdr, Weapon Sys, AFBMD, to Cmdr ARDC, 16 Jan 58, subj: AF Astronautics Development Program.)

1958 January 28 - . 20:16 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor DM-18. FAILURE: Failure. Failed Stage: 1.

Research and development Series II test - . Nation: USA. Agency: USAF. Apogee: 0 km (0 mi). Thor IRBM successfully fired from Cape Canaveral, flew prescribed course, and impacted in preselected area..

1958 February 1 - . LV Family: Thor.

Thor missiles to boost test satellites into orbit before the end of the year. - . Related Persons: , McElroy. Secretary of the Air Force James H. Douglas urged Secretary of Defense Neil H. McElroy to approve Air Force use of Thor missiles to boost test satellites into orbit before the end of the year..

1958 February 1 - . Launch Vehicle: Thor.

USAF to use Thor to boost spysats and moon missions by the end of the year. - . Spacecraft: Man-In-Space-Soonest.
Secretary of the Air Force James H. Douglas urged the Secretary of Defense to approve Air Force use of Thor missiles to boost test satellites into orbit before the close of the calendar year. The Secretary of Defense was also advised that in the face of the impending establishment of the Advanced Research Projects Agency (ARPA), the Air Force continue managing development of military space reconnaissance projects, first under the general direction of the Director of Guided Missiles and then under the general direction of ARPA. (Memo, SAF J. H. Douglas, to SOD, 1 Feb 58, subj: Reconnaissance Satellite.) Experimental preliminary steps to a manned space program were directed by Air Force headquarters. development command was assigned authority to develop a recoverable satellite and the first launch date was set for October 1958. The command was also instructed to conduct a moon impact program although the authority to conduct such a program had not yet been granted. Necessary planning action would be taken in order to expedite the program immediately upon approval from the Department of Defense. " (Ltr, Brig Gen H. A. Boushey, DCS/D, Hq USAF, to Cmdr ARDC, 3 Feb 58, subj: Astronautics Program.)

1958 February 3 - . LV Family: Titan, Atlas, Thor, Jupiter. Launch Vehicle: Titan I, Thor, Atlas E, Jupiter.

Highest priority to ballistic missiles, spy satellites, and ballistic missile early detection. - . Related Persons: , Eisenhower. Spacecraft: WS-117.
President Eisenhower directed the highest and equal national priority for Atlas, Titan, Thor, Jupiter, the WS 117L advanced military satellite system, and WS 224A BMEWS. This action returned the Titan program to its previous highest national priority status.

1958 February 7 - . Launch Vehicle: Thor.

Advanced Research Projects Agency established. - . Spacecraft: Man-In-Space-Soonest.
The Department of Defense established the Advanced Research Projects Agency. ARPA was to direct and conduct space research leading toward operational systems. In pursuit of these objectives the agency was authorized management of projects which would be conducted by military departments and it was also empowered to contract directly with individuals, private business organizations, scientific institutions and public agencies. (DOD Dir 5105.15, 7 Feb 58, subj: Department of Defense Advanced Research Projects Agency.)

1958 February 10 - . Launch Vehicle: Thor.

Blue Scout, Thor to be used for re-entry tests, recoverable satellites, and moon impact probes. - . Spacecraft: Man-In-Space-Soonest.
Air Research and Development Command headquarters forwarded further instructions to the missile division as a guide to planning for a space program. The research command was to proceed, when Department of Defense approval was obtained, with development of a ballistic research and test system (WS 609A, later called Blue Scout), specifically designed to satisfy most research flight test requirements. In addition, the Thor missile was to be used as a booster for (1) "Able" re-entry tests; (2) recoverable satellites; (3) and moon impact. The latter program was not yet finally approved but planning actions were authorized to "expedite this project immediately upon receipt of DOD approval" and $1 million had been set aside to cover initial project costs. (Msg, RDX-2-I-E, Hq ARDC to AFBMD, 10 Feb 58.)

1958 February 11 - . LV Family: Thor, Atlas, Titan, Navaho. Launch Vehicle: Thor Able, Thor Agena A.

14 Thor boosters to be used during year for space and ICBM missions. - . Spacecraft: Man-In-Space-Soonest.
The ballistic missile division informed command headquarters that as many as 14 Thor boosters would be available during the calendar year for special purpose flights. These were tentatively allocated as follows: three were assigned to Phase I "Able" series flights, six were assigned to the program for recoverable satellites, and five were assigned to Phase II "Able" for continued development leading to a Thor ICBM capability. (For a time Thor plus a second stage and warhead was considered as a means of acquiring an early emergency ICBM inventory well ahead of Atlas and Titan.) However, only eight additional launchings could be scheduled through 1958--three for Phase I "Able", three for recoverable satellites to be launched one a month beginning in October, and two in support of Phase II "Able" precisely guided reentry vehicles. Thus this appeared to be the maximum effort possible in the category of space related experimental flights essential to a more advance program. If a greater effort was desirable it would be necessary to obtain additional launching facilities, a problem that might be quickly and easily solved by modifying Navaho launch stands to accept Thor vehicles. (Msg, WDT 2-7E, AFBMD to ARDC, 11 Feb 58.)

1958 February 14 - . Launch Vehicle: Thor.

USAF to use Thor for variety of space missions. - . Spacecraft: Man-In-Space-Soonest, KH-1.
The Secretary of the Air Force forwarded to the Secretary of Defense, recommendations on space priorities. These recommendations "should be undertaken promptly by the Air Force. " Other than the first project, converting Thor into an intercontinental range weapon by adding a second stage, the recommendations concerned the following space proposals: (1) develop and orbit a satellite equipped with a small television transmitter to furnish weather information. A Thor plus a second stage could accomplish the first orbital launch by September 1958.: (2) Develop a recoverable satellite equipped to carry a variety of payloads which might be ejected from orbit by decelerating devices. This project would also use a Thor booster with an added Vanguard second stage which could be launched by July 1958. (3) A Thor-Hustler (later called Agena) second stage to launch a 300 pound scientific satellite by October 1958., (4) As previously recommended, the Air Force was prepared to launch a moon rocket by using a Thor plus two Vanguard upper stages. Said the secretary: "In addition to the scientific data that can be obtained from such a flight, the United States could make a major international psychological gain by beating the Russians to the moon. I urge that this Air Force approach be used. " (Memo, SAF J. H. Douglas to the SOD, 14 Feb 58, subj: Thor and WS 117L Program.)

1958 February 28 - . Launch Vehicle: Thor.

USAF to be responsible for manned space flight. - . Spacecraft: Man-In-Space-Soonest.
Advanced Research Projects Director, Mr. R. W. Johnson declared the Air Force had a ". . . long term development responsibility for manned space flight capability". In pursuit of this objective the Air For ce was told to develop a Thor booster with a suitable second stage vehicle "as an available device for experimental flights with laboratory animals." Provision for the recovery of the orbiting animals in "furtherance of the objective of manned flight" was also authorized. (Memo, R. W. Johnson, Dir, ARPA, to SAF, 28 Feb 58, subj: Reconnaissance Satellites and Manned Space Exploration.)

1958 February 28 - . 13:08 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18. FAILURE: Failure. Failed Stage: 1.

Research and development Series II test - . Nation: USA. Agency: USAF. Apogee: 0 km (0 mi). Copper heatsink nose cone.

1958 March 3 - . Launch Vehicle: Thor.

WS 117L acceleration approved using Thor boosters. - . Spacecraft: Man-In-Space-Soonest, KH-1.
The Secretary of Defense approved acceleration of the 117L military satellite system, including test vehicles launched with the Thor booster--a series of orbital experiments that were also considered. The ballistic missile division was instructed to submit a complete development plan and fiscal estimate by 15 March 1958 for "review and approval."

1958 March 5 - . LV Family: Thor, Atlas. Launch Vehicle: Thor Agena A, Atlas Agena A.

USAF lead role in space reaffirmed. WS 117L to be prioritized. - . Spacecraft: Man-In-Space-Soonest, KH-1, WS-117.
The Office of the Secretary of Defense, in the first significant forward step to accelerate development of a space capability, reiterated the space role of the Air Force. In addition to its missile programs the Air Force was responsible for the 117L system and "... has a recognized long term development responsibility for manned space flight capability with the primary objective of accomplishing satellite flight as soon as technology permits." Furthermore, the Air Force was told it was to carry forward and accelerate the Atlas 117L project "under the highest national priority in order to attain an initial operational capability in the earliest possible date," But the proposed interim system using a Thor booster combined with a second stage and recoverable capsule "should not be pursued. " The Department of Defense did agree that a Thor booster with a suitable second stage "may be the most promptly and readily available device for experimental flights with laboratory animals" and development of such hardware including a system for recovery of animals was authorized. (Msg 03-014, Cmdr ARDC, to Cmdr AFBMD, 5 Mar 58.)

1958 March 12 - . Launch Vehicle: Thor.

USAF accelerated development plan for the man in space program. - . Related Persons: Schriever. Spacecraft: Man-In-Space-Soonest.
An Air Research and Development Command meeting held at the ballistic missile division to prepare an abbreviated development plan for the man in space program. The general Air Research and Development Command headquarters outline of the immediate planning task centered about designing a manned vehicle within a weight limitation of 2, 700-3,000 pounds which would have to contain a man, a life support system with a capacity to remain aloft for 48 hours, telemetry-communications, and a recovery system. The Air Force Ballistic Missile Division approach was directed to a more distant goal, "Man on the Moon and Return. " By the second day of the conference general agreement on program objectives had been reached. Technical recommendations included selection of an improved thrust Thor with a fluorine-hydrazine second stage, 2, 700-3, 000 pound spacecraft and a General Electric guidance system. As then planned the complete experimental and test program would require approximately 30 Thor boosters, 8 to 12 Vanguard second stages and about 20 fluorine-hydrazine second stages for testing and advanced phases of the program. By the third day an abbreviated dra.ft development plan had been completed. The conference was pervaded by a strong sense of urgency, motivated by the dramatic Air Force mission to get a man in space at the earliest possible time. Those attending the conference anticipated accelerated program approval and scheduled contractor selection to begin on or about 10 April 1958., (Memo, Col C. H. Terhune, Dep Cmdr, Tech Operations, to Maj Gen B. A. Schriever, Cmdr, AFBMD, 25 Mar 58, subj: Man in Space Meeting at AFBMD, lu-12 March 58.)

1958 April 10 - . LV Family: Titan, Atlas, Thor, Jupiter.

Equal priority for all ICBM and IRBM programs - . Related Persons: , Eisenhower. President Dwight D. Eisenhower reaffirmed the highest and equal national priority for Atlas, Titan, Thor, and Jupiter..

1958 April 19 - . 13:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18. FAILURE: Failure. Failed Stage: 1.

Research and development Series II test - . Nation: USA. Agency: USAF. Apogee: 0 km (0 mi).

1958 April 21 - . Launch Vehicle: Thor.

Pentagon managers briefed on USAF manned Military Space System Development Plan - . Spacecraft: Man-In-Space-Soonest.
Air Force Ballistic Missile Division presented briefings on the manned Military Space System Development Plan to higher Air Force and Department of Defense authorities in Washington. Also briefed were Air Research and Development Command headquarters, the Vice Chief of Staff, and R. W, Johnson, Director of the Advanced Research Projects Agency. (Chronological Space Hist, 58.)

1958 April 24 - . 00:10 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able. FAILURE: Thor turbopump gearbox failed T+146 sec.. Failed Stage: 1.

Able RTV re-entry vehicle test flight - . Nation: USA. Agency: USAF. Spacecraft: Man-In-Space-Soonest. Apogee: 80 km (49 mi).
The first Thor/Able missile, a special test vehicle designed to examine an improved General Electric lightweight, ablative nose cone at full ICBM ranges failed. Mouse 'Mia' not recovered. This was the first small beginning of a research program to determine the requirements of a space life support system. (Msg SAFIS-3C 47151, SAF to AFBMD, 29 Apr 58.)

1958 April 25 - . LV Family: Thor, Titan. Launch Vehicle: Thor Able, Titan C.

USAF goal to to "...land a man on the moon and return him safely to earth". - . Spacecraft: Man-In-Space-Soonest, Lunex.
The Air Force Ballistic Missile Division published the development plan for an Air Force Manned Military Space Systems Program. The objective was to ". achieve an early capability to land a man on the moon and return him safely to earth. The program represented a reasonable level of accomplishment with a minimum of time and money and called for start of a high priority program (similar to that enjoyed by ballistic missiles) characterized by "concurrency" and single Air Force agency management. The complete program would be carried out in four phases: first, "Man-In-Space-Soonest," was to determine functional capabilities and limitations of man in space by means of earth orbital flights--beginning with an instrumented 2,900 pound re-entry body, then a primate passenger and, finally, a manned capsule. The second, designated "Man-In-Space-Sophisticated," would use a drag type 3, 200 pound re-entry vehicle, capable of a 14 day manned space flight. This device would be used for earth orbital flight only but it would perform experiments essential to the final phase of the lunar program. The third phase, "Lunar Reconnaissance," would explore the moon by television camera and by means of a soft landing of an instrumented package on the moonIs surface. The final phase of the projected program was "Manned Lunar Landing and Return, " which would first test equipment by circumlunar flights returning to earth with instrumented capsules containing animals. At this stage of project development payload capacity would be increased to 9,000 pounds. The spacecraft would then undertake a full scale flight to the moon and safe return to earth with an animal passenger. The climax of the entire project would then be a manned lunar landing, brief surface exploration, and return to earth. This would be followed by other circumlunar flights to fully explore the moon's surface and gather additional physical data. The program was scheduled for completion in December of 1965 at a total estimated cost of $1.5 billion. Program cost estimates were based on use of Air Force rocket hardware and available ground facilities thus eliminating much new development and construction funding. However, new launch vehicle combinations would have to be developed progressing in performance as follows: a Thor-Vanguard second stage, a Thor-fluorine second stage, a "super" Titan with a fluorine-hydrazine second and third stages. Methods of landing involved use of retrorockets to insure a soft landing on the moon and return to earth through re-entry to a predetermined landing area. (USAF Manned Military Space Syst.em Development Plan, 25 Apr 58, prep by AFBMD.)

1958 April 30 - . Launch Vehicle: Thor, Atlas.

AVCO-Convair proposal for a manned satellite at the earliest possible date. - . Spacecraft: Man-In-Space-Soonest.
An AVCO-Convair contractor team submitted to the Air Force an unsolicited proposal for development of a manned satellite at the earliest possible date. The proposed system was built around an Atlas booster, no second stage, mounting a light double walled capsule which would rely on a steel mesh drag chute for deceleration and recovery. The proposal was analyzed by Air Force space specialists who concluded that the plan was feasible but offered little margin for error. Furthermore, weight estimates were optimistic, its orbital endurance and altitude were low and it possessed no growth potential although use of Atlas as a booster appeared to have merit. Air Force Ballistic Missile Division felt adoption of the proposal would only gain three or four months over the much more versatile Thor-fluorine combination vehicle which would also be free from the major limitations inherent in the AVCO-Convair proposal. (Memo, Col J. D. Lowe, AFBMD. to Col H. Evans, AFBMD, 16 May 1958, no subject.)

1958 May - . LV Family: Thor.

First operational Thor IRBM. - . The Air Force accepted the first operational Thor IRBM (SM-75)..

1958 May 2 - . Launch Vehicle: Thor.

Man-In-Space-Soonest plan to put American in orbit by October 1960. - . Spacecraft: Man-In-Space-Soonest.
The missile division published its second Man-In-Space Development Plan. This plan concentrated on the first phase of the over-all manned lunar program, designated "Man-In-Space-Soonest". During this phase of project development the launch vehicles would be a Thor-Vanguard combination for instrumented tests, and a Thor fluorine second stage combination for the manned flights. This plan, if approved, would place a man in a 150 nautical mile orbit by October 1960 at an approximate cost of $120 million. (USAF Manned Military Space System Development Plan, 2 May 1958, prep by AFBMD)

1958 May 15 - . Launch Vehicle: Thor.

USAF provides manned space funding alternatives. - . Related Persons: Schriever. Spacecraft: Man-In-Space-Soonest.
On instructions from command headquarters, the ballistic missile division prepared several funding alternatives to meet the amount of money that might be realistically budgeted for manned space. These were sorted out at four levels: (a) $100 million fiscal 1959 appropriation which reduced the test program for Thor-Vanguard vehicles but maintained the October 1960 date for the first manned space flight; (b) a $90 million program for the same number of vehicles but postponing the first manned flight from October 1960 to April 1961; (c) a $90 million high risk effort incurred by deleting four more vehicles from the program and retaining the October 1960 launch date; (d) a $75 million program with the same number of vehicles as (c) but delaying the first manned flight date to October 1961. (Memo, Col C. H. Terhune, Dep Cmdr, Tech Operations, AFBMD, to Maj Gen B. A. Schriever, Cmdr AFBMD, 15 May 58, subj: Revisions to the Man-In-Space Development Plan.)

1958 May 15 - . Launch Vehicle: Thor.

USAF establishes a fluorine propulsion program. - . Related Persons: Schriever. Spacecraft: Man-In-Space-Soonest.
Acting on directions from General Schriever, the missile division staff prepared to establish a fluorine propulsion program. This development was to support the manned military space system, particularly the Man-In-SpaceSoonest effort which was to use a Thor-fluorine second stage. The first action was to arrange a meeting of Air Force, North American Aviation and Bell Aircraft propulsion specialists to determine the status of their fluorine propulsion programs, funds available and overall development expectations for fluorine propulsion systems. (Chronological Space Hist, 1958.)

1958 May 20 - . Launch Vehicle: Thor, Atlas.

Man-In-Space Soonest plan presented to LeMay. - . Spacecraft: Man-In-Space-Soonest.
The ballistic missile division briefing on Man-In-SpaceSoonest was presented at Air Research and Development Command headquarters. Present were General C. E. LeMay and "members of the Air Staff, and to Air Force Undersecretary M. A. Maclntyre and Assistant Secretary R. E. Horner. Favorable reception was accorded the briefings and the command was assured that adequate funding, "somewhere between seventy-five and one hundred million dollars" would be allocated the program for fiscal year 1959. The briefing to Maclntyre and Horner evoked a specific suggestion that an ICBM be used as a booster in lieu of developing a second stage for the Thor. The division was allowed two weeks to prepare a plan using an Atlas booster and bring it to Washington for secretarial review. (Memo, Col H. L. Evans, Asst Dep Cmdr, Space Sys, to Col C. H. Terhune, 23 May 58, subj: Trip Report.)

1958 June 4 - . 21:17 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18.

Research and development Series III test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).
The first Air Force Thor IRBM flight test missile (Number 115) to be fired from a tactical-type launcher was launched at Cape Canaveral. The missile completed a successful flight, impacting 1,170 nautical miles downrange. This was also the first Thor to be launched without a flight readiness firing of its propulsion system. USAF Thor flight tested for the first time from a tactical-type launcher at Cape Canaveral.

1958 June 6 - . Launch Vehicle: Thor.

Special Assistant for BioAstronautics established at USAF. - . Spacecraft: Man-In-Space-Soonest.
Air Research and Development Command headquarters established a post of Special Assistant for BioAstronautics to the Deputy Commander for Ballistic Missiles. Life sciences personnel were to be placed on temporary duty with, or assigned to the ballistic missile division and authorized to make appropriate decisions. Command headquarters was to be informed of all decisions and through monthly reports maintain cognizance of development, fabrication, testing and scheduling of the life sciences portion of the over-all program. The Aeromedical Laboratory at Wright Air Development Center; USAF School of Aviation Medicine; and Aeromedical Field Laboratory of Air Force Missile Development Center were designated points of contact for weapon systems management organizations and contractors concerned with the life sciences experiments and hardware development. (Chronological Space Hist, 1958.)

1958 June 13 - . 15:06 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18.

Research and development Series III test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1958 June 19 - . Launch Vehicle: Thor, Atlas.

No "go ahead" for the man in space program. - . Spacecraft: Man-In-Space-Soonest, Mercury, Project 7969.
The Advanced Research Projects Agency had not yet directed a "go ahead" for the man in space program. However, Air Force headquarters considered it a certainty that direction of an Atlas boosted manned space flight would be given to the Air Force at an early date, that funds for the project would probably total $66 million and that a series of Thor boosted, instrument and animal capsule flights would precede the Atlas full sized instrumented capsule, chimpanzee, and manned shots. The Air Force would probably re-program to obtain whatever additional funds were required to support the program. The ballistic missile division was advised that while waiting for an authoritative "go ahead" it should continue preparation of work statements for industry competition and contractor selection so they might be coordinated with the Advanced Research iProjects Agency and the National Advisory Committee for Aeronautics. (Ltr, Maj Gen J. E. Smart, Asst V/CS, to Lt Gen S. E. Anderson, Cmdr ARDC, 19 Jun 58, no subject given, quoted in TWX, RDZGW6-33-K, Hq ARDC, to Hq AFBMD, 27 Jun 58.)

1958 June 24 - . Launch Vehicle: Thor, Atlas.

Secretary of the Air Force authorized an increase in missile production. - . Spacecraft: Man-In-Space-Soonest, , KH-1.
Inasmuch as availability of basic booster units threatened to limit selection of the most desirable space programs, the Secretary of the Air Force authorized an increase in missile production as follows: four more Thor boosters, delivery to begin in December 1958 at a rate of one a month; four more Atlas boosters, delivery to begin in May 1959 at a rate of one a month; and $8 million budgeted to the Advanced Research Projects Agency for procurement of four additional Lockheed 117L vehicles, delivery to begin January 1959 at a rate of one a month. (Memo, SAF to C/S USAF, 24 Jun 58, no subject.)

1958 June 30 - . Launch Vehicle: Thor.

Space Technology Laboratories to suport Air Force man in space program. - . Spacecraft: Man-In-Space-Soonest.
Space Technology Laboratories was requested to submit a proposal to perform system engineering and technical direction of the Air Force man in space program based on the Air Force Ballistic Missile Division's work statement. In event program authorization was received prior to completion of the proposal, work would begin under a letter contract. Pending receipt of such approval, the contractor's work on Man-In-SpaceSoonest program would be confined to technical staff assistance, a function it was performing as a technical requirement of the existing contract. (Chronological Space Hist, 1958.)

1958 July 10 - . 02:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able.

Able RTV re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 1,600 km (900 mi).
Mouse 'Mia II' reached 1600 km altitude, flew 9600 km range, but re-entry vehicle not recovered. The second Air Force Thor/Able reentry (nose cone) test vehicle, testing a GE ablation-type nose cone, was launched from Cape Canaveral on a 6,000-mile flight down the Atlantic Missile Range. This was the first U.S. reentry vehicle to make a full-range ICBM flight and reentry.

1958 July 13 - . 06:36 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18.

Research and development Series III test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1958 July 23 - . 22:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able.

Able RTV re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 1,600 km (900 mi).
In its second successful flight test, the Thor/Able (Number 1.19) advanced reentry test vehicle demonstrated proper reentry of the advanced General Electric ablative nose cone during a 5,300-mile test flight. Two successful tests established the two-stage Thor/Able as a reliable vehicle for further special test programs. This allowed the Air Force and other government agencies to complete plans for more advanced space programs. Mouse 'Wickie' not recovered; nose cone lost.

1958 July 25 - . Launch Vehicle: Thor.

Pentagon briefings on USAF manned space program. - . Spacecraft: Mercury, Project 7969, Man-In-Space-Soonest.
Air Force Ballistic Missile Division representatives again presented a series of Washington briefings. These were to Lt General S. E. Anderson, Commander, Air Research and Development Command; the Air Staff; Secretary of the Air Force and Staff; and Director Roy Johnson, of the Advanced Research Projects Agency. The latter presentation, in addition to reporting detailed man in space planning, requested prompt program approval and emphasized the urgency of firm funds commitment if further delay was to be avoided. Johnson's response to the briefing may be summarized as follows: (a) the man in space program would not be approved at this time; (b) it appeared that $50 million would be an optimistic estimate of man in space funding until the Space Council, authorized by recent legislation, was organized and working, an event that was not probable before Thanksgiving; (c) planning anything over a $50 million program, the maximum likely to be approved under any circumstances, was wasted effort; (d) statements of prominent scientists had convinced the White House there was no currently valid reason for Man-InSpace: (e) when the Space Council became a viable organization, man in space would probably become a joint effort of the Advanced Research Projects Agency and the National Advisory Committee for Aeronautics; (f) The National Advisory Committee for Aeronautics (the National Aeronautics and Space Act creating the National Aeronautics and Space Administration was to become law on 29 July 1958) was already thinking of an independent but very similar space program that would cost about $40 million in fiscal 1959. After these two days of briefings it was clear that quick approval of a military man in space program was not forthcoming. (MFR, Col J. D. Lowe, Ch, Space Sys Div, AFBMD, 30 Jul 58, subj: MISS Briefing to Hq ARDC, Hq USAF, the Secretary of the Air Force and ARPA on 24-25 July 1958.)

1958 July 26 - . 06:40 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18. FAILURE: Failure. Failed Stage: 1.

Research and development Series III test - . Nation: USA. Agency: USAF. Apogee: 0 km (0 mi).

1958 August 6 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18.

Research and development Series III test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi). The last of 18 Thor research and development flight test missiles was launched from Cape Canaveral. Only seven of the 18 launches were categorized as successes while 11 were failures. .

1958 August 17 - . 12:18 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able I. FAILURE: Thor exploded after 77 sec.. Failed Stage: 1.

Pioneer (1) - . Payload: Pioneer / Able 1. Mass: 38 kg (83 lb). Nation: USA. Agency: USAF. Program: Pioneer. Class: Moon. Type: Lunar probe. Spacecraft: Pioneer 0-1-2. Decay Date: 1958-08-17 . Apogee: 16 km (9 mi).
An Air Force Thor/Able It launch vehicle, carrying the first U.S. International Geophysical Year (IGY) lunar payload, exploded 77 seconds after liftoff from Cape Canaveral because of a first-stage engine failure. First US lunar attempt. The first US Air Force lunar probe, using a Thor-Able booster. An explosion ripped it apart 77 seconds after launch.

1958 August 22 - . LV Family: Atlas, Thor, Minuteman, .

Largely as a result of the successful Thor/Able reentry tests, Brigadier General Osmond J. - .
Ritland, AFBMD Vice Commander, reoriented the Division's reentry vehicle research and development program. Avco was directed to cancel its work on a y copper "heat sink" reentry vehicle. General Electric's Mark II copper "heat sink" nose con^ would be used on Thor IRBMs and early model Atlas ICBMs. Moreover, GE was assigned to start work on lightweight, second generation nose cones for heavier warheads.

1958 September 1 - . Launch Vehicle: Thor.

USAF space program uncertain due to the creation of NASA. - . Spacecraft: Mercury, Project 7969, Man-In-Space-Soonest, Lunex, KH-1.
The future of the proposed Air Force space program was uncertain due to the creation of the Advanced Research Projects Agency and the National Aeronautics and Space Administration. It appeared probable that final over-all space program would be adopted until the large area of overlapping jurisdiction between the two agencies was sorted out. In addition, the Department of Defense was required to transfer some $117 million in fiscal 1959 funds to the National Aeronautics and Space Administration of which $58.8 million was Air Force money. Thus it appeared that of the various proposed programs already within National Aeronautics and Space Administration's legitimate area of interest it might well take over the man in space program primarily because it had the money to undertake its development. In respect to the lunar probe program, the Air Force had to wait for further direction before proceeding further. The large booster (one million pound thrust) authorized for Air Force development was transferred to the civilian. space agency. The Air Force would continue development of the 117L system under the over-all direction of the Advanced Research Projects Agency. (Memo, Col C. R. Roderick, Committee Liaison Div, Ofc of Legislative Liaison, to Asst Dir, Legislative Liaison, Sep 58, no subj.)

1958 October 11 - . 08:42 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able I. FAILURE: Third stage produced insufficient thrust. Partial Failure.. Failed Stage: 3.

Pioneer 1 - . Payload: Pioneer 1 / Able 2. Mass: 38 kg (83 lb). Nation: USA. Agency: NASA. Program: Pioneer. Class: Moon. Type: Lunar probe. Spacecraft: Pioneer 0-1-2. Decay Date: 1958-10-12 . USAF Sat Cat: 110 . COSPAR: 1958-Eta-1. A Thor/Able launched the NASA Pioneer I, the first successful space probe, to a new altitude record of over 70,000 miles. AFBMD provided the vehicle and launched it under NASA direction. Set distance record; failed to reach moon..

1958 November 5 - . 08:53 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi). The initial launch of an operationally configured Thor IRBM (SM-75) was conducted at Cape Canaveral, but the missile had to be destroyed at T+35 seconds after the pitch attitude gyro malfunctioned. .

1958 November 8 - . 07:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able I. FAILURE: Third stage ignition unsuccessful.. Failed Stage: 3.

Pioneer 2 - . Payload: Pioneer 2 / Able 3. Mass: 39 kg (85 lb). Nation: USA. Agency: NASA. Program: Pioneer. Class: Moon. Type: Lunar probe. Spacecraft: Pioneer 0-1-2. Decay Date: 1958-11-08 . Apogee: 1,550 km (960 mi). Pioneer 2 was launched from the Atlantic Missile Range, using a Thor-Able booster, the Air Force acting as executive agent to NASA. The 86.3-pound instrumented payload, intended as a lunar probe, failed to reach escape velocity..

1958 November 25 - . Launch Vehicle: Thor, Atlas.

USAF receives request for booster support of NASA manned space program. - . Spacecraft: Man-In-Space-Soonest, Mercury.
Air Force Ballistic Missile Division received its first specific request from the civilian space agency to support a "preliminary research program leading to manned space flight." The division was requested to procure one Atlas C ballistic missile booster with its associated control and guidance equipment." '... This request was a forerunner of a support effort for a program "requiring approximately thirteen (13) ballistic missile boosters of the Thor and Atlas class."' The space agency would procure the payload, scheduled for May 1959 delivery. The missile division was to furnish detailed plans, subject to the approval of the National Aeronautics and Space Administration, for the design, construction and launching of this vehicle. One million dollars was immediately transferred to the Air Force with more money to be supplied as it was requested. (Msg, no cite number, Hq NASA, to Cmds. AFBMD, 25 Nov 58.)

1958 November 26 - . 09:09 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi). First operational launch.

1958 December 6 - . 00:41 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1958 December 16 - . 23:44 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Operational missile test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi). Two Thor shots, one from Cape Canaveral and one from Vandenberg AFB, were successful. Intermediate range ballistic missile portion of PMR was inaugurated with successful firing of USAF Thor from Vandenberg AFB..

1958 December 17 - . 04:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1958 December 31 - . 02:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18A. FAILURE: Failure. Failed Stage: 1.

Series IV research and development launch - . Nation: USA. Agency: USAF.

1959 January 21 - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena A. FAILURE: Launch vehicle failure.. Failed Stage: U.

Thor Agena test - . Mass: 779 kg (1,717 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-1. COSPAR: F590121A. First flight test of Thor-Agena for KH program..

1959 January 23 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able II.

RVX-1 - . Nation: USA. Agency: USAF. Apogee: 100 km (60 mi).

1959 January 23 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able II. FAILURE: Failure.

RVX-1 Re-entry Vehicle test - . Nation: USA. Agency: USAF. Apogee: 0 km (0 mi).

1959 January 30 - . 23:53 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 February 28 - . 07:58 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able II.

RVX-1 Re-entry Vehicle test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).
In the first use of a Thor as a space booster, the world's first polar orbiting satellite, Discoverer I, was launched by a Thor/Agena (Thor 163) booster combination from Vandenberg AFB. The mission was also the first successful flight test of Lockheed's Agena A upper stage vehicle designed for orbiting U.S. satellite systems.

1959 February 28 - . 21:49 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena A.

Discoverer 1 - . Payload: KH-1 prototype / Agena A 1022. Mass: 618 kg (1,362 lb). Nation: USA. Agency: DARPA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1959-03-03 . USAF Sat Cat: 13 . COSPAR: 1959-Beta-1. Apogee: 968 km (601 mi). Perigee: 163 km (101 mi). Inclination: 89.70 deg. Period: 96.00 min.
In the first use of a Thor as a space booster, the world's first polar orbiting satellite, Discoverer I, was launched by a Thor/Agena (Thor 163) booster combination from Vandenberg AFB. The mission was also the first successful flight test of Lockheed's Agena A upper stage vehicle designed for orbiting U.S. satellite systems. First polar orbiting satellite; KH-1 prototype; did not carry camera or film capsule.

1959 March 21 - . 06:19 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able II.

RVX-1 Re-entry Vehicle test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 March 22 - . 00:58 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 March 27 - . 04:02 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 April 8 - . 06:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able II.

RVX-1 Reentry test / particles mission - . Nation: USA. Agency: USAF. Apogee: 1,230 km (760 mi).
A Thor/Able reentry test vehicle launched from Cape Canaveral, Florida, completed a successful flight down the Atlantic Missile Range. The reentry body of the Thor/Able was recovered at the far end of the range in the South Atlantic. This was the first recovery of an ablative nose cone following an ICBM-range flight.

1959 April 13 - . 21:18 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena A.

Discoverer 2 - . Payload: KH-1 prototype / Agena A 1022. Mass: 743 kg (1,638 lb). Nation: USA. Agency: DARPA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1959-04-26 . USAF Sat Cat: 14 . COSPAR: 1959-Gamma-1. Apogee: 346 km (214 mi). Perigee: 239 km (148 mi). Inclination: 89.90 deg. Period: 90.40 min.
An Air Force Thor/Agena A booster vehicle lifted Discoverer II into orbit from Vandenberg AFB. Discoverer II became the world's first satellite to be stabilized in orbit in all three axes, to be maneuvered on command from earth, to separate a reentry vehicle on command, and to send its reentry vehicle back to earth. The capsule ejector system malfunctioned, causing the capsule to impact near Spitsbergen on 14 April rather than near Hawaii as planned. KH-1 prototype; tested capsule recovery techniques; did not carry camera; capsule recovery failed. Because of a timing error, the US believed that the capsule landed somewhere on the island of Spitsbergen, north of Norway, instead of landing in the recovery zone near Hawaii. The capsule was never found; and CIA officials suspect it may have been snatched by the Soviets. The search for this capsule formed the basis of the book and film 'Ice Station Zebra'.
In the winter of 1960/1961, a US Discovery spy satellite capsule was found by loggers near Kalinin, 200 km north of Moscow. The loggers cracked it open with an axe. Sergei Khrushchev believed this to be the Discoverer 2 capsule. What was left was examined by Soviet engineers but didn't reveal much information - it was a polished aluminium sphere, 30 cm in diameter, gilded on the exterior. Some said it was found as early as the winter of 1959.

1959 April 16 - . 20:46 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LE-8. LV Family: Thor. Launch Vehicle: Thor DM-18A.

IWST test flight - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi). The first Thor IRBM to be fired by a Royal Air Force (RAF) crew was launched from Vandenberg AFB. Integrated Weapon System Training 1. First Thor IRBM launched by British crew at Vandenberg AFB..

1959 April 23 - . 05:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi). Fourth recovery of a data capsule at AMR, USAF Thor 1,500-mile accuracy test flight..

1959 April 25 - . 05:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 April 28 - . LV Family: Thor. Launch Vehicle: Thor Delta A.

Delta launch vehicle contract. - . Nation: USA. NASA announced the signing of a $24 million contract with Douglas Aircraft Co., Inc., for a three-stage Thor-Vanguard launching rocket called Delta..

1959 May 12 - . 17:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 May 21 - . 06:40 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able II.

RVX-1 Re-entry Vehicle test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 May 23 - . 02:42 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 June 3 - . 20:09 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena A. FAILURE: No telemetry after Agena ignition.. Failed Stage: U.

Discoverer 3 - . Payload: KH-1 prototype / Agena A 1018. Mass: 753 kg (1,660 lb). Nation: USA. Agency: DARPA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1959-06-03 . KH-1 prototype; did not carry camera; film capsule recovery failed..

SRV - . Mass: 779 kg (1,717 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-1.

1959 June 11 - . 06:44 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able II.

RVX-1 Re-entry Vehicle test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 June 16 - . 21:45 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10E. LV Family: Thor. Launch Vehicle: Thor DM-18A. FAILURE: Autopilot error.. Failed Stage: G.

IWST test flight - . Nation: USA. Agency: RAF. Apogee: 0 km (0 mi). Integrated Weapon System Training Launch 2.

1959 June 22 - . LV Family: Thor.

First Thor squadron in the UK operational. - . The 77th Strategic Missile Squadron, with fifteen Thor missiles, was transferred to the Royal Air Force at Feltwell, England. This was the first Thor squadron to achieve operational status in the UK..

1959 June 25 - . 22:47 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena A. FAILURE: Insufficient stage 2 velocity.. Failed Stage: U.

Discoverer 4 - . Payload: KH-1 9001. Mass: 743 kg (1,638 lb). Nation: USA. Agency: DARPA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1959-06-25 . COSPAR: F590625A. KH-1; 1st generation low resolution photo surveillance. Failed to achieve orbit..

SRV 102 - . Mass: 779 kg (1,717 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-1. COSPAR: F590625B.

1959 June 26 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 June 30 - . 02:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV Lofted Trajectory research and development mission - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

1959 July 21 - . 07:33 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A. FAILURE: Failure. Failed Stage: 1.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 1.00 km (0.60 mi).

1959 July 24 - . 12:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi). USAF Thor data capsule recovered near Antigua which contained movie film showing nose cone separation..

1959 August 3 - . 21:41 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor DM-18A.

IWST - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1959 August 6 - . 02:48 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 August 7 - . 14:24 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able III.

Explorer 6 - . Payload: S-2. Mass: 64 kg (141 lb). Nation: USA. Agency: NASA. Program: Explorer. Class: Earth. Type: Magnetosphere satellite. Spacecraft: S-2. Decay Date: 1961-06-30 . USAF Sat Cat: 15 . COSPAR: 1959-Delta-1. Apogee: 42,400 km (26,300 mi). Perigee: 245 km (152 mi). Inclination: 47.00 deg. Period: 765.00 min. First Earth photo; radiation data..

1959 August 13 - . 19:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena A.

Discoverer 5 - . Payload: KH-1 9002 / Agena A 1029. Mass: 781 kg (1,721 lb). Nation: USA. Agency: DARPA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1959-09-28 . USAF Sat Cat: 18 . COSPAR: 1959-Epsilon-1. Apogee: 731 km (454 mi). Perigee: 214 km (132 mi). Inclination: 79.90 deg. Period: 94.10 min. KH-1; 1st generation low resolution photo surveillance; film capsule boosted into higher orbit, decayed 2/11/61. Mission failed. Power supply failure. No recovery..

Discoverer 5 Capsule - . Payload: KH-1 9002 Capsule. Mass: 779 kg (1,717 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1961-02-11 . USAF Sat Cat: 26 . COSPAR: 1959-Epsilon-2. Apogee: 1,700 km (1,000 mi). Perigee: 218 km (135 mi). Inclination: 78.90 deg. Period: 104.30 min. KH-1; 1st generation low resolution photo surveillance; film capsule boosted into higher orbit, decayed 2/11/61. Mission failed. Power supply failure. No recovery..

1959 August 14 - . 09:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 August 14 - . 19:36 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor DM-18A. FAILURE: Failure. Failed Stage: 1.

IWST - . Nation: USA. Agency: RAF. Apogee: 0 km (0 mi).

1959 August 19 - . 19:24 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena A.

Discoverer 6 - . Payload: KH-1 9003 / Agena A 1028. Mass: 783 kg (1,726 lb). Nation: USA. Agency: DARPA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1959-10-20 . USAF Sat Cat: 19 . COSPAR: 1959-Zeta-1. Apogee: 846 km (525 mi). Perigee: 207 km (128 mi). Inclination: 83.90 deg. Period: 95.10 min. KH-1; 1st generation low resolution photo surveillance; film capsule recovery failed. Mission failed. Retro rockets malfunctioned negating recovery..

1959 August 27 - . 12:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 September 12 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 September 17 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able II. FAILURE: Third stage failed.. Failed Stage: 3.

Transit 1A - . Payload: Transit 1A. Mass: 119 kg (262 lb). Nation: USA. Agency: DARPA. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. Decay Date: 1959-09-17 . A Thor/Able II booster carrying the Navy's Transit IA navigation satellite was launched from Cape Canaveral. A third stage malfunction prevented the satellite from achieving orbit. First Transit test satellite; failed to reach orbit..

1959 September 17 - . 21:09 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor DM-18A.

IWST - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi). A Thor/Able II booster carrying the Navy's Transit IA navigation satellite was launched from Cape Canaveral. A third stage malfunction prevented the satellite from achieving orbit. .

1959 September 21 - . LV Family: Titan, Atlas, Thor.

USAF responsible for all military spacecraft. - . Related Persons: , LeMay.
General Curtis E. LeMay, Vice Chief of Staff, USAF, informed Headquarters ARDC that the Secretary of Defense had assigned responsibility to the Air Force for developing and launching all military spacecraft. The Air Force was also to perform all required systems integration for military space systems. The decision was made for reasons of efficiency and economy.

1959 September 22 - . 18:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch/Ionosphere/Meteorites mission - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 September 23 - . LV Family: Polaris, Titan, Atlas, Thor, Jupiter, .

Responsibility for military space programs assigned to USAF - . Spacecraft: WS-117, Transit, Midas, Samos.
Once again, the Defense Department reorganized its space program. Primary responsibility for military space programs was assigned to the Air Force. ARPA retained responsibility for advanced research on missile defense, solid propellants, and several other projects. Existing projects were reassigned to the military services from ARPA - MIDAS and SAMOS to the Air Force,the Transit navigation satellite to the Navy, and NOTUS to the Army. These reassignments were not immediately effective, but the move toward Air Force development, production, and launching of military space vehicles was quite clear.

1959 October 6 - . 16:41 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch/Meteorites mission - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 October 6 - . 18:26 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LE-8. LV Family: Thor. Launch Vehicle: Thor DM-18A.

IWST - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1959 October 14 - . 04:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 October 21 - . 22:57 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor DM-18A.

IWST - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1959 October 29 - . 02:12 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch/Meteorites mission - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 November 3 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch/Meteorites mission - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 November 7 - . 20:28 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena A.

Discoverer 7 - . Payload: KH-1 9004 / Agena A 1051. Mass: 794 kg (1,750 lb). Nation: USA. Agency: DARPA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1959-11-26 . USAF Sat Cat: 24 . COSPAR: 1959-Kappa-1. Apogee: 820 km (500 mi). Perigee: 158 km (98 mi). Inclination: 81.60 deg. Period: 94.40 min. KH-1; 1st generation low resolution photo surveillance; satellite tumbled; film capsule not recovered. Mission failed. Failed to achieve orbit..

1959 November 12 - . 19:24 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor DM-18A.

IWST - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1959 November 19 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 November 20 - . 19:25 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena A.

Discoverer 8 - . Payload: KH-1 9005 / Agena A 1050. Mass: 795 kg (1,752 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1960-03-08 . USAF Sat Cat: 25 . COSPAR: 1959-Lambda-1. Apogee: 1,661 km (1,032 mi). Perigee: 186 km (115 mi). Inclination: 80.50 deg. Period: 103.50 min. KH-1; 1st generation low resolution photo surveillance; film capsule recovery failed. Mission failed. Eccentric orbit negating recovery..

1959 December 1 - . 17:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1959 December 2 - . 05:29 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor DM-18A. FAILURE: Failure. Failed Stage: 1.

Combat training launch - . Nation: USA. Agency: RAF. Apogee: 0 km (0 mi).

1959 December 9 - . LV Family: Thor.

RAF fully operational with the Thor missile. - . The British Air Ministry announced that the Royal Air Force had attained operational status with the Thor missile..

1959 December 15 - . 02:14 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor DM-18A. FAILURE: Failure. Failed Stage: 1.

IWST - . Nation: USA. Agency: RAF. Apogee: 0 km (0 mi).

1959 December 17 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Series IV research and development launch/Meteorites mission - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi). Flight testing of the Thor IRBM was completed with the launch of Thor 217 from Pad 18B at Cape Canaveral, Florida. .

1960 Jan - . LV Family: Thor.

Thor R&D program completed. - .
Executive management responsibility for the Thor IRBM (redesignated from WS 315A to WS 115A) was transferred from AFBMD to Air Materiel Command's San Bernardino Air Materiel Area (SBAMA). This marked the successful conclusion of the Thor research and development program after only four years.

1960 Jan - . LV Family: Titan, Atlas, Thor. Launch Vehicle: Thor Ablestar.

Ablestar second stage completed - .
Aerojet-General Corporation completed development of the Ablestar second stage for use with Atlas, Titan, or Thor boosters. Primary improvements over the previous Able vehicles were increased propellant capacity, multiple restart capability, and full-time attitude control.

1960 January 14 - . 16:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18C.

Special test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1960 January 21 - . 20:10 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor DM-18A.

IWST - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1960 February 4 - . 18:51 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena A. FAILURE: Failure. Failed Stage: U.

Discoverer 9 - . Payload: KH-1 9006. Mass: 765 kg (1,686 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1960-02-04 . KH-1; 1st generation low resolution photo surveillance. Mission failed..

SRV 113 - . Mass: 779 kg (1,717 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-1.

1960 February 9 - . 17:11 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18C.

Special test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1960 February 19 - . 20:15 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena A. FAILURE: Failure. Failed Stage: U.

Discoverer 10 - . Payload: KH-1 9007. Mass: 765 kg (1,686 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1960-02-19 . KH-1; Mission failed..

SRV 110 - . Mass: 779 kg (1,717 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-1.

1960 February 29 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18B. Launch Pad: LC18B. LV Family: Thor. Launch Vehicle: Thor DM-18C.

Special test - . Nation: USA. Agency: USAF. Apogee: 520 km (320 mi).

1960 March 2 - . 20:06 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LE-8. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Combat training launch - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1960 March 11 - . 13:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able IV.

Pioneer 5 - . Payload: Pioneer P 2 / Able 6. Mass: 43 kg (94 lb). Nation: USA. Agency: NASA. Program: Pioneer. Class: Astronomy. Type: Solar satellite. Spacecraft: Pioneer 5. USAF Sat Cat: 27 . COSPAR: 1960-Alpha-1.
An Air Force Thor/Able IV booster launched the NASA Pioneer V spacecraft on its journey to Venus. The satellite measured radiation and magnetic fields between Earth and Venus. The last scientific measurements were transmitted back to Earth on 26 June, three and one-half months after launch, from almost 22.5 million miles in space. Pioneer V was by far the most successful space probe yet launched. AFBMD and Space Technology Laboratories managed the Pioneer V satellite, payload, and booster for NASA and provided launch services at Cape Canaveral. Solar research. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1960 April 1 - . 11:40 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able II.

Tiros 1 - . Payload: Tiros A (A-1). Mass: 120 kg (260 lb). Nation: USA. Agency: NASA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Tiros. USAF Sat Cat: 29 . COSPAR: 1960-Beta-2. Apogee: 696 km (432 mi). Perigee: 656 km (407 mi). Inclination: 48.40 deg. Period: 98.30 min.
A Thor/Able II booster placed NASA's Television and Infrared Observation Satellite (TIROS) weather satellite into the most accurate orbit yet achieved by any U.S. satellite. TIROS I opened a new era in meteorology by transmitting nearly 23,000 pictures of global cloud cover from 450 miles in space and providing the first glimpse of global cloud structure data. TIROS I completed 1,302 orbits before its operational life ceased on 29 June 1960. TV and Infrared Observation Satellite; returned 22952 cloud cover photos. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1960 April 13 - . 12:02 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Transit 1B - . Mass: 121 kg (266 lb). Nation: USA. Agency: DARPA. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. Duration: 89.00 days. Decay Date: 1967-10-05 . USAF Sat Cat: 31 . COSPAR: 1960-Gamma-2. Apogee: 644 km (400 mi). Perigee: 363 km (225 mi). Inclination: 51.20 deg. Period: 94.60 min.
The first Thor/Ablestar launched from Cape Canaveral placed the Navy's Transit IB navigation satellite into orbit. This was the first navigation satellite to be placed in orbit. The Ablestar upper stage demonstrated the first engine restart in space. The Able-Star second stage demonstrated the first engine restart in space and the feasibility of using satellites as navigational aids. The first experimental Transit satellite to achieve orbit operated for 89 days. It transmitted on two frequency pairs to test the technique for refraction correction and to determine if the transmitted frequencies should be close together or far apart. It also tested a magnetic torque device for spacecraft attitude control - the first satellite to do so.

Dummy subsatellite - . Payload: GRAB dummy. Mass: 18 kg (39 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft: GRAB. Decay Date: 1960-07-17 . USAF Sat Cat: 33 . COSPAR: 1960-Gamma-3. Apogee: 615 km (382 mi). Perigee: 285 km (177 mi). Inclination: 51.30 deg. Period: 93.60 min. Mass model of GRAB ELINT satellite..

1960 April 15 - . 20:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena A.

Discoverer 11 - . Payload: KH-1 9008 / Agena A 1055. Mass: 790 kg (1,740 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1960-04-26 . USAF Sat Cat: 32 . COSPAR: 1960-Delta-1. Apogee: 603 km (374 mi). Perigee: 166 km (103 mi). Inclination: 80.40 deg. Period: 92.20 min. KH-1; film capsule recovery failed. Mission failed. Attitude control system malfunctioned..

1960 April 27 - . LV Family: Thor.

Last Thor IRBM squadron transferred to the RAF. - . The last of four 15-missile Thor IRBM squadrons were transferred to the Royal Air Force..

1960 May 13 - . 09:16 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta. FAILURE: Second stage attitude control failure.. Failed Stage: U.

Echo 1 - . Payload: A-10. Mass: 56 kg (123 lb). Nation: USA. Agency: NASA. Class: Communications. Type: Civilian communications satellite. Spacecraft: Echo. Decay Date: 1960-05-13 .
The first three-stage, NASA-developed Thor/Delta space booster was launched from Cape Canaveral, but the Echo passive communications satellite failed to achieve orbit due to a second stage malfunction. This booster was for NASA programs and used the basic Thor first stage with a modified Vanguard second stage as its upper stage configuration.

1960 June 22 - . 05:54 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Transit 2A - . Mass: 101 kg (222 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. USAF Sat Cat: 45 . COSPAR: 1960-Eta-1. Apogee: 988 km (613 mi). Perigee: 604 km (375 mi). Inclination: 66.70 deg. Period: 100.80 min.
A Thor/Ablestar booster placed a U.S. Navy Transit IIA research and development navigation satellite into orbit using the Ablestar second stage with a restart engine. A smaller parasitic radiation-measuring satellite, the Galactic Radiation Experiment Background (GREB), was also placed into orbit. This was the first time two satellites had been carried in "piggyback" alignment on a single booster. Also returned geodetic data. Similar to Transit 1B, it transmitted until 26 October 1962. A planned Transit 2B was considered redundant and never built.

Solrad 1 - . Payload: Grab 1. Mass: 19 kg (41 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: SIGINT. Spacecraft: GRAB. USAF Sat Cat: 46 . COSPAR: 1960-Eta-2. Apogee: 935 km (580 mi). Perigee: 596 km (370 mi). Inclination: 66.70 deg. Period: 100.20 min.
ELINT satellite, retransmitting to US ground stations signals from Soviet radar stations. Classified at time; official purpose and secondary payload collected solar radiation data. Officially: Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1960 June 22 - . 23:26 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10E. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Combat training launch - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1960 June 29 - . 22:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena A. FAILURE: Failure. Failed Stage: U.

Discoverer 12 - . Payload: KH-1 prototype. Mass: 790 kg (1,740 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1960-06-29 . KH-1 prototype; designed to test capsule recovery system; did not carry camera..

SRV - . Mass: 779 kg (1,717 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-1.

1960 August 10 - . 20:37 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena A.

Discoverer 13 - . Payload: KH-1 prototype / Agena A 1057. Mass: 850 kg (1,870 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1960-11-14 . USAF Sat Cat: 48 . COSPAR: 1960-Theta-1. Apogee: 683 km (424 mi). Perigee: 258 km (160 mi). Inclination: 82.80 deg. Period: 94.00 min.
A Thor/Agena A launched from Vandenberg AFB placed Discoverer XIII in orbit. On 11 August, the data capsule was ejected during the 17th pass and recovered Pacific Ocean near Hawaii by a Navy helicopter that was part of the 6593d Test Squadron's task force. Although the planned mid-air recovery was not made, the return of Discoverer XIII1s data capsule marked the first successful recovery of a man-made object ejected from an orbiting satellite. KH-1 prototype; designed to test capsule recovery system; did not carry camera; capsule successfully recovered from ocean.

1960 August 12 - . 09:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta.

Echo 1 - . Payload: A-11. Mass: 76 kg (167 lb). Nation: USA. Agency: NASA. Class: Technology. Type: Communications technology satellite. Spacecraft: Echo. Decay Date: 1968-05-24 . USAF Sat Cat: 49 . COSPAR: 1960-Iota-1. Apogee: 2,157 km (1,340 mi). Perigee: 966 km (600 mi). Inclination: 47.30 deg. Period: 117.30 min.
A Thor/Delta was launched from Cape Canaveral carrying NASA's Echo I, the first passive communications satellite to be placed into orbit. Balloon; passively relayed TV and voice transmissions. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1960 August 18 - . 19:57 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena A.

Discoverer 14 - . Payload: KH-1 9009 / Agena A 1056. Mass: 850 kg (1,870 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1960-09-16 . USAF Sat Cat: 54 . COSPAR: 1960-Kappa-1. Apogee: 803 km (498 mi). Perigee: 177 km (109 mi). Inclination: 79.60 deg. Period: 94.40 min. Discoverer XIV was launched from Vandenberg AFB aboard a Thor/Agena A booster.' KH-1; film capsule recovered 1.2 days later; 1st successful photosurveillance mission. First successful mission. Cameras operated satisfactorily..

1960 August 18 - . 19:58 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Ablestar. FAILURE: Exploded 2.5 minutes after launch.. Failed Stage: U.

Courier 1A - . Mass: 225 kg (496 lb). Nation: USA. Agency: DARPA. Class: Communications. Type: Military communications satellite. Spacecraft: Courier. Decay Date: 1960-08-18 . Discoverer XIV was launched from Vandenberg AFB aboard a Thor/Agena A booster.' Experimental communications sattelite..

1960 September 13 - . 22:14 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena A.

Discoverer 15 - . Payload: KH-1 9010 / Agena A 1058. Mass: 863 kg (1,902 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-1. Decay Date: 1960-10-18 . USAF Sat Cat: 57 . COSPAR: 1960-Mu-1. Apogee: 755 km (469 mi). Perigee: 200 km (120 mi). Inclination: 80.90 deg. Period: 94.10 min. KH-1; film capsule lost at sea. Mission failed. Attained orbit successfully. Capsule sank prior to retrieval..

1960 October 4 - . 17:50 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Courier 1B - . Mass: 230 kg (500 lb). Nation: USA. Agency: US Army. Class: Technology. Type: Communications technology satellite. Spacecraft: Courier. USAF Sat Cat: 58 . COSPAR: 1960-Nu-1. Apogee: 1,214 km (754 mi). Perigee: 967 km (600 mi). Inclination: 28.30 deg. Period: 107.10 min. Experimental communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1960 October 11 - . 21:53 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LE-8. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Combat training launch - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1960 October 26 - . 20:26 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B. FAILURE: Failure. Failed Stage: U.

Discoverer 16 - . Payload: KH-2 9011. Mass: 1,091 kg (2,405 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-2. Decay Date: 1960-10-26 . KH-1; mission failed..

SRV 506 - . Mass: 1,146 kg (2,526 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-2.

1960 November 12 - . 20:43 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 17 - . Payload: KH-2 9012 / Agena B 1062. Mass: 1,091 kg (2,405 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-2. Decay Date: 1960-12-29 . USAF Sat Cat: 61 . COSPAR: 1960-Omicron-1. Apogee: 984 km (611 mi). Perigee: 190 km (110 mi). Inclination: 81.70 deg. Period: 96.40 min.
The second Thor/Agena B to be launched from Vandenberg AFB was the first successful flight of the more advanced Lockheed Agena B upper stage. KH-1; film capsule recovered 2.1 days later. Mission failed. Obtained orbit successfully. Film separated before any camera operation leaving only 1.7 ft of film in capsule. On December 2, the Air Force revealed that exceedingly valuable information had been obtained from human tissues carried by Discoverer 17 (the cover story for the mission). The tissues had been exposed to an unexpectedly heavy dose of radiation for more than 50 hours in flight.

1960 November 23 - . 11:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta.

Tiros 2 - . Payload: Tiros B (A-2). Mass: 130 kg (280 lb). Nation: USA. Agency: NASA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Tiros. Decay Date: 2014-05-18 . USAF Sat Cat: 63 . COSPAR: 1960-Pi-1. Apogee: 610 km (370 mi). Perigee: 547 km (339 mi). Inclination: 48.50 deg. Period: 96.30 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1960 November 30 - . 19:50 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Ablestar. FAILURE: Failure. Failed Stage: 1.

Transit 3A - . Mass: 91 kg (200 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. Decay Date: 1960-11-30 . Destroyed by range safety; launched with Solrad 2. Thor shut down too early..

Solrad 2 - . Payload: Grab B. Mass: 18 kg (39 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft: GRAB. ELINT satellite..

1960 December 7 - . 20:20 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 18 - . Payload: KH-2 9013 / Agena B 1103. Mass: 1,240 kg (2,730 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-2. Decay Date: 1961-04-02 . USAF Sat Cat: 67 . COSPAR: 1960-Sigma-1. Apogee: 510 km (310 mi). Perigee: 233 km (144 mi). Inclination: 81.50 deg. Period: 92.00 min. KH-2; film capsule recovered 3.1 days later. First successful mission employing KH-2 camera system..

1960 December 13 - . 20:08 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LE-8. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Combat training launch - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1960 December 20 - . 20:32 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 19 - . Payload: Midas test payload. Mass: 1,060 kg (2,330 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Early warning satellite. Spacecraft Bus: WS-117. Spacecraft: Midas. Decay Date: 1961-01-23 . USAF Sat Cat: 68 . COSPAR: 1960-Tau-1. Apogee: 359 km (223 mi). Perigee: 186 km (115 mi). Inclination: 83.40 deg. Period: 90.00 min. A Thor/Agena B vehicle successfully launched Discoverer XIX into a polar orbit from Vandenberg AFB. The spacecraft carried a Project MIDAS test payload. Tested IR sensors for Midas program; did not carry camera or film capsule. .

1961 February 17 - . 20:25 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 20 - . Payload: KH-5 s/n 9014A / Agena B 1104. Mass: 1,110 kg (2,440 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-5. Decay Date: 1962-07-28 . USAF Sat Cat: 83 . COSPAR: 1961-Epsilon-1. Apogee: 491 km (305 mi). Perigee: 277 km (172 mi). Inclination: 80.80 deg. Period: 92.30 min. KH-5; film capsule not ejected. Mission failed. Program malfunctioned and capsule did not reenter. First attempted ARGON mission. Officially: Spacecraft Engaged in investigation of spaceflight techniques and technology (US Cat A)..

SRV 520 - . Mass: 1,274 kg (2,808 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-5. Decay Date: 1961-10-31 . USAF Sat Cat: 90 . COSPAR: 1961-Epsilon-4. Apogee: 327 km (203 mi). Perigee: 321 km (199 mi). Inclination: 80.70 deg. Period: 91.00 min.

1961 February 18 - . 22:58 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 21 - . Payload: Midas test payload. Mass: 1,110 kg (2,440 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Early warning satellite. Spacecraft Bus: WS-117. Spacecraft: Midas. Decay Date: 1962-04-20 . USAF Sat Cat: 84 . COSPAR: 1961-Zeta-1. Apogee: 458 km (284 mi). Perigee: 212 km (131 mi). Inclination: 80.60 deg. Period: 91.30 min. Tested IR sensors for Midas program; did not carry camera or film capsule..

1961 February 22 - . 03:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Transit 3B - . Mass: 112 kg (246 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. Decay Date: 1961-02-22 . USAF Sat Cat: 87 . COSPAR: 1961-Eta-1. Apogee: 225 km (139 mi). Perigee: 135 km (83 mi). Inclination: 28.40 deg. Period: 88.10 min.
Lofti 1 piggyback payload did not separate. Nevertheless Transit 3B returned useful data needed for design of the operational satellites. It carried a digital clock driven by the same oscillator that drove the transmitters. It transmitted timing signals governed by the clock and a 384-bit memory. This allowed testing of the techniques for loading the memory from the ground, the ability of the memory to hold a message in orbit, and the ability to encode the memory contents by means of a frequency modulation on one of the main transmitters. It was also shown that ±60° phase modulation could be used to transmit the contents of the satellite memory without degradation of the accuracy of the Doppler signal and Doppler measurements.

Lofti - . Mass: 26 kg (57 lb). Nation: USA. Agency: USAF. Spacecraft: Lofti. COSPAR: 1961-Eta-xx.

Lofti 1 - . Mass: 25 kg (55 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. Decay Date: 1961-03-30 . USAF Sat Cat: 87 . COSPAR: 1961-Eta-2. Apogee: 983 km (610 mi). Perigee: 188 km (116 mi). Inclination: 28.30 deg. Period: 96.40 min. Failed to separate from Transit 3B..

1961 March 25 - . 15:17 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta.

Explorer 10 - . Payload: P-14. Mass: 35 kg (77 lb). Nation: USA. Agency: NASA. Program: Explorer. Class: Astronomy. Type: Solar satellite. Spacecraft Bus: P. Spacecraft: P-14. Decay Date: 1961-06-30 . USAF Sat Cat: 98 . COSPAR: 1961-Kappa-1. Apogee: 181,100 km (112,500 mi). Perigee: 221 km (137 mi). Inclination: 33.00 deg. Period: 5,013.90 min. Magnetic field data. Decay date suspect Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

1961 March 30 - . 05:13 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10E. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Combat training launch - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1961 March 30 - . 20:34 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B. FAILURE: Failure. Failed Stage: U.

Discoverer 22 - . Payload: KH-2 9015. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-2. Decay Date: 1961-03-30 . KH-2; Mission failed..

SRV 509 - . Mass: 1,146 kg (2,526 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-2.

1961 April 8 - . 19:21 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 23 - . Payload: KH-5 s/n 9016A / Agena B 1106 / Capsule SRV 521. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-5. Decay Date: 1962-04-16 . USAF Sat Cat: 100 . COSPAR: 1961-Lambda-1. Apogee: 651 km (404 mi). Perigee: 295 km (183 mi). Inclination: 82.30 deg. Period: 94.10 min. KH-5; film capsule boosted into higher orbit, decayed 5/23/62. Mission failed. Loss of satellite control gas caused unstable condition. No recovery. Officially: Spacecraft Engaged in investigation of spaceflight techniques and technology (US Cat A)..

1961 June 8 - . 21:16 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B. FAILURE: Failure. Failed Stage: U.

Discoverer 24 - . Payload: KH-5 s/n 9018A. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-5. Decay Date: 1961-06-08 . KH-5. Mission failed..

SRV 541 - . Mass: 1,274 kg (2,808 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-5.

1961 June 16 - . 23:02 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 25 - . Payload: KH-2 9017 / Agena B 1107. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-2. Decay Date: 1961-07-12 . USAF Sat Cat: 108 . COSPAR: 1961-Xi-1. Apogee: 404 km (251 mi). Perigee: 222 km (137 mi). Inclination: 82.10 deg. Period: 90.80 min. KH-2; film capsule recovered 2.1 days later. Capsule recovered from water on orbit 32. Streaks throughout film..

1961 June 20 - . 23:54 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10E. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Combat training launch - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1961 June 29 - . 04:22 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Transit 4A - . Mass: 79 kg (174 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. USAF Sat Cat: 116 . COSPAR: 1961-Omicron-1. Apogee: 986 km (612 mi). Perigee: 865 km (537 mi). Inclination: 66.80 deg. Period: 103.50 min. Transits 4A and 4B were drum-shaped instead of spherical to provide more space for solar cells. In addition, operational 150-and 400-MHz frequencies were used for the first time. Carried SNAP-3A nuclear power source..

Injun 1 - . Mass: 25 kg (55 lb). Nation: USA. Agency: USN. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Injun. USAF Sat Cat: 117 . COSPAR: 1961-Omicron-2. Apogee: 992 km (616 mi). Perigee: 869 km (539 mi). Inclination: 66.80 deg. Period: 103.60 min. Dual launch; failed to separate from Solrad 3; still returned radiation data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

Solrad 3 - . Payload: Grab 2. Mass: 18 kg (39 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft: GRAB. COSPAR: 1961-Omicron-xx. ELINT satellite, retransmitting to US ground stations signals from Soviet radar stations. Classified at time; official purpose and secondary payload collected solar radiation data..

1961 July 7 - . 23:29 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 26 - . Payload: KH-2 9019 / Agena B 1109. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-2. Decay Date: 1961-12-05 . USAF Sat Cat: 160 . COSPAR: 1961-Pi-1. Apogee: 803 km (498 mi). Perigee: 228 km (141 mi). Inclination: 82.90 deg. Period: 94.90 min. KH-2; film capsule recovered 2.1 days later. Main camera malfunctioned on pass 22..

1961 July 12 - . 10:25 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta.

Tiros 3 - . Payload: Tiros C (A-3). Mass: 129 kg (284 lb). Nation: USA. Agency: NASA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Tiros. USAF Sat Cat: 162 . COSPAR: 1961-Rho-1. Apogee: 790 km (490 mi). Perigee: 723 km (449 mi). Inclination: 47.90 deg. Period: 100.00 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1961 July 21 - . 22:35 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B. FAILURE: Failure. Failed Stage: U.

Discoverer 27 - . Payload: KH-5 s/n 9020A. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-5. Decay Date: 1961-07-21 . KH-5; destroyed by range safety. Mission failed..

SRV 524 - . Mass: 1,274 kg (2,808 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-5.

1961 August 4 - . 00:01 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena B. FAILURE: Failure. Failed Stage: U.

Discoverer 28 - . Payload: KH-2 9021. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-2. Decay Date: 1961-08-03 . KH-2; Mission failed..

SRV 512 - . Mass: 1,146 kg (2,526 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-2.

1961 August 16 - . 03:21 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta.

Explorer 12 - . Payload: EPE A (S-3). Mass: 38 kg (83 lb). Nation: USA. Agency: NASA. Program: Explorer. Class: Astronomy. Type: Solar satellite. Spacecraft: EPE. Decay Date: 1963-08-31 . USAF Sat Cat: 170 . COSPAR: 1961-Upsilon-1. Apogee: 76,620 km (47,600 mi). Perigee: 790 km (490 mi). Inclination: 33.40 deg. Period: 1,587.30 min. Radiation and solar wind data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1961 August 25 - . LV Family: Thor, Atlas. Launch Vehicle: Atlas Agena D, Thor Agena D.

Lockheed contracted for the Agena D upper stage. - . Lockheed was awarded an Air Force letter contract to develop and manufacture the first 12 flight models of the standardized configuration Agena D (Standard Stage OlA, SS-01A)..

1961 August 30 - . 20:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 29 - . Payload: KH-3 s/n 9023 / Agena B 1112. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-3. Decay Date: 1961-09-09 . USAF Sat Cat: 181 . COSPAR: 1961-Psi-1. Apogee: 542 km (336 mi). Perigee: 152 km (94 mi). Inclination: 82.10 deg. Period: 91.50 min. KH-3; film capsule recovered 2.1 days later. First use of KH-3 camera system. All frames out of focus..

1961 September 6 - . 22:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10E. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Combat training launch - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1961 September 12 - . 19:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 30 - . Payload: KH-3 s/n 9022 / Agena B 1113. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-3. Decay Date: 1961-12-11 . USAF Sat Cat: 182 . COSPAR: 1961-Omega-1. Apogee: 557 km (346 mi). Perigee: 219 km (136 mi). Inclination: 82.50 deg. Period: 92.30 min. KH-3; film capsule recovered 2.1 days later. Best mission to date. Same out-of-focus condition as in 9023..

1961 September 17 - . 21:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 31 - . Payload: KH-3 s/n 9024 / Agena B 1114. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-3. Decay Date: 1961-10-26 . USAF Sat Cat: 186 . COSPAR: 1961-A-Beta-1. Apogee: 403 km (250 mi). Perigee: 231 km (143 mi). Inclination: 82.60 deg. Period: 90.80 min. KH-3; film capsule recovery failed. Mission failed. Power failure and loss of control gas on orbit 33..

1961 October 13 - . 19:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 32 - . Payload: KH-3 s/n 9025 / Agena B 1115. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-3. Decay Date: 1961-11-13 . USAF Sat Cat: 189 . COSPAR: 1961-A-Gamma-1. Apogee: 391 km (242 mi). Perigee: 233 km (144 mi). Inclination: 81.60 deg. Period: 90.70 min. The 100th successful firing of a Thor placed Discoverer XXXII in orbit. KH-3; film capsule recovered 1.1 days later. Capsule recovered on orbit 18. 96% of film out of focus..

1961 October 23 - . 19:23 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B. FAILURE: Failure. Failed Stage: U.

Discoverer 33 - . Payload: KH-3 s/n 9026. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-3. Decay Date: 1961-10-23 . KH-3; Mission failed..

SRV 513 - . Mass: 1,250 kg (2,750 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-3.

1961 November 5 - . 20:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 34 - . Payload: KH-3 s/n 9027 / Agena B 1117. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-3. Decay Date: 1962-12-07 . USAF Sat Cat: 197 . COSPAR: 1961-A-Epsilon-1. Apogee: 859 km (533 mi). Perigee: 231 km (143 mi). Inclination: 82.40 deg. Period: 95.60 min. KH-3; film capsule recovery not attempted. Mission failed. Improper launch angle resulted in extreme orbit..

SRV 553 - . Mass: 1,250 kg (2,750 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-3. COSPAR: 1961-A-Epsilon-x.

1961 November 15 - . 21:23 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 35 - . Payload: KH-3 s/n 9028 / Agena B 1118. Mass: 2,100 kg (4,600 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-3. Decay Date: 1961-12-03 . USAF Sat Cat: 201 . COSPAR: 1961-A-Zeta-1. Apogee: 278 km (172 mi). Perigee: 238 km (147 mi). Inclination: 81.60 deg. Period: 89.70 min. KH-3; film capsule recovered 1.1 days later. All cameras operated satisfactorily. Grainy emulsion noted..

1961 November 15 - . 22:19 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Transit 4B - . Mass: 86 kg (189 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. USAF Sat Cat: 202 . COSPAR: 1961-A-Eta-1. Apogee: 1,104 km (685 mi). Perigee: 953 km (592 mi). Inclination: 32.40 deg. Period: 105.70 min.
Together, Transits 4A and 4B allowed the determination of harmonics in the Earth's gravity field that had not yet been evaluated, and they also allowed firm navigational ties to be established from continent to continent as well as to isolated islands. As a result, it was discovered that the position of Hawaii was incorrect by 1 km. Carried SNAP 3 nuclear power source.

TRAAC - . Mass: 109 kg (240 lb). Nation: USA. Agency: USN. Class: Technology. Type: Navigation technology satellite. Spacecraft: TRAAC. USAF Sat Cat: 205 . COSPAR: 1961-A-Eta-2. Apogee: 1,107 km (687 mi). Perigee: 956 km (594 mi). Inclination: 32.40 deg. Period: 105.80 min. Transit Research and Attitude Control. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1961 December 6 - . 01:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LE-8. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Combat training launch - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1961 December 12 - . 20:40 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 36 - . Payload: KH-3 s/n 9029 / Agena B 1119. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-3. Decay Date: 1962-03-08 . USAF Sat Cat: 213 . COSPAR: 1961-A-Kappa-1. Apogee: 173 km (107 mi). Perigee: 131 km (81 mi). Inclination: 89.50 deg. Period: 87.50 min. KH-3; film capsule recovered 4.1 days later. Best mission to date..

Oscar 1 - . Mass: 5.00 kg (11.00 lb). Nation: USA. Agency: USAF. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Oscar. Decay Date: 1962-01-31 . USAF Sat Cat: 214 . COSPAR: 1961-A-Kappa-2. Apogee: 474 km (294 mi). Perigee: 245 km (152 mi). Inclination: 81.20 deg. Period: 91.80 min.
The first Oscar Phase I amateur satellite was launched piggyback with Discover 36. A group of enthusiasts in California formed Project OSCAR and persuaded the United States Air Force to replace ballast on the Agena upper stage with the 4.5 kg OSCAR I package. The satellite was box shaped with a single monopole antenna and battery powered. The 140 mW transmitter onboard discharged its batteries after three weeks. 570 Amateurs in 28 countries reported receiving its simple 'HI-HI' morse code signals on the VHF 2 meter band (144.983 MHz) until January 1, 1962. The speed of the HI-HI message was controlled by a temperature sensor inside the spacecraft. OSCAR I re-entered the atmosphere January 31, 1962 after 312 revolutions. Additional Details: here....

1962 January 9 - . LV Family: Thor.

Surplus Thor IRBM's to be used as space boosters. - . The Defense Department announced its approval of the conversion of the Thor IRBM to a space booster..

1962 January 13 - . 21:41 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B. FAILURE: Failure. Failed Stage: U.

Discoverer 37 - . Payload: KH-3 s/n 9030. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-3. Decay Date: 1962-01-13 . KH-3. Mission failed. Last attempted flight of KH-3 series..

SRV 571 - . Mass: 1,250 kg (2,750 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-3.

1962 January 15 - . 11:07 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor DSV-2D.

AVT-1 Satellite test - . Nation: USA. Agency: USAF. Apogee: 1,400 km (800 mi).

1962 January 24 - . 09:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Ablestar. FAILURE: Failure. Failed Stage: U.

Lofti 2 - . Mass: 99 kg (218 lb). Nation: USA. Agency: USN. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Lofti 2. Decay Date: 1962-01-24 . Carried 5 satellites..

Injun 2 - . Nation: USA. Agency: USAF. Spacecraft: Injun.

Surcal - . Nation: USA. Agency: USAF. Class: Surveillance. Type: Radar calibration target. Spacecraft: Surcal.

Solrad 4 - . Payload: Grab D. Mass: 18 kg (39 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft: GRAB. ELINT satellite..

Secor - . Nation: USA. Agency: USAF. Spacecraft: SECOR.

1962 Feb - . LV Family: Thor. Launch Vehicle: Thor DSV-2D.

Standard Thor to use three strap-on, solid-propellant motors. - . Space Systems Division asked the Douglas Aircraft Company to define the performance and design of a Standard Thor (DSV-2C) using three strap-on, solid-propellant motors..

1962 February 8 - . 12:43 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta.

Tiros 4 - . Payload: Tiros D (A-9). Mass: 129 kg (284 lb). Nation: USA. Agency: NASA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Tiros. USAF Sat Cat: 226 . COSPAR: 1962-Beta-1. Apogee: 812 km (504 mi). Perigee: 693 km (430 mi). Inclination: 48.30 deg. Period: 99.90 min. Returned 32593 cloud cover photos. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1962 February 21 - . 18:44 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B. FAILURE: Partial failure. Agena failed to restart to circularize orbit.. Failed Stage: U.

Ferret 1 - . Payload: Ferret 1 / Agena B 2301. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1962-03-04 . USAF Sat Cat: 242 . COSPAR: 1962-Delta-1. Apogee: 219 km (136 mi). Perigee: 169 km (105 mi). Inclination: 81.90 deg. Period: 88.30 min.

1962 February 27 - . 19:39 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 38 - . Payload: KH-4 s/n 9031 / Agena B 1123. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-03-21 . USAF Sat Cat: 247 . COSPAR: 1962-Epsilon-1. Apogee: 277 km (172 mi). Perigee: 207 km (128 mi). Inclination: 82.20 deg. Period: 89.40 min. First mission of the KH-4 series. Much of film slightly out of focus.. Capsule recovered 4.1 days later..

1962 March 7 - . 16:06 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta.

OSO 1 - . Payload: OSO A (S-16). Mass: 208 kg (458 lb). Nation: USA. Agency: NASA. Class: Astronomy. Type: Solar satellite. Spacecraft: OSO. Decay Date: 1981-10-08 . USAF Sat Cat: 255 . COSPAR: 1962-Zeta-1. Apogee: 553 km (343 mi). Perigee: 522 km (324 mi). Inclination: 32.80 deg. Period: 95.30 min. Orbiting Solar Observatory; solar flare observations. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1962 March 19 - . 23:28 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10E. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Combat training launch - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi).

1962 April 18 - . 00:54 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B.

Discoverer 39 - . Payload: KH-4 s/n 9032 / Agena B 1124. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-05-28 . USAF Sat Cat: 276 . COSPAR: 1962-Lambda-1. Apogee: 540 km (330 mi). Perigee: 158 km (98 mi). Inclination: 73.50 deg. Period: 91.60 min. KH-4. Best mission to date..

1962 April 26 - . 18:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta.

Ariel 1 - . Payload: UK 1 (S-51). Mass: 60 kg (132 lb). Nation: UK. Agency: NASA. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Ariel. Decay Date: 1976-03-31 . USAF Sat Cat: 285 . COSPAR: 1962-Omicron-1. Apogee: 1,203 km (747 mi). Perigee: 398 km (247 mi). Inclination: 53.80 deg. Period: 100.80 min. Ionospheric studies; returned X-ray, ionospheric, cosmic ray data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1962 April 29 - . 00:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

KH-4 9033 - . Payload: KH-4 s/n 9033 / Agena B 1125. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-05-26 . USAF Sat Cat: 290 . COSPAR: 1962-Rho-1. Apogee: 475 km (295 mi). Perigee: 180 km (110 mi). Inclination: 73.10 deg. Period: 91.10 min. KH-4. Mission failed. Parachute ejector squibs holding parachute container cover failed to fire. No recovery..

1962 May 1 - . Launch Site: Cape Canaveral. LV Family: Atlas, Thor.

Contract to the Thor DSV-2C. - .
Space Systems Division awarded a letter contract to the Douglas Aircraft Company for the design, development, fabrication, assembly, and pre-flight testing of one Douglas Space Vehicle 2C (DSV-2C). This was originally proposed by the company in June 1961. The DSV-2C, later SLV-2A in Air Force nomenclature, was the Thrust Augmented Thor (TAT) that was the first attempt to combine solid and liquid fuel engines in a single space booster. Intended to fill the gap between the basic Thor booster (LV-2) and the Atlas (SLV-3), the TAT was to use three TX-33-52 solid-pro-pellant Sergeant rocket motors installed around the engine section and attached to the three main thrust beams. Each of the solid-rocket motors would generate 54,500 pounds of thrust for 27 seconds after lift-off. This increased the total thrust of the vehicle to over 330,000 pounds, vastly improving its payload capabilities. The new TAT would have a 50 percent improvement in payload capacity since it could place 1,450 pounds into a 300-NM circular orbit when launched from Cape Canaveral - a 500-pound increase over the present Thor/Agena booster.

1962 May 2 - . 23:44 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE1. LV Family: Thor. Launch Vehicle: Thor DSV-2E.

TIGERFISH test - . Nation: USA. Agency: USAF. Apogee: 500 km (310 mi).

1962 May 10 - . 12:07 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Ablestar. FAILURE: Able-Star failed to ignite.. Failed Stage: U.

Anna 1A - . Payload: Anna 1A. Mass: 160 kg (350 lb). Nation: USA. Agency: US Army. Class: Earth. Type: Geodetic satellite. Spacecraft: Anna. Decay Date: 1962-05-10 . USN, USAF, US Army, NASA joint program..

1962 May 15 - . 19:36 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B.

KH-5 9034A - . Payload: KH-5 s/n 9034A/Agena B 1126. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-5. Decay Date: 1963-11-26 . USAF Sat Cat: 292 . COSPAR: 1962-Sigma-1. Apogee: 550 km (340 mi). Perigee: 283 km (175 mi). Inclination: 82.30 deg. Period: 93.00 min. KH-5; film capsule recovered 4.1 days later. First successful KH-5 mission. Officially: Spacecraft Engaged in investigation of spaceflight techniques and technology (US Cat A)..

1962 May 29 - . LV Family: Atlas, Thor. Launch Vehicle: Atlas Agena D, Thor Agena D.

Standardized Agena D upper stage for use with Atlas and Thor. - .
The Defense Department and NASA signed a joint agreement that authorized the Defense Department to develop a standardized Agena D upper stage for joint use with Atlas and Thor booster stages. The Agena would use present flight-proven equipment, stress simplification of vehicle design, permit adaptability to advanced components without any basic changes, and permit production at lower costs.

1962 May 30 - . 01:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena B.

KH-4 9035 - . Payload: KH-4 s/n 9035 / Agena B 1128. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-06-11 . USAF Sat Cat: 302 . COSPAR: 1962-Phi-1. Apogee: 350 km (210 mi). Perigee: 192 km (119 mi). Inclination: 74.10 deg. Period: 89.90 min. KH-4; film capsule recovered 3.1 days later. Slight corona static on film..

1962 June 2 - . 00:31 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

KH-4 9036 - . Payload: KH-4 s/n 9036 / Agena B 1127. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-06-28 . USAF Sat Cat: 304 . COSPAR: 1962-Chi-1. Apogee: 401 km (249 mi). Perigee: 211 km (131 mi). Inclination: 74.50 deg. Period: 90.60 min. KH-4. Mission failed. During air catch, chute tore loose. Capsule sank..

Oscar 2 - . Mass: 10 kg (22 lb). Nation: USA. Agency: USAF. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Oscar. Decay Date: 1962-06-21 . USAF Sat Cat: 305 . COSPAR: 1962-Chi-2. Apogee: 339 km (210 mi). Perigee: 188 km (116 mi). Inclination: 74.20 deg. Period: 89.80 min.
OSCAR II was launched piggyback with a United States Air Force satellite. OSCAR II was very similar to OSCAR I. Differences included (1) changing the surface thermal coatings to achieve a cooler internal spacecraft environment, (2) modifying the sensing system so the satellite temperature could be measured accurately as the batteries decayed, and (3) lowering the transmitter power output to 100 mW to extend the life of the onboard battery. OSCAR II lasted 18 days ceasing operation on June 20, 1962 and re-entered June 21, 1962.

1962 June 4 - . 09:44 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE1. LV Family: Thor. Launch Vehicle: Thor DSV-2E.

BLUEGILL Nuclear test - . Nation: USA. Agency: USAF. Apogee: 500 km (310 mi).
Initial attempt to launch a live nuclear weapon using the Thor IRBM from Johnston Atoll. The range safety radar had been unreliable before launch,. Five minutes after launch, after shutdown of the booster, the Johnston missile tracking system failed. Unable to monitor the warhead's flight path, the range safety officer destroyed it 10 minutes later, prior to warhead detonation.

1962 June 18 - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B.

Ferret 2 - . Payload: Ferret 2 / Agena B 2312. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1963-10-30 . USAF Sat Cat: 308 . COSPAR: 1962-Omega-2. Apogee: 377 km (234 mi). Perigee: 347 km (215 mi). Inclination: 82.10 deg. Period: 91.80 min.

FTV 2312 - . Payload: Ferret 2. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1963-10-30 . USAF Sat Cat: 308 . COSPAR: 1962-Omega-1. Apogee: 170 km (100 mi). Perigee: 161 km (100 mi). Inclination: 82.20 deg. Period: 87.80 min.

1962 June 19 - . 00:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LE-8. LV Family: Thor. Launch Vehicle: Thor DM-18A.

Combat training launch - . Nation: USA. Agency: RAF. Apogee: 520 km (320 mi). A Royal Air Force crew launched the 22d and last operational test Thor IRBM (PGM-17A) from Vandenberg AFB. First launch and first missile was fired from Vandenberg AFB on 16 December 1958.

1962 June 19 - . 12:19 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta.

Tiros 5 - . Payload: Tiros E (A-50). Mass: 129 kg (284 lb). Nation: USA. Agency: NASA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Tiros. USAF Sat Cat: 309 . COSPAR: 1962-A-Alpha-1. Apogee: 880 km (540 mi). Perigee: 580 km (360 mi). Inclination: 58.10 deg. Period: 99.40 min. Returned 58226 cloud cover images. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1962 June 20 - . 08:46 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE1. LV Family: Thor. Launch Vehicle: Thor DSV-2E. FAILURE: Failure. Failed Stage: 1.

STARFISH Nuclear test - . Nation: USA. Agency: USAF. Apogee: 10 km (6 mi).

1962 June 23 - . 00:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

KH-4 9037 - . Payload: KH-4 s/n 9037 / Agena B 1129. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-07-07 . USAF Sat Cat: 315 . COSPAR: 1962-A-Beta-1. Apogee: 314 km (195 mi). Perigee: 199 km (123 mi). Inclination: 75.10 deg. Period: 89.60 min. KH-4. Corona static occurs on some film..

1962 June 28 - . 01:09 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena D.

KH-4 9038 - . Payload: KH-4 s/n 9038 / Agena D 1151. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-09-14 . USAF Sat Cat: 316 . COSPAR: 1962-A-Gamma-1. Apogee: 698 km (433 mi). Perigee: 205 km (127 mi). Inclination: 76.00 deg. Period: 93.60 min.
The first Agena D (#1151) upper stage vehicle was successfully flown on a Thor booster (#340) launched from Vandenberg AFB. The Lockheed Agena D was a redesign of the basic Agena B and was intended to be the standard stage vehicle for most Defense Department and NASA programs. The program was begun in August 1961, revised and accelerated in November, and had its first flight in June 1962. KH-4; film capsule recovered 4.1 days later. Severe corona static.

1962 July 9 - . 08:46 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE1. LV Family: Thor. Launch Vehicle: Thor DSV-2E.

STARFISH PRIME Nuclear test - . Nation: USA. Agency: USAF. Apogee: 400 km (240 mi).
Successful high-altitude test of a Thor IRBM with a live nuclear warhead. The payload included test instrumentation and a W-49 warhead/Mk-4 re-entry vehicle. The 1.45 megaton bomb exploded at an altitude of 400 km. The explosion was visible 2,600 km away, at Kwajalein Atoll; an artificial aurora lasted seven minutes. The unforeseen and most militarily significant effect was the electromagnetic pulse (EMP) generated by the test. This caused power mains surges in Oahu, knocking out street lights, blowing fuses and circuit breakers, and triggering burglar alarms (and this in the days before microelectronics). The explosion supercharged the Van Allen radiation belts, resulting in several satellites malfunctioning.

1962 July 10 - . 08:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta.

Telstar 1 - . Mass: 77 kg (169 lb). Nation: USA. Agency: ATT. Class: Communications. Type: Civilian communications satellite. Spacecraft: Telstar. USAF Sat Cat: 340 . COSPAR: 1962-A-Epsilon-1. Apogee: 5,643 km (3,506 mi). Perigee: 945 km (587 mi). Inclination: 44.80 deg. Period: 157.80 min.
A NASA Thor/Delta boosted Telstar, the first commercially developed international communications satellite, into orbit. First commercial comsat; active repeater. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1962 July 18 - . 09:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor DSV-2D.

AVT 2 Satellite test - . Nation: USA. Agency: USAF. Apogee: 1,484 km (922 mi).

1962 July 21 - . 00:56 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B.

KH-4 9039 - . Payload: KH-4 s/n 9039 / Agena B 1130. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-08-14 . USAF Sat Cat: 344 . COSPAR: 1962-A-Eta-1. Apogee: 376 km (233 mi). Perigee: 206 km (128 mi). Inclination: 70.00 deg. Period: 90.30 min. KH-4. Aborted after 6 photo passes. Heavy corona and radiation fog..

1962 July 26 - . 09:13 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE1. LV Family: Thor. Launch Vehicle: Thor DSV-2E. FAILURE: Thor exploded on liftoff.. Failed Stage: 1.

BLUEGILL PRIME Nuclear test - . Nation: USA. Agency: USAF. Apogee: 0 km (0 mi).
Second attempt to launch a nuclear weapon using the Thor IRBM. The payload consisted of two re-entry vehicles, one with an instrument pod, the other with the warhead. The missile engine malfunctioned immediately on ignition. Range safety fired the destruct system whille the missile was still on the launch pad. The Johnston Island launch complex was heavily damaged and contaminated with plutonium. Three months of repairs and decontamination were necessary before tests could resume.

1962 July 28 - . 00:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

KH-4 9040 - . Payload: KH-4 s/n 9040 / Agena B 1131. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-08-24 . USAF Sat Cat: 345 . COSPAR: 1962-A-Theta-1. Apogee: 403 km (250 mi). Perigee: 204 km (126 mi). Inclination: 71.00 deg. Period: 90.60 min. KH-4; film capsule recovered 4.1 days later. No filters on slave horizon cameras. Heavy corona and radiation fog..

1962 August 2 - . 00:17 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena D.

KH-4 9041 - . Payload: KH-4 s/n 9041 / Agena D 1152. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-08-22 . USAF Sat Cat: 360 . COSPAR: 1962-A-Kappa-1. Apogee: 423 km (262 mi). Perigee: 212 km (131 mi). Inclination: 83.00 deg. Period: 90.80 min. KH-4; film capsule recovered 4.1 days later. Severe corona and radiation fog..

1962 August 29 - . 01:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor Agena D.

KH-4 9044 - . Payload: KH-4 s/n 9044 / Agena D 1153. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-09-10 . USAF Sat Cat: 377 . COSPAR: 1962-A-Sigma-1. Apogee: 400 km (240 mi). Perigee: 187 km (116 mi). Inclination: 65.20 deg. Period: 90.40 min. KH-4; film capsule recovered 4.1 days later. Erratic vehicle attitude. Radiation fog minimal..

1962 September 1 - . 20:39 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B.

KH-5 9042A - . Payload: KH-5 s/n 9042A/Agena B 1132. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-5. Decay Date: 1964-10-26 . USAF Sat Cat: 385 . COSPAR: 1962-A-Upsilon-1. Apogee: 639 km (397 mi). Perigee: 293 km (182 mi). Inclination: 82.80 deg. Period: 94.00 min. KH-5. Mission failed. Parachute shrouds parted during air catch, capsule sank. Officially: Spacecraft Engaged in investigation of spaceflight techniques and technology (US Cat A)..

SRV 600 - . Mass: 1,274 kg (2,808 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-5. COSPAR: 1962-A-Upsilon-x.

1962 September 17 - . 23:46 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

KH-4 9043 / TRS 1 (ERS 2) - . Payload: KH-4 s/n 9043 / TRS 1 (ERS 2) / Agena B 1133. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-11-16 . USAF Sat Cat: 396 . COSPAR: 1962-A-Chi-1. Apogee: 668 km (415 mi). Perigee: 204 km (126 mi). Inclination: 81.80 deg. Period: 93.30 min. KH-4; film capsule recovered 1.1 days later; ERS-2 subsatellite failed to deploy. Capping shutter malfunction, slight corona and radiation fog..

TRS - . Payload: ERS 2. Mass: 45 kg (99 lb). Nation: USA. Agency: USAF. Class: Earth. Type: Magnetosphere satellite. Spacecraft: ERS. COSPAR: 1962-A-Chi-xx.

1962 September 18 - . 08:53 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta.

Tiros 6 - . Payload: Tiros F2 (A-51). Mass: 127 kg (279 lb). Nation: USA. Agency: NASA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Tiros. USAF Sat Cat: 397 . COSPAR: 1962-A-Psi-1. Apogee: 654 km (406 mi). Perigee: 631 km (392 mi). Inclination: 58.30 deg. Period: 97.60 min. Returned 66674 cloud cover images. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1962 September 29 - . 06:05 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena B.

Alouette 1 - . Payload: Alouette 1 / TAVE. Mass: 145 kg (319 lb). Nation: Canada. Agency: Clemson. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Alouette. USAF Sat Cat: 424 . COSPAR: 1962-B-Alpha-1. Apogee: 1,022 km (635 mi). Perigee: 987 km (613 mi). Inclination: 80.50 deg. Period: 105.20 min. Ionospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

TAVE - . Payload: TAVE. Nation: USA. Agency: NASA. Spacecraft: TAVE. USAF Sat Cat: 426 . COSPAR: 1962-B-Alpha-2. Apogee: 1,019 km (633 mi). Perigee: 993 km (617 mi). Inclination: 80.50 deg. Period: 105.20 min. Thor Agena Vibration Experiment.

1962 September 29 - . 23:34 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor Agena D.

KH-4 9045 - . Payload: KH-4 s/n 9045 / Agena D 1154. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-10-08 . USAF Sat Cat: 427 . COSPAR: 1962-B-Beta-1. Apogee: 388 km (241 mi). Perigee: 190 km (110 mi). Inclination: 65.40 deg. Period: 90.30 min. KH-4. First use of stellar camera, erratic vehicle attitude, numerous light leaks..

1962 October 2 - . 22:11 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta A.

Explorer 14 - . Payload: EPE B (S-3A). Mass: 40 kg (88 lb). Nation: USA. Agency: NASA. Program: Explorer. Class: Astronomy. Type: Solar satellite. Spacecraft: EPE. Decay Date: 1964-12-31 . USAF Sat Cat: 432 . COSPAR: 1962-B-Gamma-1. Apogee: 96,229 km (59,793 mi). Perigee: 2,558 km (1,589 mi). Inclination: 42.30 deg. Period: 2,184.60 min. Magnetosphere studies. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1962 October 9 - . 18:35 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

KH-5 9046A - . Payload: KH-5 s/n 9046A/Agena B 1134. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-5. Decay Date: 1962-10-16 . USAF Sat Cat: 436 . COSPAR: 1962-B-Epsilon-1. Apogee: 427 km (265 mi). Perigee: 213 km (132 mi). Inclination: 82.00 deg. Period: 91.00 min. KH-5; film capsule recovered 4.1 days later. 50% of stellar terrain film was blank due to shutter malfunction. Officially: Spacecraft Engaged in investigation of spaceflight techniques and technology (US Cat A)..

SRV 603 - . Mass: 1,274 kg (2,808 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-5. COSPAR: 1962-B-Epsilon-x.

1962 October 16 - . 09:14 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Thor. Launch Vehicle: Thor DSV-2E. FAILURE: At 86 seconds after launch a booster failure occurred and the missile began tumbling.. Failed Stage: 1.

BLUEGILL DOUBLE PRIME Nuclear test - . Nation: USA. Agency: USAF. Apogee: 10 km (6 mi).
The third attempt to launch a nuclear warhead using a Thor IRBM. At 86 seconds after launch a booster failure occurred and the missile began tumbling. Range safety destroyed the errant booster at 156 seconds after launch. Some radioactive fallout from the warhead was detected on Johnston Atoll.

1962 October 26 - . 09:44 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE1. LV Family: Thor. Launch Vehicle: Thor DSV-2E.

BLUEGILL TRIPLE PRIME Nuclear test - . Nation: USA. Agency: USAF. Apogee: 500 km (310 mi).
On the fourth attempt, a Thor IRBM was used to launch a Mk 4 Re-entry Vehicle containing a 186 kg W-50 nuclear warhead of either 200 or 400 kilotons yield. The detonation occurred at an altitude of 50 km, 31 km SSW of Johnston Atoll. A fireball formed, the colourful afterglow continuing for 30 minutes of the explosion. At this altitude the extensive disruption of the ionosphere seen in later explosions did not occur.

1962 October 26 - . 16:14 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor Agena D.

Starfish Radiation 1 - . Payload: Star-Rad 1 / Agena D 1401. Mass: 1,100 kg (2,400 lb). Nation: USA. Agency: USAF. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Starfish. Decay Date: 1967-10-05 . USAF Sat Cat: 444 . COSPAR: 1962-B-Kappa-1. Apogee: 5,458 km (3,391 mi). Perigee: 197 km (122 mi). Inclination: 71.40 deg. Period: 146.50 min. Artificial radiation data..

1962 October 27 - . 23:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta A.

Explorer 15 - . Payload: EPE C (S-3C SERB). Mass: 45 kg (99 lb). Nation: USA. Agency: NASA. Program: Explorer. Class: Astronomy. Type: Solar satellite. Spacecraft: EPE. Decay Date: 1978-12-19 . USAF Sat Cat: 445 . COSPAR: 1962-B-Lambda-1. Apogee: 17,610 km (10,940 mi). Perigee: 306 km (190 mi). Inclination: 17.90 deg. Period: 314.70 min. Radiation decay data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1962 October 31 - . 08:03 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Anna 1B - . Mass: 161 kg (354 lb). Nation: USA. Agency: USN. Class: Earth. Type: Geodetic satellite. Spacecraft: Anna. USAF Sat Cat: 446 . COSPAR: 1962-B-Mu-1. Apogee: 1,181 km (733 mi). Perigee: 1,075 km (667 mi). Inclination: 50.10 deg. Period: 107.90 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1962 November 1 - . 11:54 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Thor. Launch Vehicle: Thor DSV-2E.

KINGFISH Nuclear test - . Nation: USA. Agency: USAF. Apogee: 500 km (310 mi).
A Thor IRBM was used to launch a Mk 4 Reentry Vehicle containing a 186 kg W-50 nuclear warhead of either 200 or 400 kilotons yield. The detonation occurred at an altitude of 98 km, 69 km SSW of Johnston Atoll, and resulted in dramatic aurora-like effects visible as far away as Hawaii. More notably, the explosion had a massive effect on the ionosphere which disrupted radio communications over the entire central Pacific for three hours.

1962 November 5 - . 22:04 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

KH-4 9047 - . Payload: KH-4 s/n 9047 / Agena B 1136. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-12-03 . USAF Sat Cat: 453 . COSPAR: 1962-B-Omicron-1. Apogee: 403 km (250 mi). Perigee: 208 km (129 mi). Inclination: 75.00 deg. Period: 90.60 min. KH-4; film capsule; film capsule recovered 4.1 days later. Camera door malfunctioned, flare degraded 15% of film..

SRV 599 - . Mass: 1,200 kg (2,600 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4. COSPAR: 1962-B-Omicron-x.

1962 November 24 - . 22:01 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor Agena B.

KH-4 9048 - . Payload: KH-4 s/n 9048 / Agena B 1135. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-12-13 . USAF Sat Cat: 481 . COSPAR: 1962-B-Rho-1. Apogee: 339 km (210 mi). Perigee: 206 km (128 mi). Inclination: 65.00 deg. Period: 89.90 min. KH-4. Some film exposed through base..

1962 December 4 - . 21:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor Agena D.

KH-4 9049 - . Payload: KH-4 s/n 9049 / Agena D 1155. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1962-12-08 . USAF Sat Cat: 490 . COSPAR: 1962-B-Sigma-1. Apogee: 273 km (169 mi). Perigee: 194 km (120 mi). Inclination: 65.10 deg. Period: 89.20 min. KH-4. Mission failed. During air catch chute tore, capsule sank..

1962 December 13 - . 04:07 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena D.

Black Sphere - . Payload: NRL PL120 / Poppy 1A (Poppy 20-inch). Mass: 23 kg (50 lb). Nation: USA. Agency: USAF, USN. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. Decay Date: 1967-02-09 . USAF Sat Cat: 502 . COSPAR: 1962-B-Tau-1. Apogee: 2,385 km (1,481 mi). Perigee: 230 km (140 mi). Inclination: 70.30 deg. Period: 111.80 min. First launch of a pair of Poppy naval signals intelligence satellites, which would lead to the NOSS production series..

Injun 3 - . Mass: 52 kg (114 lb). Nation: USA. Agency: USAF, USN. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Injun. Decay Date: 1968-08-25 . USAF Sat Cat: 504 . COSPAR: 1962-B-Tau-2. Apogee: 2,406 km (1,495 mi). Perigee: 240 km (140 mi). Inclination: 70.30 deg. Period: 112.10 min. Radiation decay data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

SURCAL 2A - . Payload: NRL PL121 / Poppy 1B (Poppy 20-inch). Mass: 3.00 kg (6.60 lb). Nation: USA. Agency: USAF, USN. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. Decay Date: 1963-07-01 . USAF Sat Cat: 507 . COSPAR: 1962-B-Tau-3. Apogee: 2,762 km (1,716 mi). Perigee: 222 km (137 mi). Inclination: 70.20 deg. Period: 115.80 min. Poppy naval signals intelligence satellite. Officially: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

SURCAL 1A - . Mass: 37 kg (81 lb). Nation: USA. Agency: USAF, USN. Class: Surveillance. Type: Radar calibration target. Spacecraft: SURCAL. Decay Date: 1966-01-18 . USAF Sat Cat: 508 . COSPAR: 1962-B-Tau-4. Apogee: 2,160 km (1,340 mi). Perigee: 227 km (141 mi). Inclination: 70.30 deg. Period: 109.30 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

Calsphere 1A - . Mass: 23 kg (50 lb). Nation: USA. Agency: USAF, USN. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft: Calsphere. Decay Date: 1967-02-05 . USAF Sat Cat: 513 . COSPAR: 1962-B-Tau-5. Apogee: 2,069 km (1,285 mi). Perigee: 228 km (141 mi). Inclination: 70.30 deg. Period: 108.40 min. Surveillance calibration..

1962 December 13 - . 23:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta B.

Relay 1 - . Payload: NASA A-15. Mass: 78 kg (171 lb). Nation: USA. Agency: NASA. Class: Technology. Type: Communications technology satellite. Spacecraft: Relay. USAF Sat Cat: 503 . COSPAR: 1962-B-Upsilon-1. Apogee: 7,440 km (4,620 mi). Perigee: 1,319 km (819 mi). Inclination: 47.50 deg. Period: 185.10 min. Communications satellite technology tests. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1962 December 14 - . 21:26 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena D.

KH-4 9050 - . Payload: KH-4 s/n 9050 / Agena D 1156. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1963-01-08 . USAF Sat Cat: 505 . COSPAR: 1962-B-Phi-1. Apogee: 386 km (239 mi). Perigee: 200 km (120 mi). Inclination: 70.00 deg. Period: 90.30 min. KH-4; film capsule recovered 4.1 days later. Best mission to date..

1963 January 7 - . 21:09 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena D.

KH-4 9051 - . Payload: KH-4 s/n 9051 / Agena D 1157 / OPS 0048. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1963-01-24 . USAF Sat Cat: 525 . COSPAR: 1963-002A. Apogee: 384 km (238 mi). Perigee: 202 km (125 mi). Inclination: 82.00 deg. Period: 90.30 min. KH-4. Erratic vehicle attitude. Frame ephemeris not created..

1963 January 16 - . 21:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena B.

OPS 0180 - . Payload: Ferret 3 / Agena B 2313. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1969-01-09 . USAF Sat Cat: 527 . COSPAR: 1963-003A. Apogee: 522 km (324 mi). Perigee: 461 km (286 mi). Inclination: 81.90 deg. Period: 94.40 min.

1963 February 14 - . 05:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta B.

Syncom 1 - . Payload: Syncom 1. Mass: 39 kg (85 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: HS 301. Spacecraft: Syncom. Completed Operations Date: 1963-02-14 . USAF Sat Cat: 553 . COSPAR: 1963-004A. Apogee: 36,739 km (22,828 mi). Perigee: 34,392 km (21,370 mi). Inclination: 33.30 deg. Period: 1,425.50 min.
During firing of the apogee kick motor, contact was lost with the satellite. Syncom (Synchronous Communications) was a NASA project supported by DoD ground stations and communications experiments. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Four score. Last known longitude (10 March 1987) 172.58 deg E drifting at 2.429 deg E per day.

1963 February 28 - . 21:48 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D. FAILURE: Failure. Failed Stage: U.

KH-4 9052 - . Payload: KH-4 s/n 9052. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1963-02-28 . KH-4. Mission failed..

SRV 610 - . Mass: 1,200 kg (2,600 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4.

1963 March 18 - . 21:13 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D. FAILURE: Failure. Failed Stage: U.

KH-6 8001 - . Payload: KH-6 s/n 8001. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-6. Decay Date: 1963-03-18 . First launch of KH-6. Mission failed..

P-11 No. 1 - . Payload: P-11 No. 1. Mass: 80 kg (176 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1963-03-18 . Ferret subsatellite aboard first launch of KH-6. Mission failed..

P-11 - . Payload: P-11. Nation: USA. Agency: USAF. Spacecraft: P 11.

1963 April 1 - . 23:01 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor Agena D.

KH-4 9053 - . Payload: KH-4 s/n 9053 / Agena D 1160 / OPS 0720. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1963-04-26 . USAF Sat Cat: 562 . COSPAR: 1963-007A. Apogee: 408 km (253 mi). Perigee: 198 km (123 mi). Inclination: 74.90 deg. Period: 90.50 min. KH-4; film capsule recovered 3.1 days later. Best imagery to date..

1963 April 3 - . 02:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta B.

Explorer 17 - . Payload: AE A (S-6). Mass: 185 kg (407 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Atmosphere satellite. Spacecraft: AE. Decay Date: 1966-11-24 . USAF Sat Cat: 564 . COSPAR: 1963-009A. Apogee: 891 km (553 mi). Perigee: 254 km (157 mi). Inclination: 57.60 deg. Period: 96.10 min. Atmospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1963 April 26 - . 20:13 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena D. FAILURE: Attitude sensors were misaligned. No orbit.. Failed Stage: U.

KH-5 9055A - . Payload: KH-5 s/n 9055A. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-5. Decay Date: 1963-04-26 . Mission failed..

1963 May 7 - . 11:38 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta B.

Telstar 2 - . Mass: 79 kg (174 lb). Nation: USA. Agency: ATT. Class: Communications. Type: Civilian communications satellite. Spacecraft: Telstar. USAF Sat Cat: 573 . COSPAR: 1963-013A. Apogee: 10,802 km (6,712 mi). Perigee: 972 km (603 mi). Inclination: 42.70 deg. Period: 225.30 min. Active repeater. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1963 May 18 - . 22:21 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-6 8002 - . Payload: KH-6 s/n 8002 / Agena D 1165 / OPS 0924. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-6. Decay Date: 1963-05-27 . USAF Sat Cat: 578 . COSPAR: 1963-016A. Apogee: 506 km (314 mi). Perigee: 147 km (91 mi). Inclination: 74.50 deg. Period: 91.00 min. KH-6. Second launch of KH-6. Operation was successful but no film was used. Officially: Spacecraft Engaged in investigation of spaceflight techniques and technology (US Cat A)..

1963 June 12 - . 23:58 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4 9054 - . Payload: KH-4 s/n 9054 / Agena D 1161 / OPS 0954. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1963-07-11 . USAF Sat Cat: 590 . COSPAR: 1963-019A. Apogee: 416 km (258 mi). Perigee: 193 km (119 mi). Inclination: 81.80 deg. Period: 90.70 min. KH-4. Some imagery seriously affected by corona..

1963 June 15 - . 14:29 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena D.

Lofti 2A - . Mass: 26 kg (57 lb). Nation: USA. Agency: USN. Class: Technology. Type: Communications technology satellite. Spacecraft: Lofti. Decay Date: 1963-07-18 . USAF Sat Cat: 601 . COSPAR: 1963-021B. Apogee: 876 km (544 mi). Perigee: 170 km (100 mi). Inclination: 69.90 deg. Period: 95.10 min. VLF experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

Solrad 6A - . Payload: NRL PL110 / Poppy 2A (Poppy 24-inch). Mass: 39 kg (85 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. Decay Date: 1963-08-01 . USAF Sat Cat: 599 . COSPAR: 1963-021C. Apogee: 869 km (539 mi). Perigee: 170 km (100 mi). Inclination: 69.90 deg. Period: 95.10 min.
First launch of a triplet of Poppy naval signals intelligence satellites, which would lead to the NOSS production series. Official and secondary mission: Solar radiation data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

RADOSE 112 - . Payload: NRL PL 112 / Poppy 2B (Poppy 20-inch). Mass: 25 kg (55 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. Decay Date: 1963-07-30 . USAF Sat Cat: 600 . COSPAR: 1963-021D. Apogee: 875 km (543 mi). Perigee: 170 km (100 mi). Inclination: 69.90 deg. Period: 95.10 min. Poppy naval signals intelligence satellite. Official and secondary mission: Radiation dosimeter measurements. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

USN satellite - . Payload: NRL PL130 / Poppy 2C / RADOSE (Poppy 24-inch). Mass: 35 kg (77 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. Decay Date: 1963-07-27 . USAF Sat Cat: 598 . COSPAR: 1963-021E. Apogee: 859 km (533 mi). Perigee: 170 km (100 mi). Inclination: 69.90 deg. Period: 94.90 min. Poppy naval signals intelligence satellite..

SURCAL 1B - . Mass: 3.00 kg (6.60 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Radar calibration target. Spacecraft: SURCAL. Decay Date: 1963-07-05 . USAF Sat Cat: 597 . COSPAR: 1963-021F. Apogee: 802 km (498 mi). Perigee: 172 km (106 mi). Inclination: 69.90 deg. Period: 94.40 min. Surveillance Calibration. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1963 June 19 - . 09:50 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta B.

Tiros 7 - . Payload: Tiros G (A-52). Mass: 135 kg (297 lb). Nation: USA. Agency: NASA Greenbelt. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Tiros. Decay Date: 1994-06-03 . USAF Sat Cat: 604 . COSPAR: 1963-024A. Apogee: 349 km (216 mi). Perigee: 338 km (210 mi). Inclination: 58.20 deg. Period: 91.40 min. Returned over 150000 cloud cover images. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1963 June 27 - . 00:37 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4 9056 - . Payload: KH-4 s/n 9056 / Agena D 1166 / OPS 0999. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1963-07-26 . USAF Sat Cat: 609 . COSPAR: 1963-025A. Apogee: 338 km (210 mi). Perigee: 199 km (123 mi). Inclination: 81.60 deg. Period: 89.90 min. KH-4. Experimental camera carried. Film affected by light leaks..

Hitch Hiker 1 - . Payload: P-11 No. 2. Mass: 80 kg (176 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. USAF Sat Cat: 614 . COSPAR: 1963-025B. Apogee: 2,506 km (1,557 mi). Perigee: 323 km (200 mi). Inclination: 82.10 deg. Period: 114.10 min. Radiation data. First successful flight of P-11 bus, mainly used for radar signals intelligence gathering..

1963 June 29 - . 22:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena B.

OPS 1440 - . Payload: Ferret 4 / Agena B 2314. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1969-10-26 . USAF Sat Cat: 613 . COSPAR: 1963-027A. Apogee: 530 km (320 mi). Perigee: 487 km (302 mi). Inclination: 82.30 deg. Period: 94.80 min.
An Air Force Thor/Agena B launched from Vandenberg established a number of distinctive records. It was the 200th Thor to be launched since Number 101 was launched at Cape Canaveral on 25 January 1957. It was the first, last and only-Thrust Augmented Thor/Agena B to be used by the Air Force. It was the final Agena B (#2314) to be employed with a Thor booster.

1963 July 19 - . 00:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Agena D.

KH-4 9057 - . Payload: KH-4 s/n 9057 / Agena D 1412 / OPS 1266. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1963-08-13 . USAF Sat Cat: 621 . COSPAR: 1963-029A. Apogee: 382 km (237 mi). Perigee: 197 km (122 mi). Inclination: 82.90 deg. Period: 90.40 min. KH-4. Best mission to date..

1963 July 26 - . 14:33 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta B.

Syncom 2 - . Mass: 39 kg (85 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: HS 301. Spacecraft: Syncom. Completed Operations Date: 1969-04-01 . USAF Sat Cat: 634 . COSPAR: 1963-031A. Apogee: 35,891 km (22,301 mi). Perigee: 35,891 km (22,301 mi). Inclination: 32.70 deg. Period: 1,441.50 min.
NASA's Syncom II synchronous communications satellite was placed in orbit by a Thor/Delta launched from Cape Canaveral. Experimental commsat; first geosynchronous satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 55 deg W in 1963; 26 deg W in 1965. Last known longitude (19 July 1995) 68.47 deg E drifting at 0.089 deg W per day.

1963 July 31 - . 00:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH 4A-07 - . Payload: KH-6 s/n 8003 / Agena D 1167 / OPS 1370. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-6. Decay Date: 1963-08-12 . USAF Sat Cat: 626 . COSPAR: 1963-032A. Apogee: 455 km (282 mi). Perigee: 152 km (94 mi). Inclination: 74.90 deg. Period: 90.60 min. KH-6. Third and final KH-6 mission (LANYARD). Mission was successful but image quality was poor. Officially: Spacecraft Engaged in investigation of spaceflight techniques and technology (US Cat A)..

1963 August 25 - . 00:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1001 - . Payload: KH-4A s/n 1001 / Agena D 1162 / OPS 1419. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1963-09-12 . USAF Sat Cat: 636 . COSPAR: 1963-034A. Apogee: 320 km (190 mi). Perigee: 161 km (100 mi). Inclination: 75.00 deg. Period: 89.40 min. KH-4A. First mission of KH-4A. Some film was fogged. Two buckets but 1001-2 was never recovered..

1963 August 29 - . 20:31 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena D.

KH-4 9033 - . Payload: KH-4 s/n 9033 & Lampo / Agena D 1169 / OPS 1561. Mass: 1,000 kg (2,200 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1963-11-07 . USAF Sat Cat: 637 . COSPAR: 1963-035A. Apogee: 324 km (201 mi). Perigee: 292 km (181 mi). Inclination: 81.90 deg. Period: 90.80 min. The first Thor standard launch vehicle, SLV-2, with an Agena D upper stage vehicle, was launched from Vandenberg AFB. KH-5; deployed ELINT subsatellite. Considered to be best mission to date in Argon program..

LAMPO - . Payload: 0.1 Square Meter Target. Nation: USA. Agency: USAF. Class: Surveillance. Type: Naval signals intelligence satellite. Spacecraft: LAMPO. Decay Date: 1963-09-29 . USAF Sat Cat: 638 . COSPAR: 1963-035B. Apogee: 422 km (262 mi). Perigee: 315 km (195 mi). Inclination: 81.90 deg. Period: 92.00 min. The first Thor standard launch vehicle, SLV-2, with an Agena D upper stage vehicle, was launched from Vandenberg AFB. Radar monitoring. Not identified as a subsatellite ferret by McDowell..

1963 September 6 - . LV Family: Atlas, Thor.

NASA and DoD announced a new agreement for NASA's use of Air Force-developed Agena vehicles. - .
Space Systems Division was to be responsible for design, engineering, and acceptance testing of basic Atlas and Thor vehicles and the Agena D upper stages. NASA would buy these from the Air Force, modify them as needed, and launch the Atlas/Agenas from the Atlantic Missile Range while the Air Force conducted all Atlas/Agena and Thor/Agena launches from Vandenberg.

1963 September 18 - . 09:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DSV-2F.

ASSET 1 re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 56 km (34 mi).
A Thor (SLV-2) booster lifted the first Aerothermodynamic/Elastic Structural Systems Environmental Tests (ASSET) program vehicle (ASV-1) on a successful suborbital flight from Cape Canaveral. The ASSET program was designed to test materials and study flight characteristics of glide reentry vehicles. SSD provided the boosters and launch services for the program, while Flight Dynamics Laboratory was responsible for overall program management. Suborbital test of small scale spaceplane model to test materials for the X-20 Dynasoar. Aero-thermodynamic structural test vehicle (ASV) for heat shield tests. Booster flew to peak altitude of 62 km, then pitched down, driving the spacecraft to separation at 59 km and 4,906 m/s. The spacecraft was sited under its parachute in the recovery zone at Ascension Island, but the flotation bag broke and it sank into the Atlantic.

1963 September 23 - . 23:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1002 - . Payload: KH-4A s/n 1002 / Agena D 1163 / OPS 1353. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1963-10-12 . USAF Sat Cat: 668 . COSPAR: 1963-037A. Apogee: 442 km (274 mi). Perigee: 162 km (100 mi). Inclination: 74.80 deg. Period: 90.60 min. KH-4A. Severe light leaks, 1002-2 never recovered, indefinite postponement of KH-4A series..

1963 September 28 - . 20:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Transit 5BN-1 - . Mass: 70 kg (154 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. USAF Sat Cat: 670 . COSPAR: 1963-038B. Apogee: 1,125 km (699 mi). Perigee: 1,066 km (662 mi). Inclination: 90.10 deg. Period: 107.20 min.
The first Thor/Ablestar launch from Vandenberg carried a Navy payload that became the first satellite to be operated completely with nuclear power. A SNAP-9A satellite nuclear power supply, built by the Martin Company and the Atomic Energy Commission, was used to power the satellite. First test of nuclear-powered Transit operational prototype. Carried SNAP-9A nuclear power source. The satellite achieved gravity-gradient stabilization, but upside down, making the signal level too low for operational users with low-gain antennas. However, geodetic and navigational evaluation data were obtained.

Transit 5E-1 - . Payload: APL SN 39. Mass: 61 kg (134 lb). Nation: USA. Agency: USN. Program: Transit. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Transit. USAF Sat Cat: 671 . COSPAR: 1963-038C. Apogee: 1,123 km (697 mi). Perigee: 1,065 km (661 mi). Inclination: 90.10 deg. Period: 107.10 min.
The first Thor/Ablestar launch from Vandenberg carried a Navy payload that became the first satellite to be operated completely with nuclear power. A SNAP-9A satellite nuclear power supply, built by the Martin Company and the Atomic Energy Commission, was used to power the satellite. The missions of Satellite 1963-038C were to measure omnidirectional flux of protons and electrons at various energy levels, radiation effects on transistors, and the effectiveness of thermal coatings. The satellite was launched together with a classified Department of Defense spacecraft on September 28, 1963. Its planned orbit was apogee 1120 kilometres, perigee 1070 kilometres, inclination 88.9 degrees. The satellite weighed 62 kg; its body was in the shape of an 0.46 m x 0.25 m octagonal prism. It was powered by four solar blades and transmited on 136, 162, and 324 mcs. The spacecraft was built for the Bureau of Naval Weapons. In 1967 it was still sending usable data from all systems.

1963 October 29 - . 21:19 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-5 9059A - . Payload: KH-5 s/n 9059A/Agena D 1601 / OPS 2437. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-5. Decay Date: 1964-01-21 . USAF Sat Cat: 681 . COSPAR: 1963-042A. Apogee: 318 km (197 mi). Perigee: 283 km (175 mi). Inclination: 89.90 deg. Period: 90.60 min. KH-5; deployed ELINT subsatellite. Fourth film payload retrieved in ARGON program. Film comparable to that of 9058A. Officially: Spacecraft Engaged in investigation of spaceflight techniques and technology (US Cat A)..

Hitch Hiker 2 - . Payload: P-11 s/n A3. Mass: 80 kg (176 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1965-05-23 . USAF Sat Cat: 682 . COSPAR: 1963-042B. Apogee: 581 km (361 mi). Perigee: 288 km (178 mi). Inclination: 90.00 deg. Period: 93.30 min. Radar monitoring..

1963 October 30 - . LV Family: Thor.

Thrust Augmented Thor Agena announced - .
The Defense Department and NASA announced that the Thrust Augmented Thor (TAT) space booster developed by the Air Force would be added to the national launch vehicles program as a booster for Agena. The TAT increased total thrust to over 330,000 pounds and would improve the Delta's payload into earth orbit from 800 to 1,000 pounds.

1963 November 9 - . 20:27 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena D. FAILURE: Failure. Failed Stage: U.

KH-4 9060 - . Payload: KH-4 s/n 9060. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1963-11-09 . KH-4. Mission failed..

SRV 632 - . Mass: 1,200 kg (2,600 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4.

1963 November 27 - . 02:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta C.

Explorer 18 - . Payload: IMP A. Mass: 62 kg (136 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Magnetosphere satellite. Spacecraft: IMP. Decay Date: 1965-11-30 . USAF Sat Cat: 693 . COSPAR: 1963-046A. Apogee: 197,616 km (122,792 mi). Perigee: 192 km (119 mi). Inclination: 33.30 deg. Period: 5,666.20 min. Radiation data; Interplanetary Monitoring Program. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1963 November 27 - . 21:15 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena D.

KH-4 9061 - . Payload: KH-4 s/n 9061 / Agena D 1172 / OPS 2260. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1963-12-15 . USAF Sat Cat: 695 . COSPAR: 1963-048A. Apogee: 368 km (228 mi). Perigee: 182 km (113 mi). Inclination: 69.60 deg. Period: 90.00 min. KH-4. Mission failed. Return capsule separated from satellite but remained in orbit..

1963 December 5 - . 21:51 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Transit 5BN-2 - . Mass: 75 kg (165 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. USAF Sat Cat: 704 . COSPAR: 1963-049B. Apogee: 1,110 km (680 mi). Perigee: 1,061 km (659 mi). Inclination: 90.10 deg. Period: 107.00 min.
Transit operational prototype powered by a SNAP-9A nuclear power source. First operational navigation satellite. It was used regularly by both surface and submarine units of the Navy until November 1964. From this point in time the US Navy had continuous use of satellite navigation.

Transit 5E-3 - . Mass: 53 kg (116 lb). Nation: USA. Agency: USN. Program: Transit. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Transit. USAF Sat Cat: 705 . COSPAR: 1963-049C. Apogee: 1,108 km (688 mi). Perigee: 1,060 km (650 mi). Inclination: 90.10 deg. Period: 106.90 min. Radiation monitoring..

1963 December 20 - . LV Family: Thor.

RAF Thor IRBM retired. - . The last Royal Air Force Thor IRBM squadron was inactivated and the missiles retired from the Royal Air Force inventory..

1963 December 21 - . 09:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta B.

Tiros 8 - . Payload: Tiros H (A-53). Mass: 119 kg (262 lb). Nation: USA. Agency: NASA Greenbelt. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Tiros. USAF Sat Cat: 716 . COSPAR: 1963-054A. Apogee: 705 km (438 mi). Perigee: 667 km (414 mi). Inclination: 58.50 deg. Period: 98.50 min. Returned more than 100,000 cloud cover images. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1963 December 21 - . 21:45 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4 9062 - . Payload: KH-4 s/n 9062 / Agena D 1168 / OPS 1388. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1964-01-08 . USAF Sat Cat: 718 . COSPAR: 1963-055A. Apogee: 337 km (209 mi). Perigee: 178 km (110 mi). Inclination: 64.80 deg. Period: 89.70 min. KH-4; deployed ELINT subsatellite. Corona static fogged much of film..

Hitch Hiker 3 - . Payload: P-11 s/n A4. Mass: 80 kg (176 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1964-11-07 . USAF Sat Cat: 719 . COSPAR: 1963-055B. Apogee: 394 km (244 mi). Perigee: 316 km (196 mi). Inclination: 64.50 deg. Period: 91.70 min. Radar monitoring..

P-11 motor - . Mass: 1,200 kg (2,600 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4. Decay Date: 1964-01-08 . COSPAR: 1963-055xx.

1964 January 11 - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

Agena D 2354 - . Mass: 700 kg (1,540 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. USAF Sat Cat: 727 . COSPAR: 1964-001A. Apogee: 937 km (582 mi). Perigee: 906 km (562 mi). Inclination: 69.90 deg. Period: 103.50 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

GGSE 1 - . Payload: NRL PL134 / Poppy 3C (Poppy 20-inch). Mass: 39 kg (85 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 728 . COSPAR: 1964-001B. Apogee: 916 km (569 mi). Perigee: 899 km (558 mi). Inclination: 69.90 deg. Period: 103.20 min.
First launch of a triplet of Poppy naval signals intelligence satellites, which would lead to the NOSS production series. Official and secondary mission: Gravity gradient stabilization tests. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

SECOR 1 - . Payload: EGRS 1. Mass: 18 kg (39 lb). Nation: USA. Agency: US Army. Class: Earth. Type: Geodetic satellite. Spacecraft: SECOR. USAF Sat Cat: 729 . COSPAR: 1964-001C. Apogee: 922 km (572 mi). Perigee: 904 km (561 mi). Inclination: 69.90 deg. Period: 103.30 min. Located Pacific islands. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

Solrad 7A - . Payload: NRL PL124 / Poppy 3A (Poppy 24-inch). Mass: 45 kg (99 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 730 . COSPAR: 1964-001D. Apogee: 920 km (570 mi). Perigee: 902 km (560 mi). Inclination: 69.90 deg. Period: 103.20 min. Poppy naval signals intelligence satellite. Official and secondary mission: Solar radiation data. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

Unidentified - . Payload: NRL PL135 / Poppy 3B (Poppy 20-inch). Mass: 40 kg (88 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 731 . COSPAR: 1964-001E. Apogee: 919 km (571 mi). Perigee: 902 km (560 mi). Inclination: 69.90 deg. Period: 103.20 min. Poppy naval signals intelligence satellite..

1964 January 19 - . 10:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena D.

OPS 3367A - . Payload: DAPP / OPS 3367 A. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft: AFP-43. USAF Sat Cat: 734 . COSPAR: 1964-002B. Apogee: 810 km (500 mi). Perigee: 789 km (490 mi). Inclination: 99.00 deg. Period: 100.90 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

OPS 3367B - . Payload: DAPP / OPS 3367 B. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft: AFP-43. USAF Sat Cat: 735 . COSPAR: 1964-002C. Apogee: 815 km (506 mi). Perigee: 791 km (491 mi). Inclination: 99.00 deg. Period: 100.90 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1964 January 21 - . 21:14 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta B.

Relay 2 - . Payload: Relay B. Mass: 78 kg (171 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Communications technology satellite. Spacecraft: Relay. USAF Sat Cat: 737 . COSPAR: 1964-003A. Apogee: 7,540 km (4,680 mi). Perigee: 1,961 km (1,218 mi). Inclination: 46.40 deg. Period: 194.70 min. Experimental commsat. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1964 January 25 - . 13:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena B.

Echo 2 - . Payload: Echo C A-12. Mass: 256 kg (564 lb). Nation: USA. Agency: NASA Langley. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Echo. Spacecraft: Echo 2. Decay Date: 1969-06-07 . USAF Sat Cat: 740 . COSPAR: 1964-004A. Apogee: 1,315 km (817 mi). Perigee: 1,030 km (640 mi). Inclination: 81.50 deg. Period: 108.80 min. Passive commsat; balloon; 1st joint US/USSR space mission. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1964 February 14 - . 07:47 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE1. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

AFP-437 demonstration interceptor mission - . Nation: USA. Agency: DACO, USAF. Apogee: 1,000 km (600 mi).

1964 February 15 - . 21:38 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1004 - . Payload: KH-4A s/n 1004 / Agena D 1174 / OPS 3444. Mass: 1,590 kg (3,500 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1964-03-09 . USAF Sat Cat: 752 . COSPAR: 1964-008A. Apogee: 429 km (266 mi). Perigee: 172 km (106 mi). Inclination: 74.90 deg. Period: 90.50 min. KH-4A. Main cameras operated satisfactorily. Minor degradations due to static and light leaks..

1964 February 28 - . 03:20 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

OPS 3722 - . Payload: Ferret 5 / Agena D 2316. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1969-02-19 . USAF Sat Cat: 759 . COSPAR: 1964-011A. Apogee: 516 km (320 mi). Perigee: 491 km (305 mi). Inclination: 82.10 deg. Period: 94.70 min.

1964 March 1 - . 06:40 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE1. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

AFP-437 demonstration interceptor mission - . Nation: USA. Agency: USAF. Apogee: 674 km (418 mi).

1964 March 19 - . 11:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta B. FAILURE: Insufficient third stage thrust.. Failed Stage: 3.

Explorer (20) - . Payload: Beacon Explorer A. Mass: 54 kg (119 lb). Nation: USA. Agency: NASA. Program: Explorer. Class: Earth. Type: Magnetosphere satellite. Spacecraft: BE. Decay Date: 1964-03-19 . Also known as Explorer S-66..

1964 March 24 - . 12:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DSV-2G. FAILURE: Second stage fired, then shut down, repeating the sequence several times.. Failed Stage: 2.

ASSET 2 re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 55 km (34 mi).
The second flight test of the ASSET reentry vehicle from Cape Canaveral failed when the second stage of the Thor/Delta failed to ignite. The test objectives were not met. Suborbital test of small scale spaceplane model to test materials for the X-20 Dynasoar. Aero-thermodynamic structural test vehicle (ASV) for heat shield tests. Good first stage burn, but the second stage fired, then shut down, repeating the sequence several times. The spacecraft separated, and began to maneuver in a 60 degree bank to recover course, when the self-destruct package blew it apart. The debris impacted the Atlantic 800 km downrange near San Salvador Island.

1964 March 24 - . 22:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D. FAILURE: Failure. Failed Stage: U.

KH-4A 1003 - . Payload: KH-4A s/n 1003. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1964-03-24 . KH-4A. Mission failed..

SRV 630 - . Payload: SRV 1003-2. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A.

ORBIS 1 - . Payload: ORBIS 1. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A.

SRV 631 - . Payload: SRV 1003-1. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A.

1964 April 21 - . 06:15 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

AFP-437 combat training interceptor mission - . Nation: USA. Agency: USAF. Apogee: 778 km (483 mi).

1964 April 21 - . 18:50 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Ablestar. FAILURE: Failure. Failed Stage: U.

Transit 5BN-3 - . Mass: 75 kg (165 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. Decay Date: 1964-04-21 . COSPAR: F640421A. Carried SNAP-9A nuclear power source. After this launch failure it was decided that operational Transits would be solar-powered only..

Transit 5E-4 - . Mass: 55 kg (121 lb). Nation: USA. Agency: USN. Program: Transit. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Transit. COSPAR: F640421B. Radiation monitoring..

1964 April 27 - . 23:23 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1005 - . Payload: KH-4A s/n 1005 / Agena D 1604 / OPS 2921. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1964-05-26 . USAF Sat Cat: 796 . COSPAR: 1964-022A. Apogee: 445 km (276 mi). Perigee: 175 km (108 mi). Inclination: 79.90 deg. Period: 90.80 min. KH-4A. Mission failed. Recovery vehicle impacted in Venezuela..

1964 May 28 - . 07:32 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Thor. Launch Vehicle: Thor DSV-2J. FAILURE: Failure. Failed Stage: 3.

AFP-437 combat training interceptor mission - . Nation: USA. Agency: USAF. Apogee: 932 km (579 mi).

1964 June - . Launch Vehicle: Thor.

Program 437 ASAT declared operational. - . Nation: USA. Spacecraft: Program 437. The system had a two week reaction time - the missiles and nuclear warheads were stored in kits at Vandenberg and had to be deployed to the Johnson Atoll launch site..

1964 June 4 - . 22:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1006 - . Payload: KH-4A s/n 1006 / Agena D 1176 / OPS 3483. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1964-06-18 . USAF Sat Cat: 802 . COSPAR: 1964-027A. Apogee: 429 km (266 mi). Perigee: 149 km (92 mi). Inclination: 80.00 deg. Period: 90.30 min. KH-4A. Highest quality imagery attained to date from the KH-4 system..

1964 June 13 - . 15:47 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-5 9065A - . Payload: KH-5 s/n 9065A / OPS 3236. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-5. Decay Date: 1965-06-02 . USAF Sat Cat: 811 . COSPAR: 1964-030A. Apogee: 362 km (224 mi). Perigee: 352 km (218 mi). Inclination: 114.90 deg. Period: 91.70 min. KH-5; carried Star Flash experiment. Officially: Spacecraft Engaged in investigation of spaceflight techniques and technology (US Cat A)..

Starflash 1A - . Nation: USA. Agency: USAF. Spacecraft: Starflash. COSPAR: 1964-030xx.

1964 June 18 - . 04:56 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena D.

OPS 4467A - . Payload: DAPP / OPS 4467 A. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft: AFP-43. USAF Sat Cat: 812 . COSPAR: 1964-031A. Apogee: 820 km (500 mi). Perigee: 812 km (504 mi). Inclination: 99.80 deg. Period: 101.20 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

OPS 4467B - . Payload: DAPP / OPS 4467 B. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Military technology satellite. Spacecraft: AFP-43. USAF Sat Cat: 813 . COSPAR: 1964-031B. Apogee: 822 km (510 mi). Perigee: 814 km (505 mi). Inclination: 99.80 deg. Period: 101.30 min.

1964 June 19 - . 23:18 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1007 - . Payload: KH-4A s/n 1007 / Agena D 1609 / OPS 3754. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1964-07-16 . USAF Sat Cat: 814 . COSPAR: 1964-032A. Apogee: 451 km (280 mi). Perigee: 180 km (110 mi). Inclination: 85.00 deg. Period: 90.90 min. KH-4A. Out-of-focus area on some film..

1964 July 2 - . 23:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

OPS 3395 - . Payload: Ferret 6 / Agena D 2315. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1969-08-07 . USAF Sat Cat: 824 . COSPAR: 1964-035A. Apogee: 520 km (320 mi). Perigee: 502 km (311 mi). Inclination: 82.10 deg. Period: 94.90 min.

1964 July 10 - . 23:15 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1008 - . Payload: KH-4A s/n 1008 / Agena D 1117 / OPS 3491. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1964-08-06 . USAF Sat Cat: 828 . COSPAR: 1964-037A. Apogee: 346 km (214 mi). Perigee: 173 km (107 mi). Inclination: 84.90 deg. Period: 89.70 min. KH-4A. Cameras operated satisfactorily, some light leaks..

1964 July 22 - . 15:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DSV-2G.

ASSET 3 re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 71 km (44 mi).
Aerothermodynamic/elastic Structural Systems Evaluation Test (ASSET) vehicle (ASV-3) was launched down the Eastern Test Range by a Thor booster. The ASV-3 was a boost-glide reentry vehicle that was designed to obtain temperature and pressure distribution data and to test materials and structural concepts during reentry. The vehicle was recovered 1,650 miles southeast of Cape Canaveral after reentering the atmosphere at 13,000 miles per hour and reaching reentry temperatures of 4,000Â° F. A part of the Spacecraft Technology and Advanced Reentry Tests (START) program managed by Space Systems Division, ASSET provided valuable data on the conditions encountered by a spacecraft during reentry. Suborbital test of small scale spaceplane model to test materials for the X-20 Dynasoar. Aero-thermodynamic structural test vehicle (ASV) for heat shield tests. Launched after four hours of holds. Tested Dynasoar hardware - tungsten nose cap, molbdenum panels with vapor-deposited disilicide, and liquid-cooled double-walled cockpit bathtub panel. Reached 5,500 m/s and recovered near Ascension Island 12 hours after launch.

1964 August 5 - . 23:15 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1009 - . Payload: KH-4A s/n 1009 / Agena D 1605 / OPS 3042. Mass: 1,540 kg (3,390 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1964-09-01 . USAF Sat Cat: 846 . COSPAR: 1964-043A. Apogee: 436 km (270 mi). Perigee: 182 km (113 mi). Inclination: 80.00 deg. Period: 90.70 min. KH-4A. Cameras operated successfully..

1964 August 19 - . 12:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta D.

Syncom 3 - . Payload: Syncom C. Mass: 39 kg (85 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: HS 301. Spacecraft: Syncom. Completed Operations Date: 1974-12-29 . USAF Sat Cat: 858 . COSPAR: 1964-047A. Apogee: 35,792 km (22,240 mi). Perigee: 35,784 km (22,235 mi). Inclination: 0.10 deg. Period: 1,436.20 min.
NASA's Syncom III synchronous communications satellite was launched into orbit by a Thrust Augmented Thor/Delta (TAD) launch vehicle in its first use as a space booster. Also carried Star Flash experiment. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 64 deg W in 1964; 180 deg E in 1964; 25 deg W in 1965; 165 deg E in 1966-1969. Last known longitude (6 December 1974) 6.08 deg W drifting at 0.188 deg W per day.

1964 August 21 - . 15:45 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-5 9066A - . Payload: KH-5 s/n 9066A / Agena D 1603 / OPS 2739. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-5. Decay Date: 1965-03-31 . USAF Sat Cat: 861 . COSPAR: 1964-048A. Apogee: 363 km (225 mi). Perigee: 351 km (218 mi). Inclination: 114.90 deg. Period: 91.70 min. KH-5. 15% of stellar film degraded by flare. Image smearing on leading edge of main camera film. Final ARGON mission. Officially: Spacecraft Engaged in investigation of spaceflight techniques and technology (US Cat A)..

Starflash 1B - . Nation: USA. Agency: USAF. Spacecraft: Starflash. Decay Date: 1965-03-31 . USAF Sat Cat: 861 . COSPAR: 1964-048xx. Apogee: 200 km (120 mi). Perigee: 196 km (121 mi). Inclination: 115.00 deg. Period: 88.50 min.

1964 August 28 - . 07:56 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena B. FAILURE: Agena-B cut off too early. Partial Failure.. Failed Stage: U.

Nimbus 1 - . Payload: Nimbus A. Mass: 376 kg (828 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Weather satellite. Spacecraft: Nimbus. Decay Date: 1974-05-16 . USAF Sat Cat: 872 . COSPAR: 1964-052A. Apogee: 937 km (582 mi). Perigee: 429 km (266 mi). Inclination: 98.70 deg. Period: 98.40 min.
An Air Force Thor/Agena B was launched from Vandenberg and placed NASA's first Nimbus meteorological satellite into orbit. Returned 27,000 cloud cover images. The spacecraft carried an advanced vidicon camera system for recording and storing remote cloudcover pictures, an automatic picture transmission camera for providing real-time cloud cover pictures, and a high-resolution infrared radiometer to complement the daytime TV coverage and to measure nighttime radiative temperatures of cloud tops and surface terrain. A short second-stage burn resulted in an unplanned eccentric orbit. Otherwise, the spacecraft and its experiments operated successfully until September 22, 1964. The solar paddles became locked in position, resulting in inadequate electrical power to continue operations.

1964 September 14 - . 22:53 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1010 - . Payload: KH-4A s/n 1010 / Agena D 1178 / OPS 3497. Mass: 1,330 kg (2,930 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1964-10-06 . USAF Sat Cat: 882 . COSPAR: 1964-056A. Apogee: 455 km (282 mi). Perigee: 174 km (108 mi). Inclination: 84.90 deg. Period: 90.90 min. KH-4A. Small out of focus areas on both cameras at random times throughout the mission..

1964 October 4 - . 03:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta C.

Explorer 21 - . Payload: IMP B. Mass: 62 kg (136 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Magnetosphere satellite. Spacecraft: IMP. Decay Date: 1965-12-31 . USAF Sat Cat: 889 . COSPAR: 1964-060A. Apogee: 95,590 km (59,390 mi). Perigee: 191 km (118 mi). Inclination: 33.50 deg. Period: 2,097.00 min. Lower than planned orbit. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1964 October 5 - . 21:50 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1011 - . Payload: KH-4A s/n 1011 / Agena D 1170 / OPS 3333. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1964-10-26 . USAF Sat Cat: 890 . COSPAR: 1964-061A. Apogee: 440 km (270 mi). Perigee: 182 km (113 mi). Inclination: 80.00 deg. Period: 90.80 min.
The 100th Thor/Agena, a Thrust Augmented Thor/Agena D (421/1170) was launched from Vandenberg AFB by the 6595th ATWg. KH-4A. Primary mode of recovery failed on second portion of the mission (1011-2). Small out of focus areas present at random on both cameras.

1964 October 6 - . 17:04 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Transit O-1 - . Payload: NNS 30010 / Ablestar 016 / OPS 5798. Mass: 60 kg (132 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. USAF Sat Cat: 897 . COSPAR: 1964-063B. Apogee: 1,077 km (669 mi). Perigee: 1,046 km (649 mi). Inclination: 90.20 deg. Period: 106.40 min. Naval Avionics Facility-assembled production spacecraft. Failed after a few days operation..

Calsphere 1 - . Payload: Dragsphere 1. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Radar calibration target. Spacecraft: Calsphere. USAF Sat Cat: 900 . COSPAR: 1964-063C. Apogee: 1,034 km (642 mi). Perigee: 997 km (619 mi). Inclination: 90.10 deg. Period: 105.50 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

Calsphere 2 - . Payload: Dragsphere 2. Mass: 10 kg (22 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Radar calibration target. Spacecraft: Calsphere. USAF Sat Cat: 902 . COSPAR: 1964-063E. Apogee: 1,078 km (669 mi). Perigee: 1,049 km (651 mi). Inclination: 90.20 deg. Period: 106.50 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1964 October 17 - . 22:02 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1012 - . Payload: KH-4A s/n 1012 / Agena D 1179 / OPS 3559. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1964-11-04 . USAF Sat Cat: 911 . COSPAR: 1964-067A. Apogee: 416 km (258 mi). Perigee: 189 km (117 mi). Inclination: 75.00 deg. Period: 90.60 min. KH-4A. Vehicle attitude became erratic on the second portion of the mission necessitating an early recovery..

1964 October 29 - . 03:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DSV-2F.

ASSET 4 re-entry vehicle test flight - . Nation: USA. Agency: USAF. Spacecraft: Asset. Apogee: 50 km (31 mi).
Suborbital test of small scale spaceplane model to test structural concepts for the X-20 Dynasoar. Aero-environmental test vehicle (AEV) to test aerodynamic properties of flexing outer skin with corrugated columbium panel. Reached 4,000 m/s at 50.6 km altitude before being released from single-stage Thor SLV-2 launch vehicle. Telemetry received for 900 seconds until spaceplane had reached Mach 2 1200 km downrange. It then became unstable and crashed into the Atlantic. Recovery was not planned. AEV-1 was part of Space Systems Division's Aerothermodynamic/ elastic Structural Systems Evaluation Test (ASSET) program, and the first of two tests to obtain data on structural behavior during reentry, with emphasis on thermoelastic effects.

1964 November 2 - . 21:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1013 - . Payload: KH-4A s/n 1013 - Agena D 1173 / OPS 5434. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1964-11-28 . USAF Sat Cat: 921 . COSPAR: 1964-071A. Apogee: 210 km (130 mi). Perigee: 181 km (112 mi). Inclination: 51.20 deg. Period: 88.40 min. KH-4A. Program anomaly occurred immediately after launch when both cameras operated for 417 frames. Main cameras ceased operation on rev 52D of first portion of mission negating second portion. About 65% of aft camera film is out of focus..

1964 November 4 - . 02:12 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

OPS 3062 - . Payload: Ferret 7 / Agena D 2317. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1969-11-05 . USAF Sat Cat: 922 . COSPAR: 1964-072A. Apogee: 526 km (326 mi). Perigee: 512 km (318 mi). Inclination: 82.00 deg. Period: 95.00 min.

1964 November 16 - . 06:57 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE1. Launch Pad: LE1?. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

AFP-437 combat training interceptor mission - . Nation: USA. Agency: USAF. Apogee: 1,148 km (713 mi).

1964 November 18 - . 20:35 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1014 (ORBIS) - . Payload: KH-4A s/n 1014 & Orbis / Agena D 1180 / OPS 3360. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1964-12-06 . USAF Sat Cat: 930 . COSPAR: 1964-075A. Apogee: 329 km (204 mi). Perigee: 177 km (109 mi). Inclination: 70.00 deg. Period: 89.60 min. KH-4A. Cameras operated successfully..

ORBIS - . Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1964-12-06 . USAF Sat Cat: 930 . COSPAR: 1964-075xx. Apogee: 276 km (171 mi). Perigee: 167 km (103 mi). Inclination: 70.00 deg. Period: 88.90 min.

1964 December 9 - . 02:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DSV-2F.

ASSET 5 re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 50 km (31 mi).
The 6555th Aerospace Test Wing successfully launched the fifth ASSET reentry test vehicle, a suborbital test of small scale spaceplane model to test structural concepts for the X-20 Dynasoar. Aero-environmental test vehicle (AEV) to test aerodynamic properties of flexing outer skin with corrugated columbium panel. Reached 4,000 m/s at 53.2 km altitude before being released from launch vehicle. Telemetry received for 900 seconds until spaceplane had reached Mach 2 1200 km downrange. It then became unstable and crashed into the Atlantic. Recovery was not planned.

1964 December 13 - . 00:08 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Transit 5E-5 - . Payload: APL SN 43 / OPS 6582. Mass: 78 kg (171 lb). Nation: USA. Agency: USN. Program: Transit. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Transit. USAF Sat Cat: 959 . COSPAR: 1964-083C. Apogee: 1,064 km (661 mi). Perigee: 1,007 km (625 mi). Inclination: 89.80 deg. Period: 105.90 min. Celestial UV, magnetic field data..

Transit O-2 - . Payload: NNS 30020 / OPS 6582. Mass: 60 kg (132 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. USAF Sat Cat: 965 . COSPAR: 1964-083D. Apogee: 1,079 km (670 mi). Perigee: 1,020 km (630 mi). Inclination: 89.80 deg. Period: 106.20 min. Naval Avionics Facility-assembled production spacecraft. Failed after a few days operation..

1964 December 19 - . 21:10 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1015 - . Payload: KH-4A s/n 1015 / Agena D 1607 / OPS 3358. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-01-14 . USAF Sat Cat: 961 . COSPAR: 1964-085A. Apogee: 405 km (251 mi). Perigee: 193 km (119 mi). Inclination: 74.90 deg. Period: 90.50 min. KH-4A. Discrepancies in planned and actual coverage due to telemetry problems during the first 6 revolutions. Small out-of-focus areas on film from aft camera..

1964 December 21 - . 09:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta C.

Explorer 26 - . Payload: EPE D - 661A Flight 21-3. Mass: 46 kg (101 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Astronomy. Type: Solar satellite. Spacecraft: EPE. Decay Date: 1978-03-31 . USAF Sat Cat: 963 . COSPAR: 1964-086A. Apogee: 10,043 km (6,240 mi). Perigee: 284 km (176 mi). Inclination: 19.80 deg. Period: 205.70 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

1964 December 21 - . 19:08 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

OPS 3762/Agena D 2355 - . Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: Quill. Duration: 4.00 days. Decay Date: 1965-01-11 . USAF Sat Cat: 964 . COSPAR: 1964-087A. Apogee: 264 km (164 mi). Perigee: 238 km (147 mi). Inclination: 70.10 deg. Period: 89.50 min.
First test of a side-looking radar from outer space. The mission lasted only four days, as planned, before the batteries ran out of power during orbits 72-73. The radar operated 14 times in orbit, between 22 and 26 December, imaging swaths of the northeastern and western United States. Data collected from the 14 radar passes were transmitted over a wideband (UHF) data link as they were obtained ("real time") to the Vandenberg or New Boston ground station in view. In addition, during the first seven radar passes data were recorded on film on board the satellite, and on 23 December, during the 33rd orbit, the reentry capsule was jettisoned and recovered. The vehicle and payload performance were within acceptable limits on all parameters. The radar maps covered about 80,000 square miles and the resolution was better than 15 feet in azimuth and 80 feet in ground range. The mission, not declassified until 2012, proved the feasibility of space-based surveillance, leading to the operational Lacrosse satellites of the 1980's.

1965 January 15 - . 21:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1016 - . Payload: KH-4A s/n 1016 / Agena D 1608 / OPS 3928. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-02-09 . USAF Sat Cat: 972 . COSPAR: 1965-002A. Apogee: 420 km (260 mi). Perigee: 180 km (110 mi). Inclination: 75.00 deg. Period: 90.50 min. KH-4A. Smearing of highly reflective images due to reflections within camera..

1965 January 19 - . 05:03 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor MG-18.

DMSP-Block-4A F1 - . Payload: DAPP 10 / OPS 7040. Mass: 150 kg (330 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 4A. Decay Date: 1979-07-13 . USAF Sat Cat: 973 . COSPAR: 1965-003A. Apogee: 833 km (517 mi). Perigee: 462 km (287 mi). Inclination: 98.80 deg. Period: 97.60 min.
The first Air Force Thor/Altair (Burner I) space booster was launched from Vandenberg AFB. The Altair upper stage was the fourth stage of the Scout rocket. Defense Meteorological Satellite Program. Launch date was January 18, 1965. The launch was successful and correct orbit was achieved. However, the heat shield on the second stage did not deploy correctly and the mission objectives were not fully realized. This first Burner I bird is distinguishable in photos by its black second stage.

1965 January 22 - . 07:52 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta C.

Tiros 9 - . Payload: Tiros I (A-54). Mass: 138 kg (304 lb). Nation: USA. Agency: NASA Greenbelt. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Tiros. USAF Sat Cat: 978 . COSPAR: 1965-004A. Apogee: 2,563 km (1,592 mi). Perigee: 705 km (438 mi). Inclination: 96.40 deg. Period: 119.00 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1965 February 3 - . 16:36 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta C.

OSO 2 - . Payload: OSO B2 (S-17). Mass: 247 kg (544 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: Solar satellite. Spacecraft: OSO. Decay Date: 1989-08-09 . USAF Sat Cat: 987 . COSPAR: 1965-007A. Apogee: 306 km (190 mi). Perigee: 294 km (182 mi). Inclination: 32.80 deg. Period: 90.50 min. Orbiting Solar Observatory; returned solar X-ray, UV, gamma ray data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1965 February 23 - . 14:36 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor DSV-2G.

ASSET 6 re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 70 km (43 mi).
The Aerothermodynamic/elastic Structural Systems Environmental Test (ASSET) program concluded when a Thor booster launched the last of the experimental vehicles from the Eastern Test Range. The payload reentered down range but was not recovered. Suborbital test of small scale spaceplane model to test materials for the X-20 Dynasoar. Reached 6,000 m/s and 4,350 km range. Tested twelve different kinds of refractory metals and covered with 2000 dots of heat-sensitive paint to characterize thermal profile on reentry. Telemetry indicated that the spacecraft survived reentry, but it evidently sank upon impacting the ocean and could not be recovered as planned.

1965 February 25 - . 21:44 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1017 - . Payload: KH-4A s/n 1017 / Agena D 1611 / OPS 4782. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-03-18 . USAF Sat Cat: 1096 . COSPAR: 1965-013A. Apogee: 377 km (234 mi). Perigee: 177 km (109 mi). Inclination: 75.10 deg. Period: 90.10 min. KH-4A. Capping shutter malfunction occurred during last 5 passes of mission..

1965 March 9 - . 18:29 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena D.

Solrad 6B - . Payload: NRL PL142 / OPS 4988 / Poppy 4B (Poppy 24-inch). Mass: 40 kg (88 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 1271 . COSPAR: 1965-016A. Apogee: 924 km (574 mi). Perigee: 896 km (556 mi). Inclination: 70.10 deg. Period: 103.20 min.
A Thor/Agena D booster was employed to launch eight military satellites into orbit from Vandenberg AFB. This was the largest number of individual payloads yet orbited by the United States with one launch vehicle. First launch of a quadruplet of Poppy naval signals intelligence satellites, which would lead to the NOSS production series. Official and secondary mission: Solar radiation data.

Solrad 7B - . Payload: NRL PL141 / Poppy 4A (Poppy 24-inch). Mass: 47 kg (103 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 1291 . COSPAR: 1965-016D. Apogee: 928 km (576 mi). Perigee: 901 km (559 mi). Inclination: 70.10 deg. Period: 103.30 min. Solar radiation monitoring. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

SECOR 3 - . Payload: EGRS 3. Mass: 18 kg (39 lb). Nation: USA. Agency: USA ACE. Class: Earth. Type: Geodetic satellite. Spacecraft: SECOR. USAF Sat Cat: 1208 . COSPAR: 1965-016E. Apogee: 925 km (574 mi). Perigee: 898 km (557 mi). Inclination: 70.10 deg. Period: 103.20 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

GGSE 3 - . Payload: NRL PL144 / Poppy 4D (Poppy 24-inch). Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 1292 . COSPAR: 1965-016C. Apogee: 915 km (568 mi). Perigee: 886 km (550 mi). Inclination: 70.10 deg. Period: 103.00 min. Poppy naval signals intelligence satellite. Official and secondary mission: Gravity gradient stabilization tests. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

SURCAL 2B - . Mass: 5.00 kg (11.00 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Radar calibration target. Spacecraft: SURCAL. Decay Date: 1981-03-27 . USAF Sat Cat: 1310 . COSPAR: 1965-016G. Apogee: 947 km (588 mi). Perigee: 902 km (560 mi). Inclination: 70.10 deg. Period: 103.50 min. Surveillance Calibration. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

GGSE 2 - . Payload: NRL PL143 / Poppy 4C (Poppy 24-inch). Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 1244 . COSPAR: 1965-016B. Apogee: 925 km (574 mi). Perigee: 898 km (557 mi). Inclination: 70.10 deg. Period: 103.20 min. Poppy naval signals intelligence satellite. Official and secondary mission: Gravity gradient stabilization tests. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

DODECAPOLE 1/Porcupine 1 - . Payload: Dodecapole 1. Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Radar calibration target. Spacecraft: DODECAPOLE. USAF Sat Cat: 1272 . COSPAR: 1965-016H. Apogee: 930 km (570 mi). Perigee: 901 km (559 mi). Inclination: 70.10 deg. Period: 103.30 min.
A Thor/Agena D booster was employed to launch eight military satellites into orbit from Vandenberg AFB. This was the largest number of individual payloads yet orbited by the United States with one launch vehicle. Surveillance calibration. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

Oscar 3 - . Mass: 14 kg (30 lb). Nation: USA. Agency: OSCAR. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Oscar. USAF Sat Cat: 1293 . COSPAR: 1965-016F. Apogee: 900 km (550 mi). Perigee: 876 km (544 mi). Inclination: 70.10 deg. Period: 102.80 min.
OSCAR III was launched piggyback with seven United States Air Force satellites. Weight 16.3 kg. It was the first amateur satellite to operate from solar power and relay signals from Earth. OSCAR III was the first true amateur satellite relaying voice contacts in the VHF 2 meter band through a 1 W 50 kHz wide linear transponder (146 MHz uplink and 144 MHz downlink). OSCAR III's transponder lasted 18 days. More than 1000 amateurs in 22 countries communicated through the linear transponder. The two beacon transmitters continued operating for several months.
Note: Designed, built, and tested, a predecssor, OSCAR* was never launched. Similar in design to OSCAR I and II, OSCAR* contained a 250 mW beacon with phase-coherent keying. OSCAR* was never launched as the workers decided to focus their efforts on the first relay satellite -- OSCAR III.

1965 March 11 - . 13:39 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Transit-O-3 - . Mass: 60 kg (132 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. Decay Date: 1965-06-14 . USAF Sat Cat: 1303 . COSPAR: 1965-017A. Apogee: 418 km (259 mi). Perigee: 191 km (118 mi). Inclination: 90.00 deg. Period: 90.70 min. Naval Avionics Facility-assembled production spacecraft. Failed after a few weeks operation..

SECOR 2 - . Payload: EGRS 2. Mass: 18 kg (39 lb). Nation: USA. Agency: USA ACE. Class: Earth. Type: Geodetic satellite. Spacecraft: SECOR. Decay Date: 1968-02-26 . USAF Sat Cat: 1250 . COSPAR: 1965-017B. Apogee: 1,014 km (630 mi). Perigee: 296 km (183 mi). Inclination: 90.00 deg. Period: 97.90 min. Failed. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1965 March 18 - . 04:43 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor MG-18.

DMSP-Block-4A F2 - . Payload: DAPP 11 / OPS 7353. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 4A. Decay Date: 1989-12-31 . USAF Sat Cat: 1273 . COSPAR: 1965-021A. Apogee: 146 km (90 mi). Perigee: 139 km (86 mi). Inclination: 99.00 deg. Period: 87.30 min. Defense Meteorological Satellite Program. A fully successful launch with all objectives met. The night launch time of 2100 hrs Vandenberg time with a 5 minute launch window was the same for both the first and second Burner I launches..

1965 March 25 - . 21:11 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1018 - . Payload: KH-4A s/n 1018 / Agena D 1612 / OPS 4803. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-04-04 . USAF Sat Cat: 1307 . COSPAR: 1965-026A. Apogee: 381 km (236 mi). Perigee: 237 km (147 mi). Inclination: 96.00 deg. Period: 90.70 min. KH-4A. Cameras operated successfully. First KH-4A reconnaissance system to be launched into a retrograde orbit..

1965 April 5 - . 07:20 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

AFP-437 combat training interceptor mission - . Nation: USA. Agency: USAF. Apogee: 826 km (513 mi).

1965 April 6 - . 23:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta D.

Intelsat 1 F-1 - . Payload: Early Bird. Mass: 39 kg (85 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 303. Spacecraft: Intelsat 1. Completed Operations Date: 1971-01-01 . USAF Sat Cat: 1317 . COSPAR: 1965-028A. Apogee: 35,819 km (22,256 mi). Perigee: 35,746 km (22,211 mi). Inclination: 11.70 deg. Period: 1,435.90 min.
Over Atlantic. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 28 deg W in 1965; 38 deg W in 1965-1966. As of 27 July 2001 located at 92.54 deg W drifting at 0.324 deg W per day. As of 2007 Jan 13 located at 47.74W drifting at 0.017E degrees per day.

1965 April 29 - . 21:44 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1019 - . Payload: KH-4A s/n 1019 / Agena D 1614 / OPS 5023. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-05-26 . USAF Sat Cat: 1330 . COSPAR: 1965-033A. Apogee: 461 km (286 mi). Perigee: 181 km (112 mi). Inclination: 85.00 deg. Period: 91.00 min. KH-4A. Cameras operated successfully. Malfunction in recovery mode on 1019-2 negated recovery..

SRV 627 - . Payload: SRV 1019-2 / OPS 5023. Mass: 60 kg (132 lb). Nation: USA. Agency: CIA, NRO. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-06-08 . USAF Sat Cat: 1367 . COSPAR: 1965-033B. Apogee: 509 km (316 mi). Perigee: 134 km (83 mi). Inclination: 84.90 deg. Period: 91.00 min. Cameras operated successfully. Malfunction in recovery mode on 1019-2 negated recovery..

1965 May 18 - . 18:02 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1021 - . Payload: KH-4A s/n 1021 / Agena D 1615 / OPS 8431. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-06-15 . USAF Sat Cat: 1374 . COSPAR: 1965-037A. Apogee: 399 km (247 mi). Perigee: 321 km (199 mi). Inclination: 75.00 deg. Period: 91.70 min. KH-4A. Aft camera ceased operation on pass 102..

1965 May 20 - . 16:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 1.

DMSP-Block-4A F3 - . Payload: DAPP 12 / OPS 8386. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 4A. Decay Date: 2012-03-09 . USAF Sat Cat: 1377 . COSPAR: 1965-038A. Apogee: 731 km (454 mi). Perigee: 503 km (312 mi). Inclination: 98.10 deg. Period: 97.10 min. Defense Meteorological Satellite Program..

1965 May 29 - . 12:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta C.

Explorer 28 - . Payload: IMP C. Mass: 58 kg (127 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Magnetosphere satellite. Spacecraft: IMP. Decay Date: 1968-07-04 . USAF Sat Cat: 1388 . COSPAR: 1965-042A. Apogee: 261,206 km (162,305 mi). Perigee: 229 km (142 mi). Inclination: 30.50 deg. Period: 8,419.70 min. Magnetic field, radiation data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1965 June 9 - . 21:58 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1020 - . Payload: KH-4A s/n 1020 / Agena D 1613 / OPS 8425. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-06-15 . USAF Sat Cat: 1396 . COSPAR: 1965-045A. Apogee: 355 km (220 mi). Perigee: 176 km (109 mi). Inclination: 75.10 deg. Period: 89.90 min. KH-4A. All cameras operated satisfactorily. Erratic attitude caused an early recovery after the second day of 1020-2..

1965 June 24 - . 22:35 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Transit O-4 - . Payload: NNS 30040 / OPS 8480. Mass: 61 kg (134 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. USAF Sat Cat: 1420 . COSPAR: 1965-048A. Apogee: 1,125 km (699 mi). Perigee: 1,016 km (631 mi). Inclination: 90.10 deg. Period: 106.60 min. Spacecraft built by Naval Avionics Facility, but refurbished by APL. Operated for 7 to 11 months, but then failed due to poor workmanship of NAFI components..

1965 July 2 - . 04:07 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta C.

Tiros 10 - . Payload: Tiros OT1. Mass: 127 kg (279 lb). Nation: USA. Agency: ESSA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Tiros. USAF Sat Cat: 1430 . COSPAR: 1965-051A. Apogee: 807 km (501 mi). Perigee: 722 km (448 mi). Inclination: 98.80 deg. Period: 100.10 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1965 July 17 - . 05:55 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

OPS 8411 - . Payload: Ferret 8 / Agena D 2702. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1968-12-18 . USAF Sat Cat: 1447 . COSPAR: 1965-055A. Apogee: 512 km (318 mi). Perigee: 471 km (292 mi). Inclination: 70.20 deg. Period: 94.50 min.

1965 July 19 - . 22:01 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1022 - . Payload: KH-4A s/n 1022 / Agena D 1617 / OPS 5543. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-08-18 . USAF Sat Cat: 1457 . COSPAR: 1965-057A. Apogee: 461 km (286 mi). Perigee: 189 km (117 mi). Inclination: 85.10 deg. Period: 91.00 min. KH-4A. All cameras operated satisfactorily..

1965 August 13 - . 22:11 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Ablestar.

Dodecapole 2 - . Payload: PORCUPINE 2. Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Radar calibration target. Spacecraft: DODECAPOLE. USAF Sat Cat: 1510 . COSPAR: 1965-065C. Apogee: 1,051 km (653 mi). Perigee: 979 km (608 mi). Inclination: 90.00 deg. Period: 105.40 min. Surveillance Calibration; dodecahedron; extended 12 25 ft. antennas. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

Calsphere 4A - . Payload: NRL PL 158?. Mass: 2.00 kg (4.40 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Radar calibration target. Spacecraft: Calsphere. USAF Sat Cat: 1520 . COSPAR: 1965-065H. Apogee: 1,179 km (732 mi). Perigee: 1,077 km (669 mi). Inclination: 90.10 deg. Period: 107.90 min. Surveillance Calibration; white 14 inch dia. sphere. .

SURCAL 5 - . Payload: NRL PL150C?. Nation: USA. Agency: USN. Class: Surveillance. Type: Radar calibration target. Spacecraft: SURCAL. USAF Sat Cat: 1521 . COSPAR: 1965-065K. Apogee: 1,196 km (743 mi). Perigee: 1,083 km (672 mi). Inclination: 90.00 deg. Period: 108.11 min.

Tempsat 1 - . Mass: 9.00 kg (19.80 lb). Nation: USA. Agency: USN. Class: Surveillance. Type: Radar calibration target. Spacecraft: Tempsat. USAF Sat Cat: 1512 . COSPAR: 1965-065E. Apogee: 1,188 km (738 mi). Perigee: 1,082 km (672 mi). Inclination: 89.90 deg. Period: 108.00 min. Surveillance Calibration; black 14 inch dia. sphere. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

Transit O-5 - . Payload: NNS 30050 / OPS 8464. Mass: 61 kg (134 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. USAF Sat Cat: 1514 . COSPAR: 1965-065F. Apogee: 1,183 km (735 mi). Perigee: 1,078 km (669 mi). Inclination: 89.90 deg. Period: 107.90 min. Naval Avionics Facility-assembled production spacecraft. Failed after a few weeks operation..

Long Rod - . Payload: Navspasur Rod. Nation: USA. Agency: USN. Class: Surveillance. Type: Radar calibration target. Spacecraft: Surcal. USAF Sat Cat: 1515 . COSPAR: 1965-065G. Apogee: 1,194 km (741 mi). Perigee: 1,090 km (670 mi). Inclination: 90.00 deg. Period: 108.10 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1965 August 17 - . 20:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1023 - . Payload: KH-4A s/n 1023 / Agena D 1618 / OPS 7208. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-10-11 . USAF Sat Cat: 1513 . COSPAR: 1965-067A. Apogee: 399 km (247 mi). Perigee: 179 km (111 mi). Inclination: 70.00 deg. Period: 90.30 min. KH-4A. Program anomaly caused the fore camera to cease operation during revolutions 103-132..

1965 August 25 - . 15:17 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta C. FAILURE: Premature third stage ignition.. Failed Stage: 3.

OSO C - . Payload: OSO C. Mass: 280 kg (610 lb). Nation: USA. Agency: NASA. Class: Astronomy. Type: Solar satellite. Spacecraft: OSO. Decay Date: 1965-08-25 .

1965 September 2 - . 20:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena D. FAILURE: Agena-D failed; destroyed by range safety.. Failed Stage: U.

Starfish Radiation 2 - . Payload: OPS 3373 / FTV 1602. Mass: 1,150 kg (2,530 lb). Nation: USA. Agency: USAF. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Starfish. Decay Date: 1965-09-02 . Apogee: 11 km (6 mi). Artificial radiation data..

1965 September 10 - . 04:41 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 1.

DMSP-Block-4A F4 - . Payload: DAPP 13 / OPS 8068. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 4A. USAF Sat Cat: 1580 . COSPAR: 1965-072A. Apogee: 993 km (617 mi). Perigee: 635 km (394 mi). Inclination: 98.50 deg. Period: 101.20 min. Defense Meteorological Satellite Program..

1965 September 22 - . 21:31 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 102 - . Payload: KH-4A s/n 102 / Agena D 1619 / OPS 7221. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-10-11 . USAF Sat Cat: 1602 . COSPAR: 1965-074A. Apogee: 364 km (226 mi). Perigee: 191 km (118 mi). Inclination: 80.00 deg. Period: 90.00 min. KH-4A. All cameras operated satisfactorily. Cameras not operated on passes 88D-93D..

1965 October 5 - . 17:45 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1025 - . Payload: KH-4A s/n 1025 / Agena D 1616 / OPS 5325. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-10-29 . USAF Sat Cat: 1615 . COSPAR: 1965-079A. Apogee: 322 km (200 mi). Perigee: 202 km (125 mi). Inclination: 75.10 deg. Period: 89.70 min. KH-4A. Main cameras operated satisfactorily..

1965 October 14 - . 13:11 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

OGO 2 - . Payload: OGO C (S-50). Mass: 507 kg (1,117 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Magnetosphere satellite. Spacecraft: OGO. Decay Date: 1981-09-17 . USAF Sat Cat: 1620 . COSPAR: 1965-081A. Apogee: 1,515 km (941 mi). Perigee: 419 km (260 mi). Inclination: 87.40 deg. Period: 104.40 min.
OGO 2 was a large observatory instrumented with 20 experiments designed to make simultaneous, correlative observations of aurora and airglow emissions, energetic particles, magnetic field variations, ionospheric properties, etc., especially over the polar areas. Soon after achieving orbit, difficulties in maintaining earth lock with horizon scanners caused exhaustion of attitude control gas by October 23, 1965, 10 days after launch. At this time, the spacecraft entered a spin mode (about 0.11 rpm) with a large coning angle about the previously vertical axis. Five experiments became useless when the satellite went into this spin mode. Six additional experiments were degraded by this loss of attitude control. By April 1966, both batteries had failed, so subsequent observations were limited to sunlit portions of the orbit. By December 1966, only eight experiments were operational, five of which were not degraded by the spin mode operation. By April 1967, the tape recorders had malfunctioned and only one third of the recorded data could be processed. Spacecraft power and periods of operational scheduling conflicts created six large data gaps so that data were observed on a total of about 306 days of the 2-yr, 18-day total span of observed satellite data to November 1, 1967. The spacecraft was shut down on November 1, 1967, with eight experiments still operational. It was reactivated for 2 weeks in February 1968 to operate the rubidium vapor magnetometer experiment.

1965 October 28 - . 21:17 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1026 - . Payload: KH-4A s/n 1026 / Agena D 1620 / OPS 2155. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-11-17 . USAF Sat Cat: 1637 . COSPAR: 1965-086A. Apogee: 432 km (268 mi). Perigee: 173 km (107 mi). Inclination: 74.90 deg. Period: 90.50 min. KH-4A. All cameras operated satisfactorily..

1965 November 6 - . 18:38 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta E.

Explorer 29 - . Payload: GEOS A. Mass: 175 kg (385 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Astronomy. Type: Solar satellite. Spacecraft: GEOS. USAF Sat Cat: 1726 . COSPAR: 1965-089A. Apogee: 2,269 km (1,409 mi). Perigee: 1,120 km (690 mi). Inclination: 59.40 deg. Period: 120.30 min.
The primary objective of GEOS-A was to provide global geodetic measurements for determining the positions of fiducial control points on the Earth to an accuracy of 10 meters in an Earth centre of mass co-ordinate system, and to determine the structure of the Earth's gravity field to 5 parts in 10 million. Instrumentation included (1) four optical beacons, (2) laser reflectors, (3) a radio range transponder, (4) Doppler beacons, and (5) a range and range rate transponder. These were designed to operate simultaneously to fulfil the objectives of locating observation points (geodetic control stations) in a three dimensional earth centre-of-mass co-ordinate system within 10 m of accuracy, of defining the structure of the earth's irregular gravitational field and refining the locations and magnitudes of the large gravity anomalies, and of comparing results of the various systems onboard the spacecraft to determine the most accurate and reliable system. In January 1967, a failure in the satellite's command system rendered several geodetic systems inoperable. Radio doppler measurements and the passive laser reflector experiment could continue indefinitely, however. Additional Details: here....

1965 November 29 - . 04:48 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena B.

Alouette 2 - . Payload: Alouette 2 / Explorer 31. Mass: 145 kg (319 lb). Nation: Canada. Agency: DRTE. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Alouette. USAF Sat Cat: 1804 . COSPAR: 1965-098A. Apogee: 2,666 km (1,656 mi). Perigee: 503 km (312 mi). Inclination: 79.80 deg. Period: 117.90 min.
Ionospheric research; data correlated with Explorer 31. The double-launch project, known as ISIS-X was the first in a new co-operative NASA-Canadian Defense Research Board program for International Satellites for Ionospheric Studies. Alouette was in orbit with an apogee just over a kilometre lower than Explorer 31's and with a perigee of just more than a kilometre higher. The orbits were some 3000 km at apogee and 500 km at perigee.

Explorer 31 - . Payload: DME A. Mass: 99 kg (218 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Ionosphere satellite. Spacecraft: DME. USAF Sat Cat: 1806 . COSPAR: 1965-098B. Apogee: 2,833 km (1,760 mi). Perigee: 505 km (313 mi). Inclination: 79.80 deg. Period: 119.70 min.
Ionospheric research; data correlated with Alouette 2. The Explorer 31, Direct Measurement Explorer, was launched with a Canadian Alouette II on November 28, 1965, on a Thor-Agena rocket from Vandenberg Air Force Base, California. The double-launch project, known as ISIS-X was the first in a new co-operative NASA-Canadian Defense Research Board program for International Satellites for Ionospheric Studies. Explorer 31 was in orbit with an apogee just over a kilometre more than Alouette's and with a perigee of just more than a kilometre lower. The orbits were some 3000 km at apogee and 500 km at perigee. Eight ionospheric measurement experiments sampled the environment both forward and after the satellite's path.

1965 December 7 - . 02:28 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

AFP-437(AP) interceptor mission - . Nation: USA. Agency: USAF. Apogee: 487 km (302 mi).

1965 December 9 - . 21:10 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1027 - . Payload: KH-4A s/n 1027 / Agena D 1621 / OPS 7249. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1965-12-26 . USAF Sat Cat: 1816 . COSPAR: 1965-102A. Apogee: 439 km (272 mi). Perigee: 186 km (115 mi). Inclination: 80.10 deg. Period: 90.80 min. KH-4A. Erratic attitude necessitated recovery after two days of operation. All cameras operated satisfactorily..

1965 December 16 - . 07:31 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta E.

Pioneer 6 - . Payload: Pioneer A. Mass: 63 kg (138 lb). Nation: USA. Agency: NASA Ames. Program: Pioneer. Class: Astronomy. Type: Solar satellite. Spacecraft: Pioneer 6-7-8-9-E. USAF Sat Cat: 1841 . COSPAR: 1965-105A. Measured solar wind, Sun's magnetic field. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

1965 December 24 - . 21:06 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1028 - . Payload: KH-4A s/n 1028 / Agena D 1610 / OPS 4639. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1966-01-20 . USAF Sat Cat: 1866 . COSPAR: 1965-110A. Apogee: 443 km (275 mi). Perigee: 181 km (112 mi). Inclination: 80.00 deg. Period: 90.70 min. KH-4A. Cameras operated satisfactorily..

1966 Jan - . LV Family: Thor.

Long Tank Thor (SLV-2G) to replace the Thrust Augmented Thor (SLV-2A). - .
Space Systems Division announced the purchase of newly designed Long Tank Thor (SLV-2G) space boosters to replace the Thrust Augmented Thor (SLV-2A). The Long Tank Thrust Augmented Thor (LTTAT) would be 14 feet longer than the older SLV-2A and would have a 40 percent increase in the volume of the liquid propellant fuel tanks. The additional fuel would give the Long Tank Thor a longer burn time than the Thrust Augmented Thor, 216 seconds versus 146 seconds. As a result of this improvement and the replacement of the Castor I (TX-33-52) solid-rocket booster motors with Thiokol's Castor II (TX-354-5) motors of 70.540 pounds of thrust, the new SLV-2G, dubbed the Thorad, would provide a 20 percent increase in payload capacity over the SLV-2A.

1966 January 8 - . 04:48 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 1. FAILURE: Second stage failed.. Failed Stage: 2.

DMSP-Block-4A F5 - . Payload: DAPP 14/OPS 2394. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 4A. Decay Date: 1966-01-06 . Defense Meteorological Satellite Program..

1966 January 18 - . 18:11 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

AFP-437(AP) interceptor mission - . Nation: USA. Agency: USAF. Apogee: 459 km (285 mi).

1966 February 2 - . 21:32 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1029 - . Payload: KH-4A s/n 1029 / Agena D 1623 / OPS 7291. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1966-02-27 . USAF Sat Cat: 1968 . COSPAR: 1966-007A. Apogee: 428 km (265 mi). Perigee: 182 km (113 mi). Inclination: 75.00 deg. Period: 90.60 min. KH-4A. Both panoramic cameras were operational throughout..

1966 February 3 - . 07:41 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta C.

ESSA 1 - . Payload: Tiros OT3. Mass: 138 kg (304 lb). Nation: USA. Agency: ESSA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Tiros. USAF Sat Cat: 1982 . COSPAR: 1966-008A. Apogee: 806 km (500 mi). Perigee: 684 km (425 mi). Inclination: 97.80 deg. Period: 99.70 min. Environmental Survey Satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1966 February 9 - . 19:45 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

OPS 1439 - . Payload: Ferret 9 / Agena D 2703. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1969-09-26 . USAF Sat Cat: 1997 . COSPAR: 1966-009A. Apogee: 511 km (317 mi). Perigee: 507 km (315 mi). Inclination: 82.00 deg. Period: 94.70 min.

1966 February 28 - . 13:58 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta E.

ESSA 2 - . Payload: Tiros OT2. Mass: 132 kg (291 lb). Nation: USA. Agency: ESSA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Tiros. USAF Sat Cat: 2091 . COSPAR: 1966-016A. Apogee: 1,415 km (879 mi). Perigee: 1,355 km (841 mi). Inclination: 101.30 deg. Period: 113.50 min. Environmental Survey Satellite; carried APT cameras. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1966 March 9 - . 22:02 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1030 - . Payload: KH-4A s/n 1030 / Agena D 1622 / OPS 3488. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1966-03-29 . USAF Sat Cat: 2099 . COSPAR: 1966-018A. Apogee: 418 km (259 mi). Perigee: 180 km (110 mi). Inclination: 75.00 deg. Period: 90.40 min. KH-4A. All cameras operated satisfactorily..

1966 March 12 - . 00:42 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

AFP-437(AP) interceptor mission - . Nation: USA. Agency: USAF. Apogee: 472 km (293 mi).

1966 March 31 - . 05:41 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 1.

DMSP-Block-4A F6 - . Payload: DAPP 15 / OPS 0340. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 4A. USAF Sat Cat: 2125 . COSPAR: 1966-026A. Apogee: 855 km (531 mi). Perigee: 604 km (375 mi). Inclination: 98.30 deg. Period: 99.40 min. The last Thor/Altair (Burner I) was launched from Vandenberg AFB. The improved Burner II would replace the Altair upper stage. Defense Meteorological Satellite Program..

1966 April 7 - . 22:02 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1031 - . Payload: KH-4A s/n 1031 / Agena D 1627 / OPS 1612. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1966-04-26 . USAF Sat Cat: 2136 . COSPAR: 1966-029A. Apogee: 312 km (193 mi). Perigee: 193 km (119 mi). Inclination: 75.10 deg. Period: 89.60 min. KH-4A. The aft-looking camera malfunctioned after the recovery of bucket '1'. No material was received in bucket '2' (1031-2)..

1966 May 3 - . 19:25 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D. FAILURE: Failure. Failed Stage: U.

KH-4A 1032 - . Payload: KH-4A s/n 1032. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1966-05-04 .

SRV 707 - . Payload: SRV 1032-1. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A.

SRV 708 - . Payload: SRV 1032-2. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A.

1966 May 15 - . 07:55 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena B.

Nimbus 2 - . Payload: Nimbus C. Mass: 414 kg (912 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Weather satellite. Spacecraft: Nimbus. USAF Sat Cat: 2173 . COSPAR: 1966-040A. Apogee: 1,176 km (730 mi). Perigee: 1,093 km (679 mi). Inclination: 100.30 deg. Period: 108.00 min.
The last Thrust Augmented Thor/Agena B was used to place NASA's NIMBUS II meteorological satellite into orbit. TV, IR cloud cover photos. The spacecraft carried an advanced vidicon camera system for recording and storing remote cloud cover pictures, an automatic picture transmission camera for providing real-time cloudcover pictures, and both high- and medium-resolution infrared radiometers (HRIR and MRIR) for measuring the intensity and distribution of electromagnetic radiation emitted by and reflected from the earth and its atmosphere. The spacecraft and experiments performed normally after launch until July 26, 1966, when the spacecraft tape recorder failed. Its function was taken over by the HRIR tape recorder until November 15, 1966, when it also failed. Some real-time data were collected until January 17, 1969, when the spacecraft mission was terminated owing to deterioration of the horizon scanner used for earth reference.

1966 May 24 - . 02:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1033 - . Payload: KH-4A s/n 1033 / Agena D 1630 / OPS 1778. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1966-06-09 . USAF Sat Cat: 2181 . COSPAR: 1966-042A. Apogee: 271 km (168 mi). Perigee: 179 km (111 mi). Inclination: 66.00 deg. Period: 89.00 min. KH-4A. The stellar camera shutter of bucket '2' remained open for approximately 200 frames..

1966 May 25 - . 14:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta C1.

Explorer 32 - . Payload: AE B. Mass: 225 kg (496 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Atmosphere satellite. Spacecraft: AE. Decay Date: 1985-02-22 . USAF Sat Cat: 2183 . COSPAR: 1966-044A. Apogee: 2,723 km (1,691 mi). Perigee: 282 km (175 mi). Inclination: 64.60 deg. Period: 116.00 min. Atmospheric Explorer; aeronomy experiments. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1966 June 21 - . 21:31 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1034 - . Payload: KH-4A s/n 1034 / Agena D 1626 / OPS 1599. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1966-07-14 . USAF Sat Cat: 2227 . COSPAR: 1966-055A. Apogee: 359 km (223 mi). Perigee: 207 km (128 mi). Inclination: 80.10 deg. Period: 90.10 min. KH-4A. Failure of velocity/altitude programmer produced poor imagery after revolution 5..

1966 June 24 - . 00:12 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

Pageos 1 - . Payload: Pageos A. Mass: 55 kg (121 lb). Nation: USA. Agency: NASA Langley. Class: Earth. Type: Geodetic satellite. Spacecraft: Pageos. Decay Date: 1975-07-12 . USAF Sat Cat: 2253 . COSPAR: 1966-056A. Apogee: 4,220 km (2,620 mi). Perigee: 3,913 km (2,431 mi). Inclination: 85.40 deg. Period: 177.10 min.
The PAGEOS (Passive Geodetic Earth Orbiting Satellite) spacecraft was a 30.48-m inflatable sphere, and had no instrumentation on board. It was the second (following GEOS 1) NASA satellite in the National Geodetic Satellites Program. The launch, orbit, separation, inflation and initial operation were nominal, with more than 40 ground stations participating in the observation program. The orbit was generally considered too high for drag-density study, although some work was done in this area by the Smithsonian Astrophysical Observatory. Additional Details: here....

Pageos canister half - . Payload: Pageos canister half. Mass: 55 kg (121 lb). Nation: USA. Agency: NASA Langley. Spacecraft: Pageos. USAF Sat Cat: 2256 . COSPAR: 1966-056C. Apogee: 4,276 km (2,656 mi). Perigee: 4,196 km (2,607 mi). Inclination: 86.90 deg. Period: 181.40 min.

Pageos canister half - . Payload: Pageos canister half. Mass: 55 kg (121 lb). Nation: USA. Agency: NASA Langley. Spacecraft: Pageos. USAF Sat Cat: 2511 . COSPAR: 1966-056D. Apogee: 4,255 km (2,643 mi). Perigee: 4,227 km (2,626 mi). Inclination: 87.00 deg. Period: 181.50 min.

1966 July 1 - . 16:02 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta E1.

Explorer 33 - . Payload: AIMP D. Mass: 93 kg (205 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Magnetosphere satellite. Spacecraft: IMP. USAF Sat Cat: 2258 . COSPAR: 1966-058A. Apogee: 480,762 km (298,731 mi). Perigee: 265,679 km (165,084 mi). Inclination: 24.10 deg. Period: 38,792.40 min. Intended to enter lunar orbit. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1966 July 2 - . 20:53 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

AFP-437(AP) interceptor mission - . Nation: USA. Agency: USAF. Apogee: 802 km (498 mi).

1966 August 9 - . 20:46 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4A 1036 - . Payload: KH-4A s/n 1036 / Agena D 1631 / OPS 1545. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1966-09-11 . USAF Sat Cat: 2393 . COSPAR: 1966-072A. Apogee: 284 km (176 mi). Perigee: 190 km (110 mi). Inclination: 100.10 deg. Period: 89.20 min. KH-4A. All cameras operated satisfactorily..

1966 August 17 - . 15:20 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta E1.

Pioneer 7 - . Payload: Pioneer B. Mass: 63 kg (138 lb). Nation: USA. Agency: NASA Ames. Program: Pioneer. Class: Astronomy. Type: Solar satellite. Spacecraft: Pioneer 6-7-8-9-E. USAF Sat Cat: 2398 . COSPAR: 1966-075A. Apogee: 993 km (617 mi). Perigee: 246 km (152 mi). Inclination: 33.00 deg. Period: 97.20 min. Monitored solar wind, cosmic rays. SOLAR ORB. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

1966 September 16 - . 04:36 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2.

DMSP-Block-4A F7 - . Payload: DAPP 1416 (FTV-3) / OPS 6026. Mass: 125 kg (275 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 4A. USAF Sat Cat: 2418 . COSPAR: 1966-082A. Apogee: 857 km (532 mi). Perigee: 674 km (418 mi). Inclination: 98.30 deg. Period: 100.20 min. Defense Meteorological Satellite Program..

1966 September 20 - . 21:14 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1035 - . Payload: KH-4A s/n 1035 / Agena D 1628 / OPS 1703. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1966-10-12 . USAF Sat Cat: 2427 . COSPAR: 1966-085A. Apogee: 430 km (260 mi). Perigee: 182 km (113 mi). Inclination: 85.10 deg. Period: 90.60 min. KH-4A. All cameras operated satisfactorily. First mission flown with pan geometry modification..

1966 October 2 - . 10:39 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta E.

ESSA 3 - . Payload: TOS A. Mass: 145 kg (319 lb). Nation: USA. Agency: ESSA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: TOS. USAF Sat Cat: 2435 . COSPAR: 1966-087A. Apogee: 1,486 km (923 mi). Perigee: 1,387 km (861 mi). Inclination: 100.90 deg. Period: 114.60 min. Environmental Survey Satellite 3; replace ESSA 1. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1966 October 26 - . 23:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta E1. FAILURE: Partial Failure.. Failed Stage: U.

Intelsat 2 F-1 - . Mass: 140 kg (300 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 303. Spacecraft: Intelsat 2. Decay Date: 1982-09-07 . USAF Sat Cat: 2514 . COSPAR: 1966-096A. Apogee: 37,070 km (23,030 mi). Perigee: 3,328 km (2,067 mi). Inclination: 17.30 deg. Period: 718.70 min. Unusable orbit due to AKM failure. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1966 November 8 - . 19:53 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4A 1037 - . Payload: KH-4A s/n 1037 / Agena D 1632 / OPS 1866. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1966-11-29 . USAF Sat Cat: 2537 . COSPAR: 1966-102A. Apogee: 300 km (180 mi). Perigee: 179 km (111 mi). Inclination: 100.00 deg. Period: 89.20 min. KH-4A. Second pan geometry mission. Higher than normal base plus fog encountered on both main camera records..

1966 December 14 - . 19:20 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta G.

Biosatellite 1 - . Payload: Biosat 1. Mass: 425 kg (936 lb). Nation: USA. Agency: NASA Ames. Class: Biology. Type: Biology satellite. Spacecraft: Biosatellite. Decay Date: 1967-02-15 . USAF Sat Cat: 2631 . COSPAR: 1966-114C. Apogee: 309 km (192 mi). Perigee: 295 km (183 mi). Inclination: 33.50 deg. Period: 90.40 min.
Reentry into the Earth's atmosphere was not achieved because the retrorocket failed to ignite. The biosatellite was never recovered. Although the scientific objectives of the mission were not accomplished, the Biosatellite I experience provided technical confidence in the program because of excellent performance in most other areas.

1966 December 29 - . 12:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

OPS 1584 - . Payload: Ferret 10 / Agena D 2731. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1969-04-05 . USAF Sat Cat: 2634 . COSPAR: 1966-118A. Apogee: 495 km (307 mi). Perigee: 487 km (302 mi). Inclination: 75.00 deg. Period: 94.40 min.

1967 January 11 - . 10:55 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta E1.

Intelsat 2 F-2 - . Mass: 87 kg (191 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 303. Spacecraft: Intelsat 2. Completed Operations Date: 1977-05-01 . USAF Sat Cat: 2639 . COSPAR: 1967-001A. Apogee: 35,808 km (22,250 mi). Perigee: 35,769 km (22,225 mi). Inclination: 1.60 deg. Period: 1,436.20 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 174 deg E in 1967-1969; over the Pacific Ocean 162-170 deg E in 1969-1970; over the Pacific Ocean 150-160 deg E in 1970-1975 As of 7 August 2001 located at 48.66 deg E drifting at 0.413 deg W per day. As of 2007 Mar 8 located at 63.48W drifting at 0.357W degrees per day.

1967 January 14 - . 21:28 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1038 - . Payload: KH-4A s/n 1038 / Agena D 1629 / OPS 1664. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1967-02-02 . USAF Sat Cat: 2642 . COSPAR: 1967-002A. Apogee: 355 km (220 mi). Perigee: 177 km (109 mi). Inclination: 80.10 deg. Period: 89.80 min. KH-4A. Fair image quality..

1967 January 26 - . 17:31 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta E.

ESSA 4 - . Payload: TOS B. Mass: 132 kg (291 lb). Nation: USA. Agency: ESSA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: TOS. USAF Sat Cat: 2657 . COSPAR: 1967-006A. Apogee: 1,440 km (890 mi). Perigee: 1,326 km (823 mi). Inclination: 102.00 deg. Period: 113.40 min. Replaced ESSA 2. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1967 February 8 - . 08:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2.

DMSP-Block-4A F8 - . Payload: DAPP 2418 (FTV-2) / OPS 6073. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 4A. USAF Sat Cat: 2669 . COSPAR: 1967-010A. Apogee: 846 km (525 mi). Perigee: 771 km (479 mi). Inclination: 99.10 deg. Period: 101.10 min. Defense Meteorological Satellite Program; lower than planned orbit, but still operational..

1967 February 22 - . 22:02 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1039 - . Payload: KH-4A s/n 1039 / Agena D 1635 / OPS 4750. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1967-03-11 . USAF Sat Cat: 2686 . COSPAR: 1967-015A. Apogee: 380 km (230 mi). Perigee: 180 km (110 mi). Inclination: 80.00 deg. Period: 90.10 min. KH-4A. Normal KH-4 mission. Light from horizon camera on both main camera records during 1039-1..

1967 March 8 - . LV Family: Thor.

Skynet contract award. - . Spacecraft: Skynet.
Space Systems Division awarded the Space and Reentry Systems Division of Philco-Ford Corporation a contract for the development and production of the spacecraft for the United Kingdom's Skynet. Two spin-stabilized, synchronous, station-keeping satellites were to be produced. Thrust Augmented Thor/Delta boosters and launch services would be procured from NASA by Space Systems Division to place the satellite into orbit. When operational, both Skynet satellites would form part of the larger United States Initial Defense Satellite Communication System Program (IDSCS).

1967 March 8 - . 16:12 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta C.

OSO 3 - . Payload: OSO E1. Mass: 281 kg (619 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: Solar satellite. Spacecraft: OSO. Decay Date: 1982-04-04 . USAF Sat Cat: 2703 . COSPAR: 1967-020A. Apogee: 570 km (350 mi). Perigee: 546 km (339 mi). Inclination: 32.80 deg. Period: 95.80 min. Orbiting Solar Observatory. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1967 March 23 - . 01:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta E1.

Intelsat 2 F-3 - . Mass: 192 kg (423 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 303. Spacecraft: Intelsat 2. Completed Operations Date: 1977-05-01 . USAF Sat Cat: 2717 . COSPAR: 1967-026A. Apogee: 35,899 km (22,306 mi). Perigee: 35,670 km (22,160 mi). Inclination: 12.50 deg. Period: 1,436.00 min.
Positioned in geosynchronous orbit over the Atlantic Ocean at 15 deg W in 1967-1971; over the Atlantic Ocean at 35 deg W in 1972; over the Atlantic Ocean at 15 deg W in 1973. As of 22 August 2001 was at 6.75 deg W drifting at 0.037 deg W per day. As of 2005 Dec 5 located at 13.34E drifting at 0.188W degrees per day. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1967 March 30 - . 18:54 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

KH-4A 1040 - . Payload: KH-4A s/n 1040 / Agena D 1636 / OPS 4779. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1967-04-17 . USAF Sat Cat: 2736 . COSPAR: 1967-029A. Apogee: 326 km (202 mi). Perigee: 167 km (103 mi). Inclination: 85.00 deg. Period: 89.50 min. KH-4A. Satellite flown nose first, all cameras operated satisfactorily..

1967 March 31 - . 06:44 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE1. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

AFP-437 combat evaluation interceptor mission - . Nation: USA. Agency: USAF. Apogee: 484 km (300 mi).

1967 April 20 - . 11:21 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta E.

ESSA 5 - . Payload: TOS C. Mass: 145 kg (319 lb). Nation: USA. Agency: ESSA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: TOS. USAF Sat Cat: 2757 . COSPAR: 1967-036A. Apogee: 1,422 km (883 mi). Perigee: 1,355 km (841 mi). Inclination: 102.00 deg. Period: 113.50 min. Replaced ESSA 3. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1967 May 9 - . 21:50 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D. FAILURE: Failure of the booster cut-off switch.. Failed Stage: 1.

KH-4A 1041 - . Payload: KH-4A s/n 1041 / Agena D 1634 / OPS 4696. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1967-07-13 . USAF Sat Cat: 2779 . COSPAR: 1967-043A. Apogee: 791 km (491 mi). Perigee: 183 km (113 mi). Inclination: 85.00 deg. Period: 94.30 min. KH-4A. Due to the failure of the booster cut-off switch, the satellite went into a highly eccentric orbit. Significant image degradation..

SRV 731 - . Payload: SRV 1041-1. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1993-03-14 . USAF Sat Cat: 2780 . COSPAR: 1967-043xx. Apogee: 145 km (90 mi). Perigee: 131 km (81 mi). Inclination: 84.90 deg. Period: 87.20 min.

OPS 1967 - . Payload: EHH B7. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1993-03-14 . USAF Sat Cat: 2780 . COSPAR: 1967-043B. Apogee: 458 km (284 mi). Perigee: 399 km (247 mi). Inclination: 84.90 deg. Period: 93.20 min. Radar monitoring. Due to the failure of the booster cut-off switch, the satellite went into a highly eccentric orbit..

1967 May 24 - . 14:05 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta E1.

Explorer 34 - . Payload: IMP F. Mass: 75 kg (165 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Magnetosphere satellite. Spacecraft: IMP. Decay Date: 1969-05-03 . USAF Sat Cat: 2817 . COSPAR: 1967-051A. Apogee: 214,379 km (133,208 mi). Perigee: 242 km (150 mi). Inclination: 67.10 deg. Period: 6,358.20 min. Radiation, magnetic field data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1967 May 31 - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2 Agena D.

Surcal 160 - . Payload: NRL PL160 / Agena D 2704. Mass: 2.00 kg (4.40 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Radar calibration target. Spacecraft: Surcal. USAF Sat Cat: 2825 . COSPAR: 1967-053B. Apogee: 927 km (576 mi). Perigee: 923 km (573 mi). Inclination: 69.90 deg. Period: 103.50 min. 20 inch dia. calibration sphere. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

Calsphere 4 - . Payload: Agena D 2704 / OPS 5712. Nation: USA. Agency: NRL. Class: Surveillance. Type: Radar calibration target. Spacecraft: Calsphere. USAF Sat Cat: 2826 . COSPAR: 1967-053A. Apogee: 834 km (518 mi). Perigee: 815 km (506 mi). Inclination: 69.90 deg. Period: 101.40 min. The last Air Force Thor/Agena D, SLV-2 #443 and SS-01B #2704, was launched from Vandenberg. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

SURCAL 150B - . Payload: NRL PL150B. Mass: 2.00 kg (4.40 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Radar calibration target. Spacecraft: SURCAL. USAF Sat Cat: 2909 . COSPAR: 1967-053J. Apogee: 816 km (507 mi). Perigee: 805 km (500 mi). Inclination: 70.00 deg. Period: 101.10 min. The last Air Force Thor/Agena D, SLV-2 #443 and SS-01B #2704, was launched from Vandenberg. 16 inch dia. calibration sphere. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

Surcal (153) - . Payload: NRL PL153 / OPS 5712 / Poppy 5C (Poppy multifacete. Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 2874 . COSPAR: 1967-053H. Apogee: 912 km (566 mi). Perigee: 905 km (562 mi). Inclination: 70.00 deg. Period: 103.20 min. Poppy naval signals intelligence satellite. Official and secondary mission: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

Calsphere 3 - . Payload: NRL PL159. Mass: 38 kg (83 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Radar calibration target. Spacecraft: Calsphere. USAF Sat Cat: 2872 . COSPAR: 1967-053F. Apogee: 906 km (562 mi). Perigee: 900 km (550 mi). Inclination: 70.00 deg. Period: 103.10 min. Surveillance Calibration. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

GGSE 4 - . Payload: NRL PL152 / Poppy 5B (Poppy multifaceted). Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 2828 . COSPAR: 1967-053C. Apogee: 910 km (560 mi). Perigee: 903 km (561 mi). Inclination: 70.00 deg. Period: 103.10 min.
Second launch of a quadruplet of Poppy naval signals intelligence satellites, which would lead to the NOSS production series. Official and secondary mission: Gravity gradient stabilization tests. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

GGSE 5 - . Payload: NRL PL154 / Poppy 5D (Poppy multifaceted). Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 2834 . COSPAR: 1967-053D. Apogee: 913 km (567 mi). Perigee: 906 km (562 mi). Inclination: 70.00 deg. Period: 103.20 min. Poppy naval signals intelligence satellite. Official and secondary mission: Gravity gradient stabilization tests. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

Timation 1 - . Mass: 700 kg (1,540 lb). Nation: USA. Agency: NRL. Program: Navstar. Class: Technology. Type: Navigation technology satellite. Spacecraft: Timation. USAF Sat Cat: 2847 . COSPAR: 1967-053E. Apogee: 900 km (550 mi). Perigee: 894 km (555 mi). Inclination: 70.00 deg. Period: 102.90 min. Navigation experiments leading eventually to Navstar/GPS system. Operated for 74 months..

Surcal (151) - . Payload: NRL PL151 / OPS 5712 / Poppy 5A (Poppy 24-inch). Mass: 4.00 kg (8.80 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 2873 . COSPAR: 1967-053G. Apogee: 910 km (560 mi). Perigee: 902 km (560 mi). Inclination: 70.00 deg. Period: 103.10 min. Poppy naval signals intelligence satellite. Official and secondary mission: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

1967 June 16 - . 21:35 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4A 1042 - . Payload: KH-4A s/n 1042 / Agena D 1633 / OPS 3559. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1967-07-20 . USAF Sat Cat: 2850 . COSPAR: 1967-062A. Apogee: 380 km (230 mi). Perigee: 169 km (105 mi). Inclination: 80.00 deg. Period: 90.00 min. KH-4A. Small out-of-focus area in forward camera of 1042-1..

OPS 1873 - . Payload: EHH B8. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1968-10-22 . USAF Sat Cat: 2851 . COSPAR: 1967-062B. Apogee: 517 km (321 mi). Perigee: 501 km (311 mi). Inclination: 80.20 deg. Period: 94.80 min. Radar monitoring..

SRV 725 - . Payload: SRV 1042-1. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1968-10-22 . USAF Sat Cat: 2851 . COSPAR: 1967-062xx. Apogee: 197 km (122 mi). Perigee: 182 km (113 mi). Inclination: 80.20 deg. Period: 88.30 min.

1967 June 29 - . 21:01 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2.

SECOR 9 - . Payload: EGRS 9. Mass: 20 kg (44 lb). Nation: USA. Agency: USA ACE. Class: Earth. Type: Geodetic satellite. Spacecraft: SECOR. USAF Sat Cat: 2861 . COSPAR: 1967-065A. Apogee: 3,940 km (2,440 mi). Perigee: 3,803 km (2,363 mi). Inclination: 90.20 deg. Period: 172.10 min.
Two scientific satellites, an Army Sequential Collation of Range (SECOR) and a Navy Aurora I, were launched from Vandenberg aboard a Thor/Burner II. This was the first flight in the Department of Defense's Space Experiments Support Program (SESP), a tri-service program that allowed qualified government-sponsored space experimenters to fly payloads on Air Force boosters. Space Systems Division managed the program and provided boosters, payload integration, and launch services. Defense's Space Experiments Support Program (SESP), a tri-service program that allowed qualified government-sponsored space experimenters to fly payloads on Air Force boosters. Space Systems Division managed the program and provided boosters, payload integration, and launch services. Location survey. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

Aurora 1 - . Payload: Aurora (P 67-1). Mass: 21 kg (46 lb). Nation: USA. Agency: USN. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Aurora. USAF Sat Cat: 2876 . COSPAR: 1967-065B. Apogee: 3,937 km (2,446 mi). Perigee: 3,808 km (2,366 mi). Inclination: 90.20 deg. Period: 172.10 min.
Two scientific satellites, an Army Sequential Collation of Range (SECOR) and a Navy Aurora I, were launched from Vandenberg aboard a Thor/Burner II. This was the first flight in the Department of Defense's Space Experiments Support Program (SESP), a tri-service program that allowed qualified government-sponsored space experimenters to fly payloads on Air Force boosters. Space Systems Division managed the program and provided boosters, payload integration, and launch services. Defense's Space Experiments Support Program (SESP), a tri-service program that allowed qualified government-sponsored space experimenters to fly payloads on Air Force boosters. Space Systems Division managed the program and provided boosters, payload integration, and launch services. Investigated aurora borealis. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1967 July 19 - . 14:19 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta E1.

Explorer 35 - . Payload: AIMP E. Mass: 104 kg (229 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Magnetosphere satellite. Spacecraft: IMP. USAF Sat Cat: 2884 . COSPAR: 1967-070A. Apogee: 675 km (419 mi). Perigee: 484 km (300 mi). Inclination: 32.40 deg. Period: 96.26 min.
Earth magnetic tail measurements. Lunar Orbit (Selenocentric). The Westinghouse Aerospace Division, under contract to National Aeronautics and Space Administration's Goddard Space Flight Center, engaged in the system design, integration, assembly and launch support for Anchored Interplanetary Monitoring Platform Satellite, officially designated Explorer 35 by the National Aeronautics and Space Administration. It was launched on July 19, 1967, with the primary objectives of investigation of interplanetary plasma and the interplanetary magnetic field out to and at the lunar distance, in either a captured lunar orbit or a geocentric orbit of the earth. In the geocentric orbit, the apogee was near or beyond the lunar distance. In a lunar orbit, additional objectives included obtaining data on dust distribution, lunar gravitational field, ionosphere, magnetic field, and radiation environment around the moon. AIMP-E also studied spatial and temporal relationships of geophysical and interplanetary phenomena simultaneously being studied by several other National Aeronautics and Space Administration satellites. The investigation in the vicinity of the moon provided for measurements of the characteristics of the interplanetary dust distribution, solar and galactic cosmic rays, as well as a study of the magnetohydrodynamic wake of the earth in the interplanetary medium at the lunar distances.

1967 July 25 - . 03:48 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

OPS 1879 - . Payload: Ferret 11 / Agena D 2732. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1969-06-05 . USAF Sat Cat: 2890 . COSPAR: 1967-071A. Apogee: 608 km (377 mi). Perigee: 390 km (240 mi). Inclination: 75.10 deg. Period: 94.50 min.

1967 July 28 - . 14:21 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

OGO 4 - . Payload: OGO D (NASA S-50A). Mass: 634 kg (1,397 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Magnetosphere satellite. Spacecraft: OGO. Decay Date: 1972-08-16 . USAF Sat Cat: 2895 . COSPAR: 1967-073A. Apogee: 885 km (549 mi). Perigee: 422 km (262 mi). Inclination: 86.00 deg. Period: 97.80 min.
OGO 4 was a large observatory instrumented with experiments designed to study the interrelationships between the aurora and airglow emissions, energetic particle activity, geomagnetic field variation, ionospheric ionization and recombination, and atmospheric heating which take place during a period of increased solar activity. After the spacecraft achieved orbit and the experiments were deployed into an operating mode, an attitude control problem occurred. This condition was corrected by ground control procedures until complete failure of the tape recording systems in mid-January 1969. At that time, due to the difficulty of maintaining attitude control without the tape recorders, the attitude control system was commanded off, and the spacecraft was placed into a spin-stabilized mode about the axis which was previously maintained vertically. In this mode, seven of the remaining experiments were turned off since no meaningful data could be observed by them. On October 23, 1969, the satellite was turned off. It was reactivated again in January 1970 for 2 months to obtain VLF observations.

1967 August 7 - . 21:44 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4A 1043 - . Payload: KH-4A s/n 1043 / Agena D 1637 / OPS 4827. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1967-09-01 . USAF Sat Cat: 2910 . COSPAR: 1967-076A. Apogee: 346 km (214 mi). Perigee: 174 km (108 mi). Inclination: 79.90 deg. Period: 89.70 min. KH-4A. Forward camera film came out of the rails on pass 230D. Film degraded past this point..

1967 August 23 - . 04:41 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2.

DMSP-Block-4A F9 - . Payload: DAPP 3419 (FTV-4) / OPS 7202. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 4A. USAF Sat Cat: 2920 . COSPAR: 1967-080A. Apogee: 873 km (542 mi). Perigee: 818 km (508 mi). Inclination: 98.90 deg. Period: 101.90 min. Defense Meteorological Satellite Program..

1967 September 7 - . 22:04 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta G.

Biosatellite 2 - . Payload: Biosat 2. Mass: 507 kg (1,117 lb). Nation: USA. Agency: NASA Ames. Class: Biology. Type: Biology satellite. Spacecraft: Biosatellite. Decay Date: 1967-09-15 . USAF Sat Cat: 2935 . COSPAR: 1967-083A. Apogee: 318 km (197 mi). Perigee: 297 km (184 mi). Inclination: 33.50 deg. Period: 90.70 min.
Biological capsule recovered. The scientific payload, consisting of 13 select biology and radiation experiments, was exposed to microgravity during 45 hours of Earth-orbital flight. Experimental biology packages on the spacecraft contained a variety of specimens, including insects, frog eggs, microorganisms and plants. The planned three-day mission was recalled early because of the threat of a tropical storm in the recovery area, and because of a communication problem between the spacecraft and the tracking systems. The primary objective of the Biosatellite II mission was to determine if organisms were more, or less, sensitive to ionizing radiation in microgravity than on Earth. To study this question, an artificial source of radiation was supplied to a group of experiments mounted in the forward part of the spacecraft.

1967 September 15 - . 19:41 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4B 1101 - . Payload: KH-4B s/n 1101 / Agena D 1641 / OPS 5089. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1967-10-04 . USAF Sat Cat: 2946 . COSPAR: 1967-087A. Apogee: 372 km (231 mi). Perigee: 156 km (96 mi). Inclination: 80.00 deg. Period: 89.70 min. KH-4B. First mission of the KH-4B series. Best film to date..

1967 September 28 - . 00:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta E1.

Intelsat 2 F-4 - . Mass: 87 kg (191 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: HS 303. Spacecraft: Intelsat 2. Completed Operations Date: 1977-05-01 . USAF Sat Cat: 2969 . COSPAR: 1967-094A. Apogee: 35,885 km (22,297 mi). Perigee: 35,729 km (22,200 mi). Inclination: 13.00 deg. Period: 1,437.10 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 176 deg E in 1967-1970; over the Pacific Ocean 166 deg W in 1971; over the Atlantic Ocean 30-42 deg W in 1972 As of 1 August 2001 located at 36.36 deg W drifting at 0.096 deg E per day. As of 2007 Mar 7 located at 168.68W drifting at 0.093W degrees per day.

1967 October 11 - . 07:57 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2.

DMSP-Block-4A F10 - . Payload: DAPP 4417 (FTV-5) / OPS 1264. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 4A. USAF Sat Cat: 2980 . COSPAR: 1967-096A. Apogee: 796 km (494 mi). Perigee: 638 km (396 mi). Inclination: 99.20 deg. Period: 99.10 min. Defense Meteorological Satellite Program..

1967 October 18 - . 15:58 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta C1.

OSO 4 - . Payload: OSO D. Mass: 272 kg (599 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: Solar satellite. Spacecraft: OSO. Decay Date: 1982-06-15 . USAF Sat Cat: 3000 . COSPAR: 1967-100A. Apogee: 555 km (344 mi). Perigee: 552 km (342 mi). Inclination: 32.90 deg. Period: 95.70 min. Extreme UV solar observations. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1967 November 2 - . 21:31 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4A 1044 - . Payload: KH-4A s/n 1044 / OPS 0562. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1967-12-02 . USAF Sat Cat: 3024 . COSPAR: 1967-109A. Apogee: 410 km (250 mi). Perigee: 184 km (114 mi). Inclination: 81.50 deg. Period: 90.40 min. KH-4A. All cameras operated fine..

SRV 733 - . Payload: SRV 1044-1. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1969-03-28 . USAF Sat Cat: 3025 . COSPAR: 1967-109xx. Apogee: 208 km (129 mi). Perigee: 179 km (111 mi). Inclination: 81.60 deg. Period: 88.40 min.

OPS 1587 - . Payload: EHH B9. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1969-03-28 . USAF Sat Cat: 3025 . COSPAR: 1967-109B. Apogee: 525 km (326 mi). Perigee: 454 km (282 mi). Inclination: 81.60 deg. Period: 94.30 min. Radar monitoring..

1967 November 10 - . 17:53 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta E1.

ESSA 6 - . Payload: TOS D. Mass: 132 kg (291 lb). Nation: USA. Agency: ESSA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: TOS. USAF Sat Cat: 3035 . COSPAR: 1967-114A. Apogee: 1,485 km (922 mi). Perigee: 1,409 km (875 mi). Inclination: 102.10 deg. Period: 114.80 min. Returned cloud cover images. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1967 December 9 - . 22:26 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4B 1102 - . Payload: KH-4B s/n 1102 / Agena D 1642 / OPS 1001. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1967-12-25 . USAF Sat Cat: 3063 . COSPAR: 1967-122A. Apogee: 248 km (154 mi). Perigee: 151 km (93 mi). Inclination: 81.60 deg. Period: 88.40 min. KH-4B. Noticeable image smear for forward camera, but best imagery to date..

1967 December 13 - . 14:08 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta E1.

Pioneer 8 - . Payload: Pioneer C / TTS 1. Mass: 63 kg (138 lb). Nation: USA. Agency: NASA Ames. Program: Pioneer. Class: Astronomy. Type: Solar satellite. Spacecraft: Pioneer 6-7-8-9-E. USAF Sat Cat: 3066 . COSPAR: 1967-123A. Solar radiation data. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

TTS 1 - . Payload: TTS A. Mass: 20 kg (44 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Tracking network technology satellite. Spacecraft: TTS. Decay Date: 1968-04-28 . USAF Sat Cat: 3067 . COSPAR: 1967-123B. Apogee: 490 km (300 mi). Perigee: 287 km (178 mi). Inclination: 32.90 deg. Period: 92.20 min. Test and Training Satellite; tested Apollo tracking network. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1968 January 11 - . 16:16 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta E1.

Explorer 36 - . Payload: GEOS B. Mass: 209 kg (460 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Astronomy. Type: Solar satellite. Spacecraft: GEOS. USAF Sat Cat: 3093 . COSPAR: 1968-002A. Apogee: 1,574 km (978 mi). Perigee: 1,081 km (671 mi). Inclination: 105.80 deg. Period: 112.20 min.
The geodetic instrumentation systems included (1) four optical beacons, (2) two C-band radar transponders, (3) a passive radar reflector, (4) a sequential collation of range radio range transponder, (5) a Goddard range and range rate transponder, (6) laser reflectors, and (7) Doppler beacons. Non-geodetic systems included a laser detector and a Minitrack interferometer beacon. The objectives of the spacecraft were to optimise optical station visibility periods and to provide complementary data for inclination-dependent terms established by the Explorer 29 (GEOS 1) gravimetric studies. The spacecraft was placed into a retrograde orbit to accomplish these objectives. Operational problems occurred in the main power system, optical beacon flash system, and the spacecraft clock, and adjustments in scheduling resulted in nominal operations.

1968 January 17 - . 10:12 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor SLV-2A Agena D.

OPS 1965 - . Payload: Ferret 12 / Agena D 2733. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1970-07-07 . USAF Sat Cat: 3097 . COSPAR: 1968-004A. Apogee: 536 km (333 mi). Perigee: 462 km (287 mi). Inclination: 75.10 deg. Period: 94.60 min.
The last scheduled Air Force Thrust Augmented Thor/Agena (SLV-2A //498/SS-01B #2733) to be launched from Vandenberg AFB was the 150th Thor/ Agena vehicle fired from there since Discoverer I was launched on 28 February 1959. From now on, the Air Force would use the more advanced Long Tank Thrust Augmented Thor (SLV-2G) - Thorad - and the newer SLV-2H.

1968 January 24 - . 22:26 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4A 1045 - . Payload: KH-4A s/n 1045 / Agena D 1640 / OPS 2243. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1968-02-27 . USAF Sat Cat: 3113 . COSPAR: 1968-008A. Apogee: 438 km (272 mi). Perigee: 179 km (111 mi). Inclination: 81.50 deg. Period: 90.70 min. KH-4A. All cameras operated satisfactorily..

OPS 6236 - . Payload: EHH B10. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1970-03-04 . USAF Sat Cat: 3114 . COSPAR: 1968-008B. Apogee: 545 km (338 mi). Perigee: 470 km (290 mi). Inclination: 81.70 deg. Period: 94.70 min. Radar monitoring..

SRV 741 - . Payload: SRV 1045-1. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1970-03-04 . USAF Sat Cat: 3114 . COSPAR: 1968-008xx. Apogee: 186 km (115 mi). Perigee: 185 km (114 mi). Inclination: 81.60 deg. Period: 88.20 min.

1968 March 14 - . 22:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4A 1046 - . Payload: KH-4A s/n 1046 / Agena D 1638 / OPS 4849. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1968-04-10 . USAF Sat Cat: 3152 . COSPAR: 1968-020A. Apogee: 390 km (240 mi). Perigee: 183 km (113 mi). Inclination: 83.00 deg. Period: 90.20 min. KH-4A. Image quality good for 1046-1 and fair for 1046-2..

OPS 7076 - . Payload: EHH B11. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1970-01-03 . USAF Sat Cat: 3153 . COSPAR: 1968-020B. Apogee: 524 km (325 mi). Perigee: 481 km (298 mi). Inclination: 83.10 deg. Period: 94.60 min. Radar monitoring..

SRV 747 - . Payload: SRV 1046-1 / OPS 7076. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1970-01-03 . USAF Sat Cat: 3153 . COSPAR: 1968-020xx. Apogee: 189 km (117 mi). Perigee: 189 km (117 mi). Inclination: 83.00 deg. Period: 88.30 min.

1968 May 1 - . 21:31 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4B 1103 - . Payload: KH-4B s/n 1103 / OPS 1419. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1968-05-15 . USAF Sat Cat: 3228 . COSPAR: 1968-039B. Apogee: 243 km (150 mi). Perigee: 164 km (101 mi). Inclination: 83.10 deg. Period: 88.60 min. KH-4B. Out-of-focus imagery is present on both main camera records..

SRV 807 - . Payload: SRV 1103-1. Mass: 3,000 kg (6,600 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1968-05-20 . USAF Sat Cat: 3232 . COSPAR: 1968-039C. Apogee: 199 km (123 mi). Perigee: 142 km (88 mi). Inclination: 83.00 deg. Period: 87.90 min.

1968 May 14 - . 07:05 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE1. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

AFP-437 combat evaluation interceptor mission - . Nation: USA. Agency: USAF. Apogee: 823 km (511 mi).

1968 May 18 - . 08:23 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D. FAILURE: Failure. Failed Stage: U.

Nimbus B - . Mass: 570 kg (1,250 lb). Nation: USA. Agency: NASA. Class: Earth. Type: Weather satellite. Spacecraft: Nimbus. Decay Date: 1968-05-18 . Nimbus B2 meteorological satellite..

EGRS 10 - . Payload: Secor 10. Nation: USA. Agency: USAF. Spacecraft: Secor. Army-sponsored Sequential Collocation of Range (SECOR) satellite..

1968 May 23 - . 04:38 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2.

DMSP-Block-4A F11 - . Payload: DAPP 4B F-1 (FTV-8) / OPS 7869. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 4A. USAF Sat Cat: 3266 . COSPAR: 1968-042A. Apogee: 883 km (548 mi). Perigee: 806 km (500 mi). Inclination: 98.90 deg. Period: 101.80 min. Defense Meteorological Satellite Program..

1968 June 20 - . 21:46 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4A 1047 - . Payload: KH-4A s/n 1047 / Agena D 1645 / OPS 5343. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1968-07-16 . USAF Sat Cat: 3296 . COSPAR: 1968-052A. Apogee: 402 km (249 mi). Perigee: 183 km (113 mi). Inclination: 85.00 deg. Period: 90.30 min. KH-4A. Out-of-focus imagery is present on both main camera records..

OPS 5259 - . Payload: EHH B12. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1970-01-11 . USAF Sat Cat: 3297 . COSPAR: 1968-052B. Apogee: 514 km (319 mi). Perigee: 435 km (270 mi). Inclination: 85.10 deg. Period: 94.10 min. Radar monitoring..

SRV 745 - . Payload: SRV 1047-1. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1970-01-11 . USAF Sat Cat: 3297 . COSPAR: 1968-052xx. Apogee: 180 km (110 mi). Perigee: 180 km (110 mi). Inclination: 85.10 deg. Period: 88.10 min.

1968 July 4 - . 17:26 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta J.

Explorer 38 - . Payload: RAE A. Mass: 190 kg (410 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: RAE. USAF Sat Cat: 3307 . COSPAR: 1968-055A. Apogee: 5,861 km (3,641 mi). Perigee: 5,835 km (3,625 mi). Inclination: 120.90 deg. Period: 224.30 min. Radio Astronomy Explorer; Earth, solar, cosmic radio emission data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1968 August 7 - . 21:36 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4B 1104 - . Payload: KH-4B s/n 1104 / Agena D 1644 / OPS 5955. Mass: 3,000 kg (6,600 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1968-08-27 . USAF Sat Cat: 3336 . COSPAR: 1968-065A. Apogee: 259 km (160 mi). Perigee: 160 km (90 mi). Inclination: 82.10 deg. Period: 88.70 min. KH-4B. Best imagery to date on any KH-4 systems. Bicolor and color infrared experiments were conducted on this mission..

1968 August 16 - . 11:24 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta N.

ESSA 7 - . Payload: TOS E. Mass: 145 kg (319 lb). Nation: USA. Agency: ESSA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: TOS. USAF Sat Cat: 3345 . COSPAR: 1968-069A. Apogee: 1,473 km (915 mi). Perigee: 1,431 km (889 mi). Inclination: 101.90 deg. Period: 114.90 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1968 September 18 - . 21:32 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1E. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4A 1048 - . Payload: KH-4A s/n 1048 / Agena D 1647 / OPS 0165. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1968-10-08 . USAF Sat Cat: 3408 . COSPAR: 1968-078A. Apogee: 393 km (244 mi). Perigee: 167 km (103 mi). Inclination: 83.00 deg. Period: 90.10 min. KH-4A. Film in the forward camera separated and camera failed on mission 1048-2, also the stellar/index camera unit failed..

OPS 8595 - . Payload: EHH B13. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1969-09-28 . USAF Sat Cat: 3409 . COSPAR: 1968-078B. Apogee: 514 km (319 mi). Perigee: 500 km (310 mi). Inclination: 83.20 deg. Period: 94.80 min. Radar monitoring..

SRV 749 - . Payload: SRV 1048-1. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1969-09-28 . USAF Sat Cat: 3409 . COSPAR: 1968-078xx. Apogee: 236 km (146 mi). Perigee: 211 km (131 mi). Inclination: 83.20 deg. Period: 89.00 min.

1968 September 19 - . 00:09 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta M. FAILURE: Control system failure; destroyed by range safety.. Failed Stage: G.

Intelsat-3 F-1 - . Mass: 293 kg (645 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Decay Date: 1968-09-18 .

1968 October 5 - . 11:16 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

OPS 0964 - . Payload: Ferret 13 / Agena D 2734. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1971-03-26 . USAF Sat Cat: 3472 . COSPAR: 1968-086A. Apogee: 511 km (317 mi). Perigee: 483 km (300 mi). Inclination: 75.00 deg. Period: 94.60 min.

1968 October 23 - . 04:34 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2.

DMSP-Block-4A F12 - . Payload: DAPP 6422 (FTV-7) / OPS 4078. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 4A. USAF Sat Cat: 3510 . COSPAR: 1968-092A. Apogee: 828 km (514 mi). Perigee: 783 km (486 mi). Inclination: 98.70 deg. Period: 101.00 min. Defense Meteorological Satellite Program..

1968 November 3 - . 21:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4B 1105 - . Payload: KH-4B s/n 1105 / Agena D 1646 / OPS 1315. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1968-11-23 . USAF Sat Cat: 3531 . COSPAR: 1968-098A. Apogee: 288 km (178 mi). Perigee: 150 km (90 mi). Inclination: 82.20 deg. Period: 88.90 min. KH-4B. Image quality is variable and displays areas of soft focus and image smear..

1968 November 8 - . 09:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta E1.

Pioneer 9 - . Payload: Pioneer D / TTS 2. Mass: 63 kg (138 lb). Nation: USA. Agency: NASA Ames. Program: Pioneer. Class: Astronomy. Type: Solar satellite. Spacecraft: Pioneer 6-7-8-9-E. USAF Sat Cat: 3533 . COSPAR: 1968-100A. Solar radiation data. Solar Orbit (Heliocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

TTS 2; TATS 2 (TETR 2) - . Payload: TETR 2. Mass: 40 kg (88 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Tracking network technology satellite. Spacecraft: TTS. Decay Date: 1979-09-19 . USAF Sat Cat: 3534 . COSPAR: 1968-100B. Apogee: 945 km (587 mi). Perigee: 375 km (233 mi). Inclination: 32.90 deg. Period: 98.00 min. Test and Training Satellite; test vehicle for NASA Manned Space Flight Network. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1968 November 20 - . 07:08 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE1. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

AFP-437 combat evaluation interceptor mission - . Nation: USA. Agency: USAF. Apogee: 1,158 km (719 mi).

1968 December 5 - . 18:55 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta E1.

HEOS 1 - . Payload: HEOS A1. Mass: 108 kg (238 lb). Nation: Europe. Agency: ESRO. Class: Earth. Type: Magnetosphere satellite. Spacecraft: HEOS. Decay Date: 1975-10-28 . USAF Sat Cat: 3595 . COSPAR: 1968-109A. Apogee: 202,780 km (126,000 mi). Perigee: 20,020 km (12,430 mi). Inclination: 60.50 deg. Period: 6,704.30 min. Highly Eccentric Orbiting Satellite; examined magnetic fields outside of Earth's magnetosphere. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1968 December 12 - . 22:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4A 1049 - . Payload: KH-4A s/n 1049 / Agena D 1648 / OPS 4740. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1968-12-28 . USAF Sat Cat: 3604 . COSPAR: 1968-112A. Apogee: 248 km (154 mi). Perigee: 169 km (105 mi). Inclination: 81.00 deg. Period: 88.70 min. KH-4A. Degraded film.

OPS 7684 - . Payload: EHH C1 / OPS 7684. Mass: 60 kg (132 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. USAF Sat Cat: 3605 . COSPAR: 1968-112B. Apogee: 1,466 km (910 mi). Perigee: 1,378 km (856 mi). Inclination: 80.40 deg. Period: 114.30 min. ABM monitoring..

SRV 751 - . Payload: SRV 1049-1. Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A. COSPAR: 1968-112xx. Apogee: 248 km (154 mi). Perigee: 169 km (105 mi). Inclination: 81.00 deg. Period: 88.70 min.

1968 December 15 - . 17:21 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta N.

ESSA 8 - . Payload: TOS F. Mass: 132 kg (291 lb). Nation: USA. Agency: ESSA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: TOS. USAF Sat Cat: 3615 . COSPAR: 1968-114A. Apogee: 1,464 km (909 mi). Perigee: 1,414 km (878 mi). Inclination: 102.00 deg. Period: 114.60 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1968 December 19 - . 00:32 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta M.

Intelsat 3 F-2 - . Mass: 293 kg (645 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Completed Operations Date: 1977-01-25 . USAF Sat Cat: 3623 . COSPAR: 1968-116A. Apogee: 37,111 km (23,059 mi). Perigee: 35,984 km (22,359 mi). Inclination: 15.10 deg. Period: 1,475.20 min.
Over Brazil. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 24 deg W in 1969-1970. As of 3 September 2001 located at 96.04 deg E drifting at 9.557 deg W per day. As of 2007 Mar 9 located at 48.04W drifting at 9.553W degrees per day.

1969 January 22 - . 16:48 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta C1.

OSO 5 - . Payload: OSO F. Mass: 291 kg (641 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: Solar satellite. Spacecraft: OSO. Decay Date: 1984-04-02 . USAF Sat Cat: 3663 . COSPAR: 1969-006A. Apogee: 559 km (347 mi). Perigee: 538 km (334 mi). Inclination: 33.00 deg. Period: 95.60 min. Orbiting Solar Observatory; solar radiation data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1969 January 30 - . 06:46 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta E1.

Isis 1 - . Payload: Isis A. Mass: 241 kg (531 lb). Nation: Canada. Agency: CRCSS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Isis. USAF Sat Cat: 3669 . COSPAR: 1969-009A. Apogee: 3,458 km (2,148 mi). Perigee: 578 km (359 mi). Inclination: 88.40 deg. Period: 127.60 min. Ionospheric measurements; data correlated with measurements from Alouette 1. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1969 February 5 - . 21:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4B 1106 - . Payload: KH-4B s/n 1106 / Agena D 1650 / OPS 3890. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1969-02-24 . USAF Sat Cat: 3672 . COSPAR: 1969-010A. Apogee: 275 km (170 mi). Perigee: 147 km (91 mi). Inclination: 81.60 deg. Period: 88.70 min. KH-4B. The best image quality to date..

SRV 801R - . Payload: SRV 1106-1. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4B. COSPAR: 1969-010xx. Apogee: 275 km (170 mi). Perigee: 147 km (91 mi). Inclination: 81.60 deg. Period: 88.70 min.

OPS 2644 - . Payload: EHH C2 / OPS 2644. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. USAF Sat Cat: 3673 . COSPAR: 1969-010B. Apogee: 1,429 km (887 mi). Perigee: 1,391 km (864 mi). Inclination: 80.40 deg. Period: 114.00 min. ABM monitoring..

1969 February 6 - . 00:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta M.

Intelsat 3 F-3 - . Mass: 293 kg (645 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Completed Operations Date: 1979-12-13 . USAF Sat Cat: 3674 . COSPAR: 1969-011A. Apogee: 35,803 km (22,246 mi). Perigee: 35,767 km (22,224 mi). Inclination: 6.10 deg. Period: 1,436.00 min.
Stationed at 63 deg E. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 174 deg E in 1969; over the Indian Ocean 062 deg E in 1969-1975. Last known longitude (24 May 1979) 66.72 deg E drifting at 0.017 deg E per day.

1969 February 26 - . 07:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Thor Delta E1.

ESSA 9 - . Payload: TOS G. Mass: 145 kg (319 lb). Nation: USA. Agency: ESSA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: TOS. USAF Sat Cat: 3764 . COSPAR: 1969-016A. Apogee: 1,505 km (935 mi). Perigee: 1,425 km (885 mi). Inclination: 101.80 deg. Period: 115.20 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1969 March 19 - . 21:38 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4A 1050 - . Payload: KH-4A s/n 1050 / Agena D 1651 / OPS 3722. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1969-03-24 . USAF Sat Cat: 3829 . COSPAR: 1969-026A. Apogee: 252 km (156 mi). Perigee: 165 km (102 mi). Inclination: 82.90 deg. Period: 88.60 min. KH-4A. Due to abnormal rotational rates after revolution 22, the mission was terminated after a total of three days collecting photography..

SRV 737 - . Payload: SRV 1050-1. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1971-12-06 . USAF Sat Cat: 3830 . COSPAR: 1969-026xx. Apogee: 168 km (104 mi). Perigee: 168 km (104 mi). Inclination: 83.00 deg. Period: 87.90 min.

OPS 2285 - . Payload: EHH B14. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1971-12-06 . USAF Sat Cat: 3830 . COSPAR: 1969-026B. Apogee: 515 km (320 mi). Perigee: 502 km (311 mi). Inclination: 83.10 deg. Period: 94.70 min. Radar monitoring..

1969 April 14 - . 07:54 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

Nimbus 3 - . Payload: Nimbus B2. Mass: 575 kg (1,267 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Weather satellite. Spacecraft: Nimbus. USAF Sat Cat: 3890 . COSPAR: 1969-037A. Apogee: 1,130 km (700 mi). Perigee: 1,071 km (665 mi). Inclination: 100.40 deg. Period: 107.30 min.
Primary experiments consisted of a satellite infrared spectrometer (SIRS) for determining the vertical temperature profiles of the atmosphere, an infrared interferometer spectrometer (IRIS) for measuring the emission spectra of the earth-atmosphere system, both high- and medium-resolution infrared radiometers (HRIR and MRIR) for yielding information on the distribution and intensity of infrared radiation emitted and reflected by the earth and its atmosphere, monitor of ultraviolet solar energy (MUSE) for detecting solar UV radiation, image dissector camera system for providing daytime cloudcover pictures in both real-time mode using the real time transmission system and tape recorder mode using the high data rate storage system, radioisotope thermoelectric generator (RTG) SNAP-19 to assess the operational capability of radioisotope power for space applications, and an interrogation, recording and location system (IRLS) experiment designed to locate, interrogate, record, and retransmit meteorological and geophysical data from remote collection stations. Nimbus-3 was successful and performed normally until July 22, 1969, when the IRIS experiment failed. The HRIR and the SIRS experiments were terminated on January 25, 1970, and June 21, 1970, respectively. The remaining experiments continued operation until September 25, 1970, when the rear horizon scanner failed. Without this horizon scanner, it was impossible to maintain proper spacecraft attitude, thus making most experimental observations useless. All spacecraft operations were terminated on January 22, 1972.

SECOR 13 - . Payload: EGRS 13. Mass: 20 kg (44 lb). Nation: USA. Agency: USA ACE. Class: Earth. Type: Geodetic satellite. Spacecraft: SECOR. USAF Sat Cat: 3891 . COSPAR: 1969-037B. Apogee: 1,129 km (701 mi). Perigee: 1,070 km (660 mi). Inclination: 100.30 deg. Period: 107.30 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1969 May - . LV Family: Thor.

Thor (SLV-2K) space booster begins development. - . SAMSO initiated development of the universal boattail Thor (SLV-2K) space booster for NASA. The new booster would provide a Thor with the capability to use three, six, or nine strap-ons boosters..

1969 May 2 - . 01:46 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4A 1051 - . Payload: KH-4A s/n 1051 / Agena D 1649 / OPS 1101. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1969-05-23 . USAF Sat Cat: 3914 . COSPAR: 1969-041A. Apogee: 325 km (201 mi). Perigee: 168 km (104 mi). Inclination: 64.90 deg. Period: 89.50 min. KH-4A. Imagery of both pan camera records is soft and lacks crispness and edge sharpness..

SRV 739 - . Payload: SRV 1051-1. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1970-02-16 . USAF Sat Cat: 3915 . COSPAR: 1969-041xx. Apogee: 193 km (119 mi). Perigee: 177 km (109 mi). Inclination: 65.70 deg. Period: 88.20 min.

OPS 1721 - . Payload: EHH B15. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1970-02-16 . USAF Sat Cat: 3915 . COSPAR: 1969-041B. Apogee: 470 km (290 mi). Perigee: 407 km (252 mi). Inclination: 65.70 deg. Period: 93.30 min. Radar monitoring..

1969 May 22 - . 02:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta M.

Intelsat 3 F-4 - . Mass: 293 kg (645 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Completed Operations Date: 1977-05-13 . USAF Sat Cat: 3947 . COSPAR: 1969-045A. Apogee: 39,752 km (24,700 mi). Perigee: 39,486 km (24,535 mi). Inclination: 6.10 deg. Period: 1,636.30 min.
Positioned in geosynchronous orbit over the Pacific Ocean at 175 deg E in 1969-1972; ? 1972-1977; over the Pacific Ocean 166 deg W in 1977. Last known longitude (20 May 1977) 161.73 deg E drifting at 44.175 deg W per day.Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1969 June 5 - . 14:42 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thorad SLV-2H Agena D.

OGO 6 - . Payload: OGO F. Mass: 634 kg (1,397 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Magnetosphere satellite. Spacecraft: OGO. Decay Date: 1979-10-12 . USAF Sat Cat: 3986 . COSPAR: 1969-051A. Apogee: 1,089 km (676 mi). Perigee: 397 km (246 mi). Inclination: 82.00 deg. Period: 99.70 min.
OGO 6 was a large observatory instrumented with 26 experiments designed to study the various interrelationships between, and latitudinal distributions of, high-altitude atmospheric parameters during a period of increased solar activity. On June 22, 1969, the spacecraft potential dropped significantly during sunlight operation and remained so during subsequent sunlight operation. This unexplained shift affected seven experiments which made measurements dependent upon knowledge of the spacecraft plasma sheath. During October 1969, a string of solar cells failed, but the only effect of the decreased power was to cause two experiments to change their mode of operation. Also during October 1969, a combination of manual and automatic attitude control was initiated, which extended the control gas lifetime of the attitude control system. In August 1970, tape recorder (TR) no. 1 operation degraded, so all recorded data were subsequently taken with TR no. 2. By September 1970, power and equipment degradation left 14 experiments operating normally, 3 partially, and 9 off. From October 14, 1970, TR no. 2 was used only on Wednesdays (world days) to conserve power and extend TR operation. In June 1971, the number of 'on' experiments decreased from 13 to 7, and on June 28, 1971, the spacecraft was placed in a spin-stabilized mode about the yaw (Z) axis and turned off due to difficulties with spacecraft power. OGO 6 was turned on again from October 10, 1971, through March 1972, for operation of experiment 25 by The Radio Research Laboratory, Japan.

1969 June 21 - . 08:47 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor Delta E1.

Explorer 41 - . Payload: IMP G. Mass: 174 kg (383 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Magnetosphere satellite. Spacecraft: IMP. Decay Date: 1972-12-23 . USAF Sat Cat: 3990 . COSPAR: 1969-053A. Apogee: 98,159 km (60,993 mi). Perigee: 80,374 km (49,941 mi). Inclination: 86.00 deg. Period: 4,906.30 min. Cislunar radiation data. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1969 June 29 - . 03:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta N.

Biosatellite 3 - . Payload: Biosat 3. Mass: 695 kg (1,532 lb). Nation: USA. Agency: NASA Ames. Class: Biology. Type: Biology satellite. Spacecraft: Biosatellite. Decay Date: 1970-01-20 . USAF Sat Cat: 4000 . COSPAR: 1969-056A. Apogee: 374 km (232 mi). Perigee: 363 km (225 mi). Inclination: 33.50 deg. Period: 92.00 min.
Biological capsule reentered 7/7/69. The intent had been to fly a 6 kg male pig-tailed monkey (Macaca nemestrina) named Bonnie in Earth-orbit for 30 days. However, after only 8.8 days in orbit, the mission was terminated because of the subject's deteriorating health. High development costs were a strong incentive for maximising the scientific return from the mission. Because of this, the scientific goals had become exceedingly ambitious over time, and a great many measurements were conducted on the single research subject flown. Although the mission was highly successful from a technical standpoint, the science results were apparently compromised. Additional Details: here....

1969 July 23 - . 04:39 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2.

DMSP-Block-4A F13 - . Payload: DAPP 7421 (FTV-6) / OPS 1127. Mass: 130 kg (280 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 4A. USAF Sat Cat: 4047 . COSPAR: 1969-062A. Apogee: 835 km (518 mi). Perigee: 768 km (477 mi). Inclination: 98.80 deg. Period: 100.90 min. Defense Meteorological Satellite Program..

1969 July 24 - . 01:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2H Agena D.

KH-4B 1107 - . Payload: KH-4B s/n 1107 / Agena D 1652 / OPS 3654. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1969-08-23 . USAF Sat Cat: 4050 . COSPAR: 1969-063A. Apogee: 203 km (126 mi). Perigee: 182 km (113 mi). Inclination: 74.90 deg. Period: 88.40 min. KH-4B. Forward camera failed on pass 1 and remained inoperative throughout the rest of the mission..

1969 July 26 - . 02:06 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta M. FAILURE: Third stage failure; left in unusable orbit.. Failed Stage: 3.

Intelsat 3 F-5 - . Mass: 269 kg (593 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Decay Date: 1988-10-14 . USAF Sat Cat: 4051 . COSPAR: 1969-064A. Apogee: 433 km (269 mi). Perigee: 211 km (131 mi). Inclination: 30.20 deg. Period: 91.00 min. Third stage failure; left in unusable orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1969 July 31 - . 10:19 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

OPS 8285 - . Payload: Ferret 14 / Agena D 2735. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1973-01-04 . USAF Sat Cat: 4054 . COSPAR: 1969-065A. Apogee: 536 km (333 mi). Perigee: 465 km (288 mi). Inclination: 75.00 deg. Period: 94.60 min.

1969 August 9 - . 07:52 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta N.

OSO 6 - . Payload: OSO G. Mass: 290 kg (630 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: Solar satellite. Spacecraft: OSO. Decay Date: 1981-03-07 . USAF Sat Cat: 4065 . COSPAR: 1969-068A. Apogee: 554 km (344 mi). Perigee: 489 km (303 mi). Inclination: 32.90 deg. Period: 95.10 min. Orbiting Solar Observatory; solar physics experiments. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

PAC 1 - . Mass: 120 kg (260 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Navigation technology satellite. Spacecraft: PAC. Decay Date: 1977-04-28 . USAF Sat Cat: 4066 . COSPAR: 1969-068B. Apogee: 552 km (342 mi). Perigee: 486 km (301 mi). Inclination: 32.90 deg. Period: 95.00 min. Package Attitude Control; semi-active gravity gradient stabilization tests. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1969 August 27 - . 21:59 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta L. FAILURE: First stage hydraulics failure. Vehicle destructed at T+383 seconds. Failed Stage: 1.

Pioneer E - . Payload: Pioneer E. Mass: 67 kg (147 lb). Nation: USA. Agency: NASA. Program: Pioneer. Class: Astronomy. Type: Solar satellite. Spacecraft: Pioneer 6-7-8-9-E. Decay Date: 1969-08-27 .

TETR C - . Payload: TETR C. Mass: 20 kg (44 lb). Nation: USA. Agency: NASA. Program: Pioneer. Spacecraft: TETR.

1969 September 22 - . 21:11 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

KH-4A 1052 - . Payload: KH-4A s/n 1052 / Agena D 1653 / OPS 3531. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1969-10-12 . USAF Sat Cat: 4102 . COSPAR: 1969-079A. Apogee: 253 km (157 mi). Perigee: 178 km (110 mi). Inclination: 85.00 deg. Period: 88.80 min. KH-4A. Last of the KH-4A missions, all camera systems operated satisfactorily..

SRV 743R - . Payload: SRV 1052-1. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1971-05-16 . USAF Sat Cat: 4103 . COSPAR: 1969-079xx. Apogee: 211 km (131 mi). Perigee: 211 km (131 mi). Inclination: 85.10 deg. Period: 88.70 min.

OPS 4710 - . Payload: EHH B16. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4A. Decay Date: 1971-05-16 . USAF Sat Cat: 4103 . COSPAR: 1969-079B. Apogee: 496 km (308 mi). Perigee: 490 km (300 mi). Inclination: 85.20 deg. Period: 94.50 min. Radar monitoring. Last of the KH-4A missions..

1969 September 30 - . 13:40 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

OPS 1807 - . Payload: EHH B17. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1970-10-30 . USAF Sat Cat: 4111 . COSPAR: 1969-082A. Apogee: 484 km (300 mi). Perigee: 446 km (277 mi). Inclination: 69.60 deg. Period: 93.90 min.

Surcal - . Payload: NRL PL176 / OPS 7613 P/L 1. Nation: USA. Agency: NRL. Class: Surveillance. Type: Radar calibration target. Spacecraft: Surcal. USAF Sat Cat: 4256 . COSPAR: 1969-082B. Apogee: 918 km (570 mi). Perigee: 893 km (554 mi). Inclination: 70.00 deg. Period: 103.10 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

SOICAL Cone - . Payload: S69-4 Cone. Nation: USA. Agency: NRL. Class: Surveillance. Type: Radar calibration target. Spacecraft: SOICAL. USAF Sat Cat: 4132 . COSPAR: 1969-082K. Apogee: 870 km (540 mi). Perigee: 844 km (524 mi). Inclination: 70.00 deg. Period: 102.10 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

SOICAL Cylinder - . Payload: S69-4 Cylinder. Nation: USA. Agency: NRL. Class: Surveillance. Type: Radar calibration target. Spacecraft: SOICAL. USAF Sat Cat: 4166 . COSPAR: 1969-082J. Apogee: 812 km (504 mi). Perigee: 791 km (491 mi). Inclination: 70.00 deg. Period: 100.90 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

Tempsat 2 - . Mass: 9.00 kg (19.80 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Radar calibration target. Spacecraft: Tempsat. USAF Sat Cat: 4168 . COSPAR: 1969-082H. Apogee: 924 km (574 mi). Perigee: 899 km (558 mi). Inclination: 70.00 deg. Period: 103.20 min. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

Surcal - . Payload: NRL PL164 / OPS 7613 / Poppy 6D (Poppy multifacete. Mass: 40 kg (88 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 4295 . COSPAR: 1969-082G. Apogee: 926 km (575 mi). Perigee: 899 km (558 mi). Inclination: 70.00 deg. Period: 103.30 min. Poppy naval signals intelligence satellite..

Timation 2 - . Mass: 700 kg (1,540 lb). Nation: USA. Agency: NRL. Program: Navstar. Class: Technology. Type: Navigation technology satellite. Spacecraft: Timation. USAF Sat Cat: 4257 . COSPAR: 1969-082C. Apogee: 925 km (574 mi). Perigee: 898 km (557 mi). Inclination: 70.00 deg. Period: 103.20 min. Navigation experiments leading eventually to Navstar/GPS system. Operated for 6 years..

Surcal - . Payload: NRL PL161 / OPS 7613 / Poppy 6A (Poppy multifacet. Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 4259 . COSPAR: 1969-082D. Apogee: 928 km (576 mi). Perigee: 899 km (558 mi). Inclination: 70.00 deg. Period: 103.30 min. Launch of a quadruplet of Poppy naval signals intelligence satellites. Official and secondary mission: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

Surcal - . Payload: NRL PL162 / OPS 7613 / Poppy 6B (Poppy multifacet. Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 4237 . COSPAR: 1969-082E. Apogee: 925 km (574 mi). Perigee: 899 km (558 mi). Inclination: 70.00 deg. Period: 103.30 min. Poppy naval signals intelligence satellite. Official and secondary mission:Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

Surcal - . Payload: NRL PL163 / OPS 7613 / Poppy 6C (Poppy multifacete. Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 4247 . COSPAR: 1969-082F. Apogee: 925 km (574 mi). Perigee: 898 km (557 mi). Inclination: 70.00 deg. Period: 103.20 min. Poppy naval signals intelligence satellite. Official and secondary mission: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

1969 November 22 - . 00:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta M.

Skynet 1A - . Mass: 243 kg (535 lb). Nation: UK. Agency: MoD. Program: Skynet. Class: Communications. Type: Military communications satellite. Spacecraft Bus: Skynet. Spacecraft: NATO 1. Completed Operations Date: 1980-01-01 . USAF Sat Cat: 4250 . COSPAR: 1969-101A. Apogee: 35,894 km (22,303 mi). Perigee: 35,682 km (22,171 mi). Inclination: 13.90 deg. Period: 1,436.20 min.
Skynet IA, the first of two Skynet military communications satellite built for the United Kingdom by the Philco-Ford Corporation, was launched from Cape Canaveral aboard a NASA Long Tank Thrust Augmented Thor/Delta (DSV-3L). The satellite was turned over to the United Kingdom on 30 January 1970, providing the United Kingdom with its first operational military communications satellite system. The Skynet satellites were designed to be usable with the Initial Defense Satellite Communication System (IDSCS) satellites of the United States. Over Indian Ocean. Military communications. Previously registered by the United States in A/AC.105/INF.220: 1969-101A, orbital data 276 x 36716 km x 28.0 deg, category C. Positioned in geosynchronous orbit over the Indian Ocean at 41 deg E in 1969-1972?; ??? 1972-1977; over the Americas at 100-110 deg W in 1977-1998 As of 26 August 2001 located at 104.51 deg W drifting at 0.015 deg W per day. As of 2007 Mar 9 located at 106.94W drifting at 0.015W degrees per day.

1969 December 4 - . 21:37 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2H Agena D.

KH-4B 1108 - . Payload: KH-4B s/n 1108 / Agena D 1655 / OPS 6617. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1970-01-10 . USAF Sat Cat: 4264 . COSPAR: 1969-105A. Apogee: 229 km (142 mi). Perigee: 161 km (100 mi). Inclination: 81.40 deg. Period: 88.40 min. KH-4B. Cameras operated satisfactorily and the mission carried 811 ft of aerial color film added to the end of the film supply..

1970 January 15 - . 00:16 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta M.

Intelsat 3 F-6 - . Mass: 293 kg (645 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Completed Operations Date: 1977-05-13 . USAF Sat Cat: 4297 . COSPAR: 1970-003A. Apogee: 36,126 km (22,447 mi). Perigee: 36,079 km (22,418 mi). Inclination: 14.30 deg. Period: 1,452.30 min.
Stationed at 336 deg E. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 25 deg W in 1970; over the Atlantic Ocean 30 deg W in 1970-1971; over the Atlantic Ocean 20 deg W in 1971 Apr-1972 Mar; over the Indian Ocean 64 deg E in 1972-1974; over the Pacific Ocean 177 deg W in 1975 As of 5 September 2001 located at 163.49 deg E drifting at 4.024 deg W per day. As of 2007 Feb 27 located at 47.49E drifting at 4.027W degrees per day.

1970 January 23 - . 11:31 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor Delta N6.

ITOS 1 - . Payload: Tiros M. Mass: 309 kg (681 lb). Nation: USA. Agency: NOAA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: ITOS. USAF Sat Cat: 4320 . COSPAR: 1970-008A. Apogee: 1,479 km (919 mi). Perigee: 1,434 km (891 mi). Inclination: 101.80 deg. Period: 115.00 min.
NASA successfully launched the Improved Tiros Operational Satellite (ITOS I) (TIROS-M) from Vandenberg AFB aboard a two-stage, Long Tank Thrust Augmented Thor/Delta (SLV-2K), Thorad/Delta, using six solid-propellaiit, strap-on Thiokol TX 354-5 Castor II motors. This was the first use of the "Super Six" Thor/Delta (DSV-3N-6) booster vehicle that employed the six Castor II motors, three of which ignited 30 seconds after lift-off. Generating nearly 600,000 pounds of thrust, the new launch vehicle could orbit a spacecraft weighing more than twice as much as the previous Tiros Operational Satellites. Improved TIROS Operational Satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

Oscar 5 - . Payload: Australis-Oscar 5. Mass: 18 kg (39 lb). Nation: Australia. Agency: Clemson. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Oscar. USAF Sat Cat: 4321 . COSPAR: 1970-008B. Apogee: 1,478 km (918 mi). Perigee: 1,434 km (891 mi). Inclination: 101.80 deg. Period: 115.00 min.
Australis-OSCAR 5 was launched piggyback with ITOS-1 (TIROS-M weather satellite. Weight 17.7 kg (9 kg of which was battery mass). Box shaped 304 x 431 x 152 mm. 2 meter monopole and 10 meter dipole antennas. It was the first amateur satellite to be remotely controlled. Built by students at The University of Melbourne, Melbourne, Victoria, Australia. Battery powered, Australis-OSCAR 5 transmitted telemetry on both 2 meter (144.050 MHz at 50 mW) and 10 meter (29.450 MHz at 250 mW) bands that operated for 23 and 46 days respectively. Passive magnetic attitude stabilization was performed by carrying two bar magnets to align with the Earth's magnetic field in order to provide a favorable antenna footprint. The University of Melbourne compiled tracking reports from hundreds of stations in 27 countries.

1970 February 4 - . 02:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

SERT 2 - . Mass: 1,404 kg (3,095 lb). Nation: USA. Agency: NASA Cleveland. Class: Technology. Type: Ion engine technology satellite. Spacecraft: SERT. USAF Sat Cat: 4327 . COSPAR: 1970-009A. Apogee: 1,046 km (649 mi). Perigee: 1,039 km (645 mi). Inclination: 99.20 deg. Period: 106.00 min.
Space Electric Rocket Test; the ion engines aboard were operated until 1981. The SERT 2 development program started in 1966 and included thruster ground tests of 6742 hours and 5169 hours duration. A prototype version of the SERT 2 spacecraft was ground-tested for a period of 2400 hours with an operating ion engine. In addition to diagnostic equipment and related ion engine hardware, the spacecraft had two identical 15 cm diameter, mercury ion engines. Flight objectives included in-space operation for a period of 6 months, measurement of thrust, and demonstration of electromagnetic compatibility. The thruster maximum power level was 0.85 kW, and this provided operation at a 28 mN thrust level at 4200 s specific impulse. Flight data were obtained from 1970 to 1981 with an ion engine operating intermittently in one of three different modes, namely, HV ion extraction, discharge chamber operation only, or just neutralizer operation. Major results were that two mercury engines thrusted for periods of 3781 hours and 2011 hours. Test duration was limited due to shorts in the ion optical system. Thrust measured in space and on the ground agreed within the measurement uncertainties. Up to 300 thruster restarts were demonstrated. One power-processing unit accumulated nearly 17,900 hours during the course of the mission. Additionally, the ion propulsion system was electromagnetically compatible with all other spacecraft systems.

1970 February 11 - . 08:40 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2.

DMSP-Block-5A F1 - . Payload: DAPP 1524 / OPS 0054. Mass: 195 kg (429 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 5A. USAF Sat Cat: 4331 . COSPAR: 1970-012A. Apogee: 840 km (520 mi). Perigee: 749 km (465 mi). Inclination: 98.80 deg. Period: 100.80 min. Defense Meteorological Satellite Program..

1970 March 4 - . 22:15 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2H Agena D.

KH-4B 1109 - . Payload: KH-4B s/n 1109 / Agena D 1657 / OPS 0440. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1970-03-26 . USAF Sat Cat: 4342 . COSPAR: 1970-016A. Apogee: 257 km (159 mi). Perigee: 167 km (103 mi). Inclination: 88.00 deg. Period: 88.80 min. KH-4B. Cameras operated satisfactorily but the overall image quality of both the forward and aft records is variable..

OPS 3402 - . Payload: EHH B18. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1971-11-10 . USAF Sat Cat: 4343 . COSPAR: 1970-016B. Apogee: 509 km (316 mi). Perigee: 441 km (274 mi). Inclination: 88.10 deg. Period: 94.10 min. Radar monitoring; may or may not have existed!!!.

SRV 819 - . Payload: SRV 1109-1. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1971-11-10 . USAF Sat Cat: 4343 . COSPAR: 1970-016xx. Apogee: 164 km (101 mi). Perigee: 164 km (101 mi). Inclination: 88.10 deg. Period: 87.80 min.

1970 March 20 - . 23:52 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta M.

NATO 1 - . Payload: NATO IIA. Mass: 243 kg (535 lb). Nation: NATO. Agency: NATO. Program: NATO. Class: Communications. Type: Military communications satellite. Spacecraft Bus: Skynet. Spacecraft: NATO 1. Completed Operations Date: 1977-01-01 . USAF Sat Cat: 4353 . COSPAR: 1970-021A. Apogee: 35,801 km (22,245 mi). Perigee: 35,768 km (22,225 mi). Inclination: 13.40 deg. Period: 1,436.00 min.
The first of two communications satellites built for the North Atlantic Treaty Organization (NATO) by the Philco-Ford Corporation under a SAMSO contract was launched from Cape Canaveral aboard a NASA Long Tank Thrust Augmented Thor/ Delta booster. Inserted into synchronous orbit on 23 March, the satellite was turned over to the Supreme Headquarters Allied Forces Europe (SHAFE) on 19 May. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 18 deg W in 1970-1972; over the Americas at 100-110 deg W in 1977-1998 As of 3 September 2001 located at 101.97 deg W drifting at 0.023 deg E per day. As of 2007 Mar 9 located at 100.55W drifting at 0.016W degrees per day.

1970 March 27 - . 07:37 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE1. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

AFP-437 Interceptor mission - . Nation: USA. Agency: USAF. Apogee: 1,074 km (667 mi).

1970 April 8 - . 08:17 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

Nimbus 4 - . Payload: Nimbus D. Mass: 620 kg (1,360 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Weather satellite. Spacecraft: Nimbus. USAF Sat Cat: 4362 . COSPAR: 1970-025A. Apogee: 1,099 km (682 mi). Perigee: 1,088 km (676 mi). Inclination: 100.10 deg. Period: 107.10 min.
A Long Tank Thrust Augmented Thor/Agena D space booster lifted NASA's Nimbus 4 meteorological satellite into orbit from Vandenberg. This was the 400th launch.. of the Thor booster that was originally developed by the Air Force as an intermediate range ballistic missile (IRBM) in the 1950s. Environmental research. Primary experiments consisted of an image dissector camera system for providing daytime cloudcover pictures both in real-time and recorded modes, temperature-humidity infrared radiometer (THIR) for measuring daytime and nighttime surface and cloudtop temperatures as well as the water vapor content of the upper atmosphere, infrared interferometer spectrometer (IRIS) for measuring the emission spectra of the earth/atmosphere system, satellite infrared spectrometer (SIRS) for determining the vertical profiles of temperature and water vapor in the atmosphere, a monitor of ultraviolet solar energy (MUSE) for detecting solar UV radiation, a backscatter ultraviolet (BUV) detector for monitoring the vertical distribution and total amount of atmospheric ozone on a global scale, a filter wedge spectrometer (FWS) for accurate measurement of IR radiance as a function of wavelength from the earth/atmosphere system, a selective chopper radiometer (SCR) for determining the temperatures of six successive 10-km layers in the atmosphere from absorption measurements in the 15-micrometer CO2 band, and an interrogation, recording, and location system (IRLS) for locating, interrogating, recording, and retransmitting meteorological and geophysical data from remote collection stations. The spacecraft performed well until April 14, 1971, when attitude problems started. The experiments then operated on a limited time basis until September 30, 1980.

TOPO 1 - . Payload: Topo A. Mass: 18 kg (39 lb). Nation: USA. Agency: USA TOPO. Class: Earth. Type: Geodetic satellite. Spacecraft: TOPO. USAF Sat Cat: 4363 . COSPAR: 1970-025B. Apogee: 1,087 km (675 mi). Perigee: 1,084 km (673 mi). Inclination: 100.00 deg. Period: 107.00 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1970 April 23 - . 00:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta M.

Intelsat 3 F-7 - . Mass: 293 kg (645 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Completed Operations Date: 1972-05-01 . USAF Sat Cat: 4376 . COSPAR: 1970-032A. Apogee: 35,791 km (22,239 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.90 deg. Period: 1,435.90 min.
Stationed at 341 deg E. Positioned in geosynchronous orbit over the Atlantic Ocean at 19 deg W in 1970-1971 Last known longitude (1 January 1972) L 139.45 deg E drifting at 0.022 deg E per day. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1970 April 24 - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Thor. Launch Vehicle: Thor DSV-2J. FAILURE: Failure. Failed Stage: 4.

SDP test - . Nation: USA. Agency: USAF. Apogee: 500 km (310 mi). ASAT test, Thor collided with satellite.

1970 May 20 - . 21:35 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2H Agena D.

KH-4B 1110 - . Payload: KH-4B s/n 1110 / Agena D 1656 / OPS 4720. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1970-06-17 . USAF Sat Cat: 4405 . COSPAR: 1970-040A. Apogee: 247 km (153 mi). Perigee: 162 km (100 mi). Inclination: 83.00 deg. Period: 88.60 min. KH-4B. The overall image quality is less than that provided by recent missions and 2,000 feet of S0-349.

OPS 8520 - . Payload: EHH B19. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1974-03-08 . USAF Sat Cat: 4406 . COSPAR: 1970-040B. Apogee: 499 km (310 mi). Perigee: 490 km (300 mi). Inclination: 83.10 deg. Period: 94.50 min. Radar monitoring; may or may not have existed!!!..

1970 July 23 - . 01:25 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2H Agena D.

KH-4B 1111 - . Payload: KH-4B s/n 1111 / Agena D 1654 / OPS 4324. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1970-08-19 . USAF Sat Cat: 4477 . COSPAR: 1970-054A. Apogee: 379 km (235 mi). Perigee: 156 km (96 mi). Inclination: 59.90 deg. Period: 89.80 min. KH-4B. The overall image quality is good..

1970 July 23 - . 23:23 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta M.

Intelsat 3 F-8 - . Mass: 270 kg (590 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 3. Completed Operations Date: 1970-07-25 . USAF Sat Cat: 4478 . COSPAR: 1970-055A. Apogee: 36,599 km (22,741 mi). Perigee: 33,877 km (21,050 mi). Inclination: 12.10 deg. Period: 1,408.20 min.
Unusable orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). As of 28 August 2001 located at 175.58 deg E drifting at 7.155 deg E per day. As of 2007 Mar 9 located at 110.93W drifting at 7.169E degrees per day.

1970 August 19 - . 12:11 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta M.

Skynet 1B - . Mass: 243 kg (535 lb). Nation: UK. Agency: MoD. Program: Skynet. Class: Communications. Type: Military communications satellite. Spacecraft Bus: Skynet. Spacecraft: NATO 1. USAF Sat Cat: 4493 . COSPAR: 1970-062A. Apogee: 37,460 km (23,270 mi). Perigee: 278 km (172 mi). Inclination: 25.90 deg. Period: 665.40 min.
The second of two British Skynet I communication satellites (Skynet B) was launched from Cape Canaveral for U.S. Air Force and United Kingdom aboard a NASA Long Tank Thrust Augmented Thor/ Delta (DSV-3M) space booster. The spacecraft was placed in a transfer orbit prior to firing of the apogee kick motor that was to put it into a synchronous orbit over Kenya. Contact with Skynet B was lost during the firing of the apogee kick motor on 22 August and was not regained. The Skynet I satellites were part of the Initial Defense Satellite Communication System (TDSCS) program which was managed for the United Kingdom by SAMSO, with NASA providing launch vehicles and services. AKM failure left in unusable orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1970 August 26 - . 10:01 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

OPS 8329 - . Payload: Ferret 15. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1975-03-26 . USAF Sat Cat: 4503 . COSPAR: 1970-066A. Apogee: 499 km (310 mi). Perigee: 496 km (308 mi). Inclination: 75.00 deg. Period: 94.50 min.

1970 September 3 - . 08:39 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2.

DMSP-Block-5A F2 - . Payload: DAPP 2525 / OPS 0203. Mass: 195 kg (429 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 5A. USAF Sat Cat: 4512 . COSPAR: 1970-070A. Apogee: 837 km (520 mi). Perigee: 739 km (459 mi). Inclination: 99.00 deg. Period: 100.60 min. Defense Meteorological Satellite Program..

1970 September 24 - . 12:54 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

HAP / SXRE X-ray astronomy / test - . Nation: USA. Agency: USAF. Apogee: 500 km (310 mi).

1970 November 18 - . 21:29 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2H Agena D.

KH-4B 1112 - . Payload: KH-4B s/n 1112 / Agena D 1658 / OPS 4992. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1970-12-11 . USAF Sat Cat: 4721 . COSPAR: 1970-098A. Apogee: 227 km (141 mi). Perigee: 180 km (110 mi). Inclination: 82.90 deg. Period: 88.50 min. KH-4B. The forward camera failed on pass 104 and remained inoperative throughout the rest of the mission..

SRV 827 - . Payload: SRV 1112-1. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1977-09-14 . USAF Sat Cat: 4722 . COSPAR: 1970-098xx. Apogee: 206 km (128 mi). Perigee: 195 km (121 mi). Inclination: 83.20 deg. Period: 88.50 min.

OPS 6829 - . Payload: EHH B20. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1977-09-14 . USAF Sat Cat: 4722 . COSPAR: 1970-098B. Apogee: 505 km (313 mi). Perigee: 493 km (306 mi). Inclination: 83.10 deg. Period: 94.60 min. Radar monitoring..

1970 December 11 - . 11:35 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Thor Delta N6.

NOAA 1 - . Payload: ITOS A. Mass: 306 kg (674 lb). Nation: USA. Agency: NOAA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: ITOS. USAF Sat Cat: 4793 . COSPAR: 1970-106A. Apogee: 1,473 km (915 mi). Perigee: 1,423 km (884 mi). Inclination: 101.70 deg. Period: 114.80 min. Built for NASA; operated by NOAA. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

CEPE - . Nation: USA. Agency: NASA Greenbelt. Program: Tiros. Spacecraft: CEPE. USAF Sat Cat: 4794 . COSPAR: 1970-106B. Apogee: 1,484 km (922 mi). Perigee: 1,426 km (886 mi). Inclination: 101.70 deg. Period: 114.92 min.

1971 February 3 - . 01:41 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta M.

NATO 2 - . Payload: NATO IIB. Mass: 243 kg (535 lb). Nation: NATO. Agency: NATO. Program: NATO. Class: Communications. Type: Military communications satellite. Spacecraft Bus: Skynet. Spacecraft: NATO 1. Completed Operations Date: 1984-06-01 . USAF Sat Cat: 4902 . COSPAR: 1971-009A. Apogee: 35,802 km (22,246 mi). Perigee: 35,772 km (22,227 mi). Inclination: 13.90 deg. Period: 1,436.10 min.
The second NATO military communications satellite (NATO IIB) was launched by NASA aboard a Thrust Augmented Thor/Delta booster. Developed for NATO under SAMSO program management, the spacecraft was first placed in a transfer orbit and then moved into an acceptable synchronous orbit on 4 February. Although numerous difficulties were experienced prior to launch, the satellite achieved its stationary orbit and has performed successfully since then. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 26 deg W in 1971-1975?; over the Americas at 105 deg W in 1976-1983; over the Americas at 110 deg W in 1983; over the Americas at 105 deg W in 1983-1998 As of 5 September 2001 located at 104.88 deg W drifting at 0.004 deg W per day. As of 2007 Mar 9 located at 105.24W drifting at 0.007W degrees per day.

1971 February 17 - . 03:52 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2.

DMSP-Block-5A F3 - . Payload: DAPP 3526 / OPS 5268. Mass: 195 kg (429 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 5A. USAF Sat Cat: 4953 . COSPAR: 1971-012A. Apogee: 799 km (496 mi). Perigee: 741 km (460 mi). Inclination: 98.70 deg. Period: 100.20 min. Defense Meteorological Satellite Program..

Calsphere 5 - . Payload: NRL PL170C / OPS 5268. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Radar calibration target. Spacecraft: Calsphere. Decay Date: 1990-01-07 . USAF Sat Cat: 4963 . COSPAR: 1971-012E. Apogee: 360 km (220 mi). Perigee: 340 km (210 mi). Inclination: 98.20 deg. Period: 91.50 min. Radar calibarion sphere. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

Calsphere 4 - . Payload: NRL PL170B / OPS 5268. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Radar calibration target. Spacecraft: Calsphere. Decay Date: 1989-09-20 . USAF Sat Cat: 4958 . COSPAR: 1971-012D. Apogee: 502 km (311 mi). Perigee: 486 km (301 mi). Inclination: 98.40 deg. Period: 94.50 min. Radar calibarion sphere. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

Calsphere 3A - . Payload: NRL PL170A / OPS 5268. Mass: 1.00 kg (2.20 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Radar calibration target. Spacecraft: Calsphere. Decay Date: 1989-10-17 . USAF Sat Cat: 4957 . COSPAR: 1971-012C. Apogee: 531 km (329 mi). Perigee: 509 km (316 mi). Inclination: 98.40 deg. Period: 95.00 min. Radar calibarion sphere. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1971 February 17 - . 20:04 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2H Agena D. FAILURE: Failure. Failed Stage: U.

KH-4B 1113 - . Payload: KH-4B s/n 1113. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1971-02-17 .
KH-4B. The launch vehicle had a very cold boattail due to a hose discovered to be leaking away warming air to the boattail. The boattail was colder than usual, below freezing. Based on earlier tests of the Thor for just that condition, as relayed by Ed Dierdorf, Thor chief engineer at the time, the temp low was of no concern.
The only problem was that those tests were made with a Thor that carried a Rocketdyne engine lubricated with "lube oil". The Thor being launched used a fuel additive, "Orinite" (like STP "super snot"). The technician that pumped the Orinite into its cannister later stated, "It wasn't for lack of orinite. I put it in just like the procedure said, and I could feel when it was full (with the hand pump). To make sure, I gave it another slug."
That "other slug" cracked the output valve that was only supposed to be cracked by turbopump output pressure. When it cracked the output valve a bit of the "honey" squirted down the tube toward engine bearing jets. This line had a low spot in it by design. The Orinite settled there. When it was chilled by the low temp air at lox loading, the Orinite formed a plug.
Unaware of this chain of circumstances, Launch Director Philip Payne made the decision to launch. The rocket (carrying Agena D and payload) flew for 18 seconds, then wiped out its gears, causing the turbine to overspeed and shed its vanes. These punctured various parts in the boattail like machine gun bullets. With loss of power, the rocket fell not far from the launch pad into Bear Creek canyon.
The final cause was therefore found to be loss of engine lubrication at startup.

SRV 825 - . Payload: SRV 1113-1. Mass: 3,000 kg (6,600 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4B.

SRV 826 - . Payload: SRV 1113-2. Mass: 3,000 kg (6,600 lb). Nation: USA. Agency: USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4B.

1971 March 13 - . 16:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta M6.

Explorer 43 - . Payload: IMP I. Mass: 288 kg (634 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Magnetosphere satellite. Spacecraft: IMP. Decay Date: 1974-10-02 . USAF Sat Cat: 5043 . COSPAR: 1971-019A. Apogee: 203,130 km (126,210 mi). Perigee: 1,845 km (1,146 mi). Inclination: 31.20 deg. Period: 5,957.90 min.
In its first use at Cape Canaveral, a NASA Long Tank Thrust Augmented Thor/ Delta boosted Explorer 43 into orbit. This was the first "Super Six" configuration Thor/Delta, with strap-on solid-rocket boosters motors, to be launched from the Eastern Test Range. Earth magnetosphere research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B).

1971 March 24 - . 21:05 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2H Agena D.

KH-4B 1114 - . Payload: KH-4B s/n 1114 / Agena D 1660 / OPS 5300. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1971-04-12 . USAF Sat Cat: 5059 . COSPAR: 1971-022A. Apogee: 245 km (152 mi). Perigee: 156 km (96 mi). Inclination: 81.50 deg. Period: 88.40 min. KH-4B. The overall image quality is good and comparable to the best of past missions. On-board program failed.

1971 April 1 - . 02:57 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta E1.

Isis 2 - . Payload: Isis B. Mass: 264 kg (582 lb). Nation: Canada. Agency: CRCSS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Isis. USAF Sat Cat: 5104 . COSPAR: 1971-024A. Apogee: 1,424 km (884 mi). Perigee: 1,358 km (843 mi). Inclination: 88.20 deg. Period: 113.60 min. Ionospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1971 June 8 - . 14:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2.

SESP 70-1 - . Payload: P70-1 / Burner II No. 12 / OPS 3850. Mass: 260 kg (570 lb). Nation: USA. Agency: USAF STP. Class: Technology. Type: Military technology satellite. Spacecraft: SESP. Decay Date: 1982-01-31 . USAF Sat Cat: 5285 . COSPAR: 1971-054A. Apogee: 580 km (360 mi). Perigee: 544 km (338 mi). Inclination: 90.20 deg. Period: 95.80 min. Space Experiments Support Program (SESP) orbital flight for the Naval Research Laboratory. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

1971 July 16 - . 10:50 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2H Agena D.

OPS 8373 - . Payload: Ferret 16 / Agena D 2737?. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO, USAF. Class: Surveillance. Type: SIGINT. Spacecraft: Ferret. Decay Date: 1978-08-31 . USAF Sat Cat: 5329 . COSPAR: 1971-060A. Apogee: 460 km (280 mi). Perigee: 450 km (270 mi). Inclination: 74.90 deg. Period: 93.60 min.

1971 September 10 - . 21:33 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2H Agena D.

KH-4B 1115 - . Payload: KH-4B s/n 1115 / Agena D 1662 / OPS 5454. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1971-10-05 . USAF Sat Cat: 5468 . COSPAR: 1971-076A. Apogee: 234 km (145 mi). Perigee: 157 km (97 mi). Inclination: 74.90 deg. Period: 88.30 min. KH-4B. Overall image quality is good..

SRV 831 - . Payload: SRV 1115-1. Nation: USA. Agency: USAF. Class: Surveillance. Type: SIGINT. Spacecraft Bus: P 11. Spacecraft: SSF. Decay Date: 1976-02-03 . USAF Sat Cat: 5469 . COSPAR: 1971-076xx. Apogee: 197 km (122 mi). Perigee: 187 km (116 mi). Inclination: 75.00 deg. Period: 88.30 min.

OPS 7681 - . Payload: EHH B21. Mass: 60 kg (132 lb). Nation: USA. Agency: NRO, USAF. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1976-02-03 . USAF Sat Cat: 5469 . COSPAR: 1971-076B. Apogee: 516 km (320 mi). Perigee: 489 km (303 mi). Inclination: 75.00 deg. Period: 94.70 min. Radar monitoring..

1971 September 29 - . 09:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Delta N.

OSO 7 - . Payload: OSO H. Mass: 635 kg (1,399 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: Solar satellite. Spacecraft: OSO. Decay Date: 1974-07-09 . USAF Sat Cat: 5491 . COSPAR: 1971-083A. Apogee: 572 km (355 mi). Perigee: 326 km (202 mi). Inclination: 33.10 deg. Period: 93.50 min. Orbiting Solar Observatory. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

TETR 3 - . Payload: TETR D. Mass: 20 kg (44 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Tracking network technology satellite. Spacecraft: TETR. Decay Date: 1978-09-19 . USAF Sat Cat: 5492 . COSPAR: 1971-083B. Apogee: 570 km (350 mi). Perigee: 403 km (250 mi). Inclination: 33.00 deg. Period: 94.30 min. Test satellite for NASA's Manned Space Flight Network. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1971 October 14 - . 07:51 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2A.

DMSP-Block-5B F1 - . Payload: DMSP 4527 / OPS 4311. Mass: 195 kg (429 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 5B. USAF Sat Cat: 5557 . COSPAR: 1971-087A. Apogee: 850 km (520 mi). Perigee: 772 km (479 mi). Inclination: 99.10 deg. Period: 101.10 min. Defense Meteorological Satellite Program..

1971 October 17 - . 13:36 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

ASTEX - . Payload: P71-2 / Agena D. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: USAF STP. Class: Technology. Type: Navigation technology satellite. Spacecraft: ASTEX. USAF Sat Cat: 5560 . COSPAR: 1971-089A. Apogee: 761 km (472 mi). Perigee: 738 km (458 mi). Inclination: 92.70 deg. Period: 99.80 min.
Space Test Program Flight 71-2 (STP 71-2), a Thorad/Agena launch vehicle, inserted four payloads into orbit from Vandenberg. Space Test Program; technology experiments. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A).

1971 October 21 - . 11:32 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta N6. FAILURE: Failure.. Failed Stage: U.

ITOS B - . Payload: ITOS B. Mass: 308 kg (679 lb). Nation: USA. Agency: NASA Greenbelt. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: ITOS. Decay Date: 1972-07-21 . USAF Sat Cat: 5565 . COSPAR: 1971-091A. Apogee: 1,483 km (921 mi). Perigee: 293 km (182 mi). Inclination: 102.50 deg. Period: 102.70 min. Unusable orbit..

1971 December 14 - . 12:13 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Thor. Launch Vehicle: Thorad SLV-2G Agena D.

OPS 7898 P/L 1 - . Payload: NRL PL171 / OPS 7898 / Poppy 7A (Poppy multifacete. Mass: 700 kg (1,540 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 5678 . COSPAR: 1971-110A. Apogee: 999 km (620 mi). Perigee: 983 km (610 mi). Inclination: 70.00 deg. Period: 104.90 min. Launch of a quadruplet of Poppy naval signals intelligence satellites. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

OPS 7898 P/L 3 - . Payload: NRL PL173 / OPS 7898 / Poppy 7C (Poppy multifacete. Mass: 700 kg (1,540 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 5681 . COSPAR: 1971-110D. Apogee: 997 km (619 mi). Perigee: 982 km (610 mi). Inclination: 70.00 deg. Period: 104.90 min. Poppy naval signals intelligence satellite. Official and secondary mission: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

OPS 7898 P/L 4 - . Payload: NRL PL174 / OPS 7898 / Poppy 7D (Poppy multifacete. Mass: 700 kg (1,540 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 5682 . COSPAR: 1971-110E. Apogee: 997 km (619 mi). Perigee: 981 km (609 mi). Inclination: 70.00 deg. Period: 104.90 min. Poppy naval signals intelligence satellite. Official and secondary mission: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

OPS 7898 P/L 2 - . Payload: NRL PL172 / OPS 7898 / Poppy 7B (Poppy multifacete. Mass: 700 kg (1,540 lb). Nation: USA. Agency: NRL. Class: Surveillance. Type: Naval SIGINT. Spacecraft: Poppy. USAF Sat Cat: 5680 . COSPAR: 1971-110C. Apogee: 999 km (620 mi). Perigee: 983 km (610 mi). Inclination: 70.00 deg. Period: 104.90 min. Poppy naval signals intelligence satellite. Official and secondary mission: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A)..

1972 January 31 - . 17:20 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta L.

HEOS 2 - . Payload: HEOS A2. Mass: 123 kg (271 lb). Nation: Europe. Agency: ESRO. Class: Earth. Type: Magnetosphere satellite. Spacecraft: HEOS. Decay Date: 1974-08-02 . USAF Sat Cat: 5814 . COSPAR: 1972-005A. Apogee: 240,164 km (149,230 mi). Perigee: 405 km (251 mi). Inclination: 89.90 deg. Period: 7,477.10 min. Highly Eccentric Orbiting Satellite; particles and fields data. Fifth satellite of ESRO. Also registered as US object 1972-05A in A/AC.105/INF.248 with orbit 7835.4 min, 439 x 248160 km x 90.2 deg, category B. .

1972 March 12 - . 01:55 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Thor. Launch Vehicle: Thor Delta N.

TD-1A; Thor Delta 1A - . Payload: TD 1A. Mass: 472 kg (1,040 lb). Nation: Europe. Agency: ESRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: TD-1A. Decay Date: 1980-01-09 . USAF Sat Cat: 5879 . COSPAR: 1972-014A. Apogee: 550 km (340 mi). Perigee: 523 km (324 mi). Inclination: 97.60 deg. Period: 95.40 min. Sixth satellite of ESRO. Also registered as US object 1972-14A in A/AC.105/INF.255 with orbit 95.3 min, 525 x 548 km x 97.5 deg, category B. .

1972 March 24 - . 08:46 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2A.

DMSP-Block-5B F2 - . Payload: DMSP 5528 / OPS 5058. Mass: 195 kg (429 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 5B. USAF Sat Cat: 5903 . COSPAR: 1972-018A. Apogee: 858 km (533 mi). Perigee: 781 km (485 mi). Inclination: 98.90 deg. Period: 101.30 min. Defense Meteorological Satellite Program..

1972 April 19 - . 21:43 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2H Agena D.

KH-4B 1116 - . Payload: KH-4B s/n 1116 / Agena D 1661 / OPS 5640. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1972-05-12 . USAF Sat Cat: 6003 . COSPAR: 1972-032A. Apogee: 276 km (171 mi). Perigee: 154 km (95 mi). Inclination: 81.00 deg. Period: 88.80 min. KH-4B. Very successful mission and image quality was good..

1972 May 25 - . 18:41 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Thor. Launch Vehicle: Thorad SLV-2H Agena D.

KH-4B 1117 - . Payload: KH-4B s/n 1117 / Agena D 1663 / OPS 6371. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: CIA, NRO. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: WS-117. Spacecraft: KH-4B. Decay Date: 1972-06-04 . USAF Sat Cat: 6037 . COSPAR: 1972-039A. Apogee: 305 km (189 mi). Perigee: 158 km (98 mi). Inclination: 96.30 deg. Period: 89.20 min. KH-4B. Last KH-4B mission. Very successful mission, image quality was good. Final CORONA mission..

1972 July 23 - . 18:06 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 0900.

Landsat 1 - . Payload: ERTS A. Mass: 816 kg (1,798 lb). Nation: USA. Agency: NASA Greenbelt. Program: Landsat. Class: Earth. Type: Earth resources satellite. Spacecraft Bus: Nimbus. Spacecraft: Landsat 1-2-3. USAF Sat Cat: 6126 . COSPAR: 1972-058A. Apogee: 909 km (564 mi). Perigee: 898 km (557 mi). Inclination: 99.10 deg. Period: 103.10 min.
The first Long Tank Thrust Augmented Thor/Delta to be launched from Vandenberg AFB using nine solid rocket motors successfully placed the Environmental Resources Technology Satellite (ERTS-A) in orbit. Earth Resources Technology Satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1972 September 23 - . 01:20 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 1604.

Explorer 47 - . Payload: IMP H. Mass: 376 kg (828 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Magnetosphere satellite. Spacecraft: IMP. USAF Sat Cat: 6197 . COSPAR: 1972-073A. Apogee: 235,600 km (146,300 mi). Perigee: 201,100 km (124,900 mi). Inclination: 17.20 deg. Period: 17,670.00 min. Investigated cislunar radiation, Earth's magnetosphere, interplantary magnetic field. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1972 October 15 - . 17:19 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 0300.

NOAA 2 - . Payload: ITOS D. Mass: 344 kg (758 lb). Nation: USA. Agency: NOAA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: ITOS. USAF Sat Cat: 6235 . COSPAR: 1972-082A. Apogee: 1,455 km (904 mi). Perigee: 1,449 km (900 mi). Inclination: 101.80 deg. Period: 114.90 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

Oscar 6 - . Payload: Amsat-Oscar-6. Mass: 16 kg (35 lb). Nation: USA. Agency: AmSat. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Oscar. USAF Sat Cat: 6236 . COSPAR: 1972-082B. Apogee: 1,455 km (904 mi). Perigee: 1,449 km (900 mi). Inclination: 101.70 deg. Period: 114.90 min.
AMSAT-OSCAR 6 was launched piggyback with ITOS-D (NOAA 2). AO-6 was the first phase 2 satellite (Phase II-A). Weight 16 kg. Box shaped 430 x 300 x 150 mm. Quarter-wave monopole antennas (144 and 435 MHz) and half-wave dipole antenna (29 MHz). Firsts: complex control system using discrete logic; satellite-to-satellite relay communication via AO-7; demonstrated doppler-location of ground station for search and rescue; demonstrated low-cost medical data relay from remote locations. Equipped with solar panels powering NiCd batteries, AO-6 provided 24 V at 3.5 W power to three transponders. It carried a Mode A transponder (100 kHz wide at 1 W) and provided store-and-forward morse and teletype messages (named Codestore) for later transmission. AO-6 lasted 4.5 years until a battery failure ceased operation on June 21, 1977. Subsystems were built in the United States, Australia, and Germany.

1972 November 9 - . 03:23 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2A.

DMSP-Block-5B F3 - . Payload: DMSP 6530 / OPS 7323. Mass: 195 kg (429 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 5B. USAF Sat Cat: 6275 . COSPAR: 1972-089A. Apogee: 841 km (522 mi). Perigee: 785 km (487 mi). Inclination: 98.60 deg. Period: 101.10 min.
A Thor/Delta booster launched from Cape Canaveral successfully placed a Canadian communications satellite, ANIK I, into orbit. This was the 75th Thor/Delta to be launched from the Cape and the first Long Tank Thrust Augmented Thor/Delta to be launched from the Cape with nine strap-on solid rocket motors. It placed the Telestar-A (ANIK) communications satellite in orbit for Canada. Defense Meteorological Satellite Program.

1972 November 10 - . 01:14 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 1914.

Anik A1 - . Payload: Telesat 1. Mass: 557 kg (1,227 lb). Nation: Canada. Agency: Telesat. Program: Anik. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 333. Completed Operations Date: 1982-07-15 . USAF Sat Cat: 6278 . COSPAR: 1972-090A. Apogee: 36,247 km (22,522 mi). Perigee: 36,145 km (22,459 mi). Inclination: 11.30 deg. Period: 1,457.10 min.
Anik I and Anik II also registered as United States objects. .The satellites, act as space repeaters capable of receiving transmissions from earth stations and retransmitting them to other earth stations in Canada. The antenna coverage of the satellite pr ovides the capability of serving virtually all of Canada. Anik I and II had weights of 1240.59 lb and 1246.48 lb. Each satellite has 12 RF channels each capable of transmitting a color television signal or up to 900 one-way voice channels. Positioned in geosynchronous orbit over the Americas at 114 deg W in 1973-1976; over the Americas at 104 deg W in 1976-1982 As of 1 September 2001 located at 66.14 deg W drifting at 5.205 deg W per day. As of 2007 Mar 9 located at 107.03W drifting at 5.211W degrees per day.

1972 December 11 - . 07:56 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 0900.

Nimbus 5 - . Payload: Nimbus E. Mass: 722 kg (1,591 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Weather satellite. Spacecraft: Nimbus. USAF Sat Cat: 6305 . COSPAR: 1972-097A. Apogee: 1,101 km (684 mi). Perigee: 1,088 km (676 mi). Inclination: 100.10 deg. Period: 107.20 min.
Environmental research. Primary experiments included a temperature-humidity infrared radiometer (THIR) for measuring day and night surface and cloudtop temperatures as well as the water vapor content of the upper atmosphere, electrically scanning microwave radiometer (ESMR) for mapping the microwave radiation from the earth's surface and atmosphere, infrared temperature profile radiometer (ITPR) for obtaining vertical profiles of temperature and moisture, Nimbus E microwave spectrometer (NEMS) for determining tropospheric temperature profiles, atmospheric water vapor abundances, and cloud liquid water contents, selective chopper radiometer (SCR) for observing the global temperature structure of the atmosphere, and a surface composition mapping radiometer (SCMR) for measuring the differences in the thermal emission characteristics of the earth's surface.

1973 April 20 - . 23:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 1914.

Anik A2 - . Payload: Telesat 2. Mass: 272 kg (599 lb). Nation: Canada. Agency: Telesat. Program: Anik. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 333. Completed Operations Date: 1982-10-28 . USAF Sat Cat: 6437 . COSPAR: 1973-023A. Apogee: 35,952 km (22,339 mi). Perigee: 35,886 km (22,298 mi). Inclination: 13.70 deg. Period: 1,442.90 min.
Anik I and Anik II also registered as United States objects. .The satellites, act as space repeaters capable of receiving transmissions from earth stations and retransmitting them to other earth stations in Canada. The antenna coverage of the satellite pr ovides the capability of serving virtually all of Canada. Anik I and II had weights of 1240.59 lb and 1246.48 lb. Each satellite has 12 RF channels each capable of transmitting a color television signal or up to 900 one-way voice channels. Positioned in geosynchronous orbit over the Americas at 109 deg W in 1973-1979; over the Americas at 106 deg W in 1979-1981; over the Americas at 114 deg W in 1981-1982 As of 26 August 2001 located at 0.59 deg E drifting at 1.690 deg W per day. As of 2007 Mar 9 located at 150.94E drifting at 1.684W degrees per day.

1973 June 10 - . 14:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 1913.

Explorer 49 - . Payload: RAE B. Mass: 328 kg (723 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: RAE. USAF Sat Cat: 6686 . COSPAR: 1973-039A. Radio Astronomy Explorer; measured galactic, stellar radio noise. Lunar Orbit (Selenocentric). Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

1973 July 16 - . 17:10 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 0300. FAILURE: Second stage failure.. Failed Stage: U.

ITOS E - . Payload: ITOS E. Mass: 345 kg (760 lb). Nation: USA. Agency: NASA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: ITOS. Decay Date: 1973-07-16 . Improved TIROS Operational System..

1973 August 17 - . 04:49 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2A.

DMSP-Block-5B F4 - . Payload: DMSP 7529 / OPS 8364. Mass: 195 kg (429 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 5B. USAF Sat Cat: 6787 . COSPAR: 1973-054A. Apogee: 819 km (508 mi). Perigee: 779 km (484 mi). Inclination: 98.90 deg. Period: 100.90 min. Defense Meteorological Satellite Program..

1973 October 26 - . 02:26 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 1604.

Explorer 50 - . Payload: IMP J. Mass: 371 kg (817 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Magnetosphere satellite. Spacecraft: IMP. USAF Sat Cat: 6893 . COSPAR: 1973-078A. Apogee: 244,361 km (151,838 mi). Perigee: 190,749 km (118,525 mi). Inclination: 31.60 deg. Period: 17,576.70 min. Solar flare and radiation monitor. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1973 November 6 - . 17:02 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 0300.

NOAA 3 - . Payload: ITOS F. Mass: 345 kg (760 lb). Nation: USA. Agency: NOAA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: ITOS. USAF Sat Cat: 6920 . COSPAR: 1973-086A. Apogee: 1,510 km (930 mi). Perigee: 1,501 km (932 mi). Inclination: 102.10 deg. Period: 116.10 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1973 December 16 - . 06:18 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 1900.

Explorer 51 - . Payload: AE C. Mass: 658 kg (1,450 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Atmosphere satellite. Spacecraft: AE. Decay Date: 1978-12-12 . USAF Sat Cat: 6977 . COSPAR: 1973-101A. Apogee: 4,306 km (2,675 mi). Perigee: 155 km (96 mi). Inclination: 68.10 deg. Period: 132.50 min. Atmospheric Explorer; upper atmospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1974 January 19 - . 01:38 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2313. FAILURE: Malfunction of the Thor Delta launch vehicle. Failed to reach planned orbit.. Failed Stage: U.

Skynet 2A - . Mass: 129 kg (284 lb). Nation: UK. Agency: MoD. Program: Skynet. Class: Communications. Type: Military communications satellite. Spacecraft: Skynet. Decay Date: 1974-01-25 . USAF Sat Cat: 7096 . COSPAR: 1974-002A. Apogee: 1,803 km (1,120 mi). Perigee: 104 km (64 mi). Inclination: 37.50 deg. Period: 104.10 min. The first of two British satellites-Skynet IIA-was launched from the Eastern Test Range. The payload was lost.

1974 March 16 - . 08:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2A.

DMSP-Block-5B F5 - . Payload: DMSP 8531 / OPS 8579. Mass: 195 kg (429 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 5B. USAF Sat Cat: 7218 . COSPAR: 1974-015A. Apogee: 846 km (525 mi). Perigee: 757 km (470 mi). Inclination: 99.10 deg. Period: 100.90 min. Defense Meteorological Satellite Program..

1974 April 13 - . 23:33 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

Westar 1 - . Mass: 500 kg (1,100 lb). Nation: USA. Agency: WUTC. Program: Westar. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 333. Completed Operations Date: 1983-05-02 . USAF Sat Cat: 7250 . COSPAR: 1974-022A. Apogee: 35,900 km (22,300 mi). Perigee: 35,886 km (22,298 mi). Inclination: 13.40 deg. Period: 1,441.50 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Americas at 99 deg W in 1974-1982; over the Americas at 100 deg W in 1982; over the Americas at 97 deg W in 1982; over the Americas at 79 deg W in 1982-1983 As of 5 September 2001 located at 85.83 deg W drifting at 1.372 deg W per day. As of 2007 Mar 10 located at 89.54E drifting at 1.381W degrees per day.

1974 May 17 - . 09:31 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

SMS 1 - . Payload: SMS A. Mass: 243 kg (535 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Weather satellite. Spacecraft: SMS. Completed Operations Date: 1981-01-29 . USAF Sat Cat: 7298 . COSPAR: 1974-033A. Apogee: 36,303 km (22,557 mi). Perigee: 36,216 km (22,503 mi). Inclination: 15.50 deg. Period: 1,460.30 min.
Synchronous Meteorological Satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 45 deg W in 1974-1975; over the Atlantic Ocean 75 deg W in 1975; over the Americas at 105 deg W in 1976-1978; over the Americas at 91 deg W in1978; over the Atlantic Ocean 75 deg W in 1979; over the Atlantic Ocean 70 deg W in 1979; over the Pacific Ocean 132 deg W in 1980 As of 3 September 2001 located at 84.60 deg W drifting at 5.986 deg W per day. As of 2007 Mar 10 located at 116.51E drifting at 5.981W degrees per day.

1974 August 9 - . 03:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2A.

DMSP-Block-5C F1 - . Payload: DMSP 9532 / OPS 6983. Mass: 195 kg (429 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 5C. USAF Sat Cat: 7411 . COSPAR: 1974-063A. Apogee: 844 km (524 mi). Perigee: 779 km (484 mi). Inclination: 98.80 deg. Period: 101.10 min. Defense Meteorological Satellite Program..

1974 October 10 - . 22:53 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

Westar 2 - . Mass: 500 kg (1,100 lb). Nation: USA. Agency: WUTC. Program: Westar. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 333. Completed Operations Date: 1986-05-07 . USAF Sat Cat: 7466 . COSPAR: 1974-075A. Apogee: 35,910 km (22,310 mi). Perigee: 35,895 km (22,304 mi). Inclination: 9.50 deg. Period: 1,442.00 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Americas at 123 deg W in 1974-1982; over the Americas at 79 deg W in 1982-1986 As of 2 September 2001 located at 144.45 deg E drifting at 1.482 deg W per day. As of 2007 Mar 8 located at 6.53W drifting at 1.482W degrees per day.

1974 November 15 - . 17:11 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 2310.

NOAA 4 - . Payload: ITOS G. Mass: 340 kg (740 lb). Nation: USA. Agency: NOAA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: ITOS. USAF Sat Cat: 7529 . COSPAR: 1974-089A. Apogee: 1,459 km (906 mi). Perigee: 1,445 km (897 mi). Inclination: 101.80 deg. Period: 114.90 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

Intasat 1 - . Payload: Intasat. Mass: 20 kg (44 lb). Nation: Spain. Agency: INTA. Class: Technology. Type: Communications technology satellite. Spacecraft: Intasat. USAF Sat Cat: 7531 . COSPAR: 1974-089C. Apogee: 1,459 km (906 mi). Perigee: 1,442 km (896 mi). Inclination: 101.80 deg. Period: 114.90 min.

Oscar 7 - . Payload: Amsat-Oscar-7. Mass: 29 kg (63 lb). Nation: USA. Agency: AmSat. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Oscar. USAF Sat Cat: 7530 . COSPAR: 1974-089B. Apogee: 1,459 km (906 mi). Perigee: 1,440 km (890 mi). Inclination: 101.80 deg. Period: 114.90 min.
AMSAT-OSCAR 7 was launched piggyback with ITOS-G (NOAA 4) and the Spanish INTASAT. The second phase 2 satellite (Phase II-B). Weight 28.6 kg. Octahedrally shaped 360 mm high and 424 mm in diameter. Circularly polarized canted turnstile VHF/UHF antenna system and HF dipole. Firsts: Satellite-to-satellite relay communication via AO-6; Early demonstrations of low-budget medical data relay and doppler location of ground transmitters for search-and-rescue operations were done using this satellite. AO-7 was fully operational for 6.5 years until a battery failed in mid 1981. However the satellite was still functional in day-side passes when its ever-degrading solar cells could function, and was still responding to amateurs as of August 2006. Additional Details: here....

1974 November 23 - . 00:28 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2313.

Skynet 2B - . Payload: Skynet 2A. Mass: 129 kg (284 lb). Nation: UK. Agency: MoD. Program: Skynet. Class: Communications. Type: Military communications satellite. Spacecraft: Skynet. Completed Operations Date: 1992-01-01 . USAF Sat Cat: 7547 . COSPAR: 1974-094A. Apogee: 35,822 km (22,258 mi). Perigee: 35,782 km (22,233 mi). Inclination: 12.20 deg. Period: 1,436.90 min.
A Thor-Delta launched from the Eastern Test Range lifted the second of two Skynet II (Skynet IIB) defense communications satellite for the United Kingdom into an elliptical transfer orbit. Two days later, a firing of the satellite's apogee boost motor placed the satellite in a near circular orbit prior to final positioning in a synchronous orbit over the Indian Ocean. The first Skynet II satellite, Skynet IIA, was lost in January 1974 due to a booster failure after launch from Cape Canaveral. Military communications. Positioned in geosynchronous orbit over the Indian Ocean at 50-55 deg E in 1975-1977; drifting As of 3 September 2001 located at 18.23 deg E drifting at 0.206 deg W per day. As of 2007 Feb 27 located at 54.93E drifting at 0.393E degrees per day.

1974 December 19 - . 02:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

Symphonie 1 - . Payload: Symphonie MV1. Mass: 221 kg (487 lb). Nation: France. Agency: CNES, DFVLR. Class: Technology. Type: Communications technology satellite. Spacecraft: Symphonie. Completed Operations Date: 1983-08-03 . USAF Sat Cat: 7578 . COSPAR: 1974-101A. Apogee: 35,893 km (22,302 mi). Perigee: 35,853 km (22,277 mi). Inclination: 14.90 deg. Period: 1,440.50 min.
Experimental commsat. Jointly registered by the Federal Republic of Germany (A/AC.105/INF.305) and France (A/AC.105/INF.306). Symphonie flying model no. 1, constructed jointly by France and the Federal Republic of Germany. Description: Experimental teleco mmunications satellite. Orbit: geostationary. Positioned in geosynchronous orbit over the Atlantic Ocean at 11 deg W in 1975-1977; over the Indian Ocean 49 deg E in 1977-1983 As of 25 August 2001 located at 179.98 deg E drifting at 1.086 deg W per day. As of 2007 Mar 11 located at 72.77E drifting at 1.184W degrees per day.

1975 January 22 - . 17:55 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 2910.

Landsat 2 - . Payload: Landsat B. Mass: 953 kg (2,101 lb). Nation: USA. Agency: NASA Greenbelt. Program: Landsat. Class: Earth. Type: Earth resources satellite. Spacecraft Bus: Nimbus. Spacecraft: Landsat 1-2-3. USAF Sat Cat: 7615 . COSPAR: 1975-004A. Apogee: 913 km (567 mi). Perigee: 900 km (550 mi). Inclination: 99.30 deg. Period: 103.10 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1975 February 6 - . 22:04 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

SMS 2 - . Payload: SMS B. Mass: 627 kg (1,382 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Weather satellite. Spacecraft: SMS. Completed Operations Date: 1982-08-11 . USAF Sat Cat: 7648 . COSPAR: 1975-011A. Apogee: 36,060 km (22,400 mi). Perigee: 35,941 km (22,332 mi). Inclination: 12.00 deg. Period: 1,447.10 min.
Synchronous Meteorological Satellite. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Americas at (GOES W) 115 deg W in 1975-1976; over the Pacific Ocean (GOES W) 135 deg W in 1976-1978; over the Atlantic Ocean (GOES E) 75 deg W in 1979-1981; over the Americas at 106 deg W in 1982 As of 29 August 2001 located at 123.04 deg W drifting at 2.760 deg W per day. As of 2007 Feb 27 located at 127.44E drifting at 2.742W degrees per day.

1975 April 9 - . 23:58 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 1410.

Geos 3 - . Payload: GEOS C. Mass: 341 kg (751 lb). Nation: USA. Agency: NASA Wallops. Class: Astronomy. Type: Solar satellite. Spacecraft: Geos. USAF Sat Cat: 7734 . COSPAR: 1975-027A. Apogee: 848 km (526 mi). Perigee: 817 km (507 mi). Inclination: 115.00 deg. Period: 101.60 min.
Geodynamics Experimental Ocean Satellite. The mission of GEOS 3 (Geodynamics Experimental Ocean Satellite) was to provide the stepping stone between the National Geodetic Satellite Program (NGSP) and the Earth and Ocean Physics Application Program. It provided data to refine the geodetic and geophysical results of the NGSP and served as a test for new systems. A major achievment was the flight of a radar altimeter. Further mission objectives: intercomparison of tracking systems, investigation of solid-earth dynamic phenomena through precision laser tracking, refinement of orbit determination techniques, determination of interdatum ties and gravity models, and support of the calibration and position determination of NASA Spaceflight Tracking and Data Network (STDN) S-band tracking stations.

1975 May 7 - . 23:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

Anik A3 (Telesat 3) - . Payload: Anik A3. Mass: 286 kg (630 lb). Nation: Canada. Agency: Telesat. Program: Anik. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 333. Completed Operations Date: 1984-11-23 . USAF Sat Cat: 7790 . COSPAR: 1975-038A. Apogee: 35,851 km (22,276 mi). Perigee: 35,845 km (22,273 mi). Inclination: 9.00 deg. Period: 1,439.20 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Americas at 104 deg W in 1975-1976; over the Americas at 114 deg W in 1976-1984 As of 4 September 2001 located at 32.38 deg E drifting at 0.812 deg W per day. As of 2007 Mar 9 located at 138.81W drifting at 0.829W degrees per day.

1975 May 24 - . 03:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2A.

DMSP-Block-5C F2 - . Payload: DMSP 10533 / OPS 6226. Mass: 194 kg (427 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 5C. USAF Sat Cat: 7816 . COSPAR: 1975-043A. Apogee: 880 km (540 mi). Perigee: 794 km (493 mi). Inclination: 98.70 deg. Period: 101.70 min. Defense Meteorological Satellite Program..

1975 June 12 - . 08:12 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 2910.

Nimbus 6 - . Payload: Nimbus F. Mass: 829 kg (1,827 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Weather satellite. Spacecraft: Nimbus. USAF Sat Cat: 7924 . COSPAR: 1975-052A. Apogee: 1,114 km (692 mi). Perigee: 1,101 km (684 mi). Inclination: 100.00 deg. Period: 107.40 min.
Environmental research. The experiments selected for Nimbus-6 were the earth radiation budget (ERB), electrically scanning microwave radiometer (ESMR), high-resolution infrared radiation sounder (HIRS), limb radiance inversion radiometer (LRIR), pressure modulated radiometer (PMR), scanning microwave spectrometer (SCAMS), temperature-humidity infrared radiometer (THIR), tracking and data relay experiment (T+DRE), and the tropical wind energy conversion and reference level experiment (TWERLE). This complement of advanced sensors was capable of mapping tropospheric temperature, water vapor abundance, and cloud water content; providing vertical profiles of temperature, ozone, and water vapor; transmitting real-time data to a geostationary spacecraft (ATS 6); and yielding data on the earth's radiation budget.

1975 June 21 - . 11:43 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 1910.

OSO 8 - . Payload: OSO I. Mass: 1,066 kg (2,350 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: Solar satellite. Spacecraft: OSO. Decay Date: 1986-07-09 . USAF Sat Cat: 7970 . COSPAR: 1975-057A. Apogee: 553 km (343 mi). Perigee: 539 km (334 mi). Inclination: 32.90 deg. Period: 95.60 min. Orbiting Solar Observatory. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1975 August 9 - . 01:48 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 2913.

COS-B - . Payload: COS B. Mass: 280 kg (610 lb). Nation: Europe. Agency: ESA. Class: Technology. Type: Navigation technology satellite. Spacecraft: COS. Decay Date: 1986-01-18 . USAF Sat Cat: 8062 . COSPAR: 1975-072A. Apogee: 99,002 km (61,516 mi). Perigee: 442 km (274 mi). Inclination: 90.30 deg. Period: 2,203.90 min.
Eighth CERS/ESRO satellite, first European Space Agency satellite. Launch time 0147:59 GMT. Argument of perigee 344.7 deg. Also registered by the United States in A/AC.105/INF.331 as 1975-72A, category B satellite with orbit 2203.9 min, 442 x 99002 km x 9 0.3 deg.

1975 August 27 - . 01:41 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 2914.

Symphonie 2 - . Payload: Symphonie MV2. Mass: 398 kg (877 lb). Nation: France. Agency: CNES, DFVLR. Class: Communications. Type: Civilian communications satellite. Spacecraft: Spacebus 100. Completed Operations Date: 1985-01-01 . USAF Sat Cat: 8132 . COSPAR: 1975-077A. Apogee: 35,873 km (22,290 mi). Perigee: 35,866 km (22,286 mi). Inclination: 12.70 deg. Period: 1,440.40 min.
Jointly registered by the Federal Republic of Germany (A/AC.105/INF.329) and France (A/AC.105/INF.330). Symphonie flying model no II. Experimental telecommunications satellite. Orbit: geostationary. Also registered by the United Stat es in A/AC.105/INF.331 as 1975-77A, category C, with orbit 1427.4 min, 35364 x 35870 km x 0.0 deg Positioned in geosynchronous orbit over the Atlantic Ocean at 11 deg W in 1975-1985 As of 1 September 2001 located at 164.06 deg W drifting at 1.071 deg W per day. As of 2007 Mar 8 located at 167.97E drifting at 1.046W degrees per day.

1975 September 9 - . 05:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1.

Kiku 1 - . Payload: ETS 1 (JETS). Mass: 85 kg (187 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 8197 . COSPAR: 1975-082A. Apogee: 1,103 km (685 mi). Perigee: 975 km (605 mi). Inclination: 47.00 deg. Period: 106.00 min.
JETS-1 (Japanese Engineering Test Satellite -1, national name 'Kiku') is intended for preliminary experiments for confirmation of the launching technologies, acquiring the satellite tracking and control technologies, and for extension tests of the extenda ble antennas, measurement of satellite environment, measurement of satellite attitudes, etc. Launch time 0530 GMT.

1975 September 19 - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

DG-5 - . Nation: USA. Agency: USAF. Apogee: 500 km (310 mi).

1975 October 6 - . 09:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 2910.

Explorer 54 - . Payload: AE D. Mass: 676 kg (1,490 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Atmosphere satellite. Spacecraft: AE. Decay Date: 1976-03-12 . USAF Sat Cat: 8353 . COSPAR: 1975-096A. Apogee: 3,819 km (2,373 mi). Perigee: 151 km (93 mi). Inclination: 90.10 deg. Period: 126.80 min. Atmospheric Explorer; atmospheric research. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1975 October 16 - . 22:40 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

GOES 1 - . Payload: GOES A. Mass: 295 kg (650 lb). Nation: USA. Agency: NOAA. Class: Earth. Type: Weather satellite. Spacecraft: GOES. Completed Operations Date: 1985-01-01 . USAF Sat Cat: 8366 . COSPAR: 1975-100A. Apogee: 35,811 km (22,251 mi). Perigee: 35,787 km (22,236 mi). Inclination: 14.80 deg. Period: 1,436.70 min.
Geostationary Operational Environmental Satellite. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). Positioned in geosynchronous orbit over the Atlantic Ocean at 55 deg W in 1975-1976; over the Pacific Ocean 135 deg W in 1976-1978; over the Atlantic Ocean 10 deg W in 1978; over the Indian Ocean 58 deg E in 1978-1979; over the Pacific Ocean 135 deg W in 1979-1980; over the Atlantic Ocean 93 deg W in 1980; over the Pacific Ocean 130 deg W in 1980-1985 As of 3 September 2001 located at 81.97 deg W drifting at 0.051 deg E per day. As of 2007 Mar 9 located at 81.95W drifting at 0.055W degrees per day.

1975 November 6 - . Launch Site: Johnston Island. Launch Complex: Johnston Island LE2. LV Family: Thor. Launch Vehicle: Thor DSV-2J.

DG-3 - . Nation: USA. Agency: USAF. Apogee: 500 km (310 mi).

1975 November 20 - . 02:06 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2910.

Explorer 55 - . Payload: AE E. Mass: 721 kg (1,589 lb). Nation: USA. Agency: NASA Greenbelt. Program: Explorer. Class: Earth. Type: Atmosphere satellite. Spacecraft: AE. Decay Date: 1981-06-10 . USAF Sat Cat: 8440 . COSPAR: 1975-107A. Apogee: 3,002 km (1,865 mi). Perigee: 154 km (95 mi). Inclination: 19.70 deg. Period: 117.70 min. Atmospheric Explorer. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1975 December 13 - . 01:56 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914.

Satcom 1 - . Mass: 464 kg (1,022 lb). Nation: USA. Agency: RCA Amer. Manufacturer: Lockheed. Program: Satcom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 1000. Completed Operations Date: 1984-06-04 . USAF Sat Cat: 8476 . COSPAR: 1975-117A. Apogee: 36,076 km (22,416 mi). Perigee: 35,875 km (22,291 mi). Inclination: 12.80 deg. Period: 1,445.80 min.
Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg W in 1976-1983; over the Americas at 119 deg W in 1983-1984; over the Pacific Ocean 139 deg W in 1984 As of 5 September 2001 located at 38.03 deg E drifting at 2.422 deg W per day. As of 2007 Mar 9 located at 137.85W drifting at 2.426W degrees per day.

1976 January 17 - . 23:27 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

CTS 1 - . Payload: Hermes. Mass: 500 kg (1,100 lb). Nation: Canada. Agency: CRCSS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CTS. Completed Operations Date: 1979-12-08 . USAF Sat Cat: 8585 . COSPAR: 1976-004A. Apogee: 35,840 km (22,260 mi). Perigee: 35,704 km (22,185 mi). Inclination: 12.80 deg. Period: 1,435.40 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Americas at 116 deg W in 1976-79; over the Pacific Ocean 142 deg W in 1979 As of 5 September 2001 located at 135.36 deg W drifting at 0.161 deg W per day. As of 2007 Mar 10 located at 131.55W drifting at 0.190W degrees per day.

1976 February 19 - . 07:52 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor Burner 2A. FAILURE: Early booster cut-off due to incorrect calculation of the Thor fuel load.. Failed Stage: G.

DMSP-Block-5C F3 - . Payload: DMSP 11534/Star 26B S/N 009 / OPS 5140. Mass: 175 kg (385 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft Bus: DMSP. Spacecraft: DMSP Block 5C. Decay Date: 1976-02-19 . USAF Sat Cat: 8696 . COSPAR: 1976-016A. Apogee: 361 km (224 mi). Perigee: 89 km (55 mi). Inclination: 98.90 deg. Period: 88.90 min. Defense Meteorological Satellite Program; unusable orbit. Last of the Thor Burner missions..

1976 February 19 - . 22:32 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

Marisat 1 - . Payload: Marisat 101. Mass: 655 kg (1,444 lb). Nation: USA. Agency: Comsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Marisat. Completed Operations Date: 1997-04-02 . USAF Sat Cat: 8697 . COSPAR: 1976-017A. Apogee: 36,143 km (22,458 mi). Perigee: 36,033 km (22,389 mi). Inclination: 13.90 deg. Period: 1,451.50 min.
Maritime communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 15 deg W in 1976-1990; over the Americas at 106 deg W in 1990-1997 As of 2 September 2001 located at 168.03 deg W drifting at 3.834 deg W per day. As of 2007 Mar 10 located at 20.39E drifting at 3.837W degrees per day.

1976 February 29 - . 03:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1.

ISS 1 - . Payload: ISS a. Mass: 139 kg (306 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Ionosphere satellite. Spacecraft: JISS. USAF Sat Cat: 8709 . COSPAR: 1976-019A. Apogee: 1,003 km (623 mi). Perigee: 988 km (613 mi). Inclination: 69.70 deg. Period: 105.00 min.
Ionospheric sounding. Japanese Ionospheric Sounding Satellite (JISS - national name 'Ume') is intended for regular observations by means of radio waves of the global distribution of the critical frequencies of the ionosphere, and for utilization of the results of the observati on for radio wave forecasts and warning necessary for effective operation of short-wave radio-communication. Time of launch 0330UT.

1976 March 26 - . 22:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914.

RCA Satcom 2 - . Payload: Satcom 2. Mass: 463 kg (1,020 lb). Nation: USA. Agency: RCA Amer. Manufacturer: Lockheed. Program: Satcom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 1000. Completed Operations Date: 1985-01-17 . USAF Sat Cat: 8774 . COSPAR: 1976-029A. Apogee: 36,494 km (22,676 mi). Perigee: 36,016 km (22,379 mi). Inclination: 8.60 deg. Period: 1,460.10 min.
Positioned in geosynchronous orbit over the Americas at 119 deg W in 1976-1984 over the Pacific Ocean 139 deg W in 1984-1985 As of 5 September 2001 located at 72.03 deg W drifting at 5.939 deg W per day. As of 2007 Mar 9 located at 127.82W drifting at 5.942W degrees per day.

1976 April 22 - . 20:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

NATO 3A - . Mass: 310 kg (680 lb). Nation: NATO. Agency: NATO. Program: NATO. Class: Communications. Type: Military communications satellite. Spacecraft: NATO 3. Completed Operations Date: 1992-12-17 . USAF Sat Cat: 8808 . COSPAR: 1976-035A. Apogee: 36,017 km (22,379 mi). Perigee: 35,801 km (22,245 mi). Inclination: 13.30 deg. Period: 1,442.40 min.
A Thor/Delta carrying the NATO IIIA satellite was successfully launched from LC-17B, Eastern Test Range. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 18 deg W in 1976-1982; over the Atlantic Ocean 30 deg W in 1982-1984; over the Atlantic Ocean 50 deg W in 1984-1985; over the Atlantic Ocean at 30 deg W in 1985-1989; over the Americas at 125 deg W in 1989-1991 As of 5 September 2001 located at 4.12 deg E drifting at 1.524 deg W per day. As of 2007 Mar 9 located at 142.00E drifting at 1.522W degrees per day.

1976 May 4 - . 08:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 2913.

Lageos - . Payload: Lageos 1. Mass: 411 kg (906 lb). Nation: USA. Agency: NASA Huntsville. Class: Earth. Type: Geodetic satellite. Spacecraft: Lageos. USAF Sat Cat: 8820 . COSPAR: 1976-039A. Apogee: 5,947 km (3,695 mi). Perigee: 5,839 km (3,628 mi). Inclination: 109.90 deg. Period: 225.50 min.
LAGEOS (Laser Geodetic Satellite) was a very dense (high mass-to-area ratio) laser retroreflector satellite which provided a permanent reference point in a very stable orbit for such precision earth-dynamics measurements as crustal motions, regional strains, fault motions, polar motion and earth-rotation variations, solid earth tides, and other kinematic and dynamic parameters associated with earthquake assessment and alleviation. The performance in orbit of LAGEOS was limited only by degradation of the retroreflectors, so many decades of useful life can be expected. The high mass-to-area ratio and the precise, stable (attitude-independent) geometry of the spacecraft, together with the orbit, made this satellite the most precise position reference available. Because it is visible in all parts of the world and has an extended operation life in orbit, LAGEOS can serve as a fundamental standard for decades. Additional Details: here....

1976 June 10 - . 00:09 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 2914.

Marisat 2 - . Payload: Marisat 102. Mass: 362 kg (798 lb). Nation: USA. Agency: Comsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Marisat. Completed Operations Date: 1996-09-25 . USAF Sat Cat: 8882 . COSPAR: 1976-053A. Apogee: 37,604 km (23,365 mi). Perigee: 36,513 km (22,688 mi). Inclination: 14.90 deg. Period: 1,501.60 min.
Maritime communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 176 deg E in 1976-1991 over the Pacific Ocean 178 deg W in 1991-1996 As of 5 September 2001 located at 158.48 deg W drifting at 15.761 deg W per day. As of 2007 Mar 10 located at 162.62W drifting at 15.745W degrees per day.

1976 July 8 - . 23:31 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 2914.

Palapa 1 - . Payload: Palapa A1. Mass: 300 kg (660 lb). Nation: Indonesia. Agency: Perumtel. Program: Palapa. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 333. Completed Operations Date: 1986-01-01 . USAF Sat Cat: 9009 . COSPAR: 1976-066A. Apogee: 35,852 km (22,277 mi). Perigee: 35,818 km (22,256 mi). Inclination: 8.60 deg. Period: 1,438.60 min.
Palapa A1 and A2 were the initial elements of Indonesia's domestic communications satellite system. The spacecraft were identical to Canada's Anik and Western Union's Westars except for a modified parabolic reflector, enlarged to give maximum illumination of the Indonesian land mass. Operational lives for Palapa A1 and A2 ended June 1985 and January 1988, respectively. Spacecraft: Based on Hughes HS-333 design.1.5 m diameter parabolic reflector with 12 transponders working through 125 Earth stations. Spin stabilised with despun antenna and feeds. Payload: Both satellites carried 12 transponders that provided 4000 voice circuits or 12 simultaneous TV channels to the country's 6000+ inhabited islands. Positioned in geosynchronous orbit over the Indian Ocean at 83 deg E in 1976-1986? As of 28 August 2001 located at 177.38 deg E drifting at 0.588 deg W per day. As of 2007 Mar 10 located at 51.89W drifting at 0.649W degrees per day.

1976 July 29 - . 17:07 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 2310.

NOAA 5 - . Payload: ITOS H. Mass: 340 kg (740 lb). Nation: USA. Agency: NOAA. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: ITOS. USAF Sat Cat: 9057 . COSPAR: 1976-077A. Apogee: 1,523 km (946 mi). Perigee: 1,507 km (936 mi). Inclination: 102.30 deg. Period: 116.30 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1976 September 11 - . 08:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor DSV-2U.

AMS 1 - . Payload: DMSP 5D S-1 / OPS 5721. Mass: 450 kg (990 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft: DMSP Block 5D. USAF Sat Cat: 9415 . COSPAR: 1976-091A. Apogee: 833 km (517 mi). Perigee: 804 km (499 mi). Inclination: 98.50 deg. Period: 101.30 min. A Thor booster carrying the first DMSP Block 5D satellite was launched from SLC-10, Western Test Range. The launch was successful but the satellite lost stability and began to tumble after attaining orbit. Defense Meteorological Satellite Program..

1976 October 14 - . 22:44 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 2914.

Marisat 3 - . Payload: Marisat 103. Mass: 362 kg (798 lb). Nation: USA. Agency: Comsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Marisat. USAF Sat Cat: 9478 . COSPAR: 1976-101A. Apogee: 35,789 km (22,238 mi). Perigee: 35,782 km (22,233 mi). Inclination: 11.60 deg. Period: 1,436.10 min.
Maritime communications. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Indian Ocean at 73 deg E in 1976-on. As of 26 August 2001 located at 33.84 deg W drifting at 0.011 deg W per day. As of 2007 Mar 10 located at 34.60W drifting at 0.007W degrees per day.

1977 January 28 - . 00:49 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 2914.

NATO 3B - . Mass: 701 kg (1,545 lb). Nation: NATO. Agency: NATO. Program: NATO. Class: Communications. Type: Military communications satellite. Spacecraft: NATO 3. Completed Operations Date: 1993-07-29 . USAF Sat Cat: 9785 . COSPAR: 1977-005A. Apogee: 37,421 km (23,252 mi). Perigee: 37,079 km (23,039 mi). Inclination: 10.50 deg. Period: 1,511.50 min.
A Delta booster launched the NATO III-B communications satellite into orbit from Cape Canaveral, Florida. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg W in 1977-1979 over the Atlantic Ocean 20 deg W in 1979-1982 over the Atlantic Ocean 18 deg W in 1983-1986 over the Atlantic Ocean60 deg W in 1987-1993 As of 5 September 2001 located at 74.61 deg W drifting at 18.018 deg W per day. As of 2007 Mar 10 located at 40.43E drifting at 18.015W degrees per day.

1977 February 23 - . 08:50 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1.

Kiku 2 - . Payload: ETS 2. Mass: 130 kg (280 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. Completed Operations Date: 1990-12-01 . USAF Sat Cat: 9852 . COSPAR: 1977-014A. Apogee: 35,860 km (22,280 mi). Perigee: 35,854 km (22,278 mi). Inclination: 11.90 deg. Period: 1,439.70 min.
Engineering test satellite. Engineering Test Satellite Type II (ETS II), Kiku 2. Launch by N launch vehicle no 3. Geographical longitude of the geostationary orbit: 130 deg E. Preliminary experiments to acquire technologies to launch,track, and control geostationary satellites. P ropagation experiment of millimetre and quasi-millimetre waves. Characteristics: Weight at launch 245 kg. Configuration: cylindrical. Height 191 cm including antenna. Diameter 141 cm. Attitude control: spin stabilization. Expected life at least 6 months. Positioned in geosynchronous orbit over the Pacific Ocean at 130 deg E in 1977-1990 As of 5 September 2001 located at 16.93 deg E drifting at 0.930 deg W per day. As of 2007 Mar 9 located at 85.65W drifting at 0.986W degrees per day.

1977 March 10 - . 23:16 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 2914.

Palapa 2 - . Payload: Palapa A2. Mass: 574 kg (1,265 lb). Nation: Indonesia. Agency: Perumtel. Program: Palapa. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 333. Completed Operations Date: 1986-01-01 . USAF Sat Cat: 9862 . COSPAR: 1977-018A. Apogee: 35,867 km (22,286 mi). Perigee: 35,843 km (22,271 mi). Inclination: 7.60 deg. Period: 1,439.60 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Indian Ocean at 80 deg E in 1977-1986? As of 5 September 2001 located at 64.27 deg W drifting at 0.845 deg W per day. As of 2007 Mar 11 located at 69.73E drifting at 0.893W degrees per day.

1977 April 20 - . 10:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

ESA-Geos 1 - . Payload: ESA GEOS 1. Mass: 573 kg (1,263 lb). Nation: Europe. Agency: ESA. Class: Earth. Type: Magnetosphere satellite. Spacecraft: ESA-Geos. USAF Sat Cat: 9931 . COSPAR: 1977-029A. Apogee: 38,214 km (23,745 mi). Perigee: 2,939 km (1,826 mi). Inclination: 26.60 deg. Period: 734.00 min. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1977 June 5 - . 02:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor DSV-2U.

AMS 2 - . Payload: DMSP 5D S-2/Star 37S S/N 15003 / OPS 5644. Mass: 450 kg (990 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft: DMSP Block 5D. USAF Sat Cat: 10033 . COSPAR: 1977-044A. Apogee: 849 km (527 mi). Perigee: 788 km (489 mi). Inclination: 99.00 deg. Period: 101.30 min.
An LV-2F booster launched the second DMSP Block 5D satellite into orbit from Vandenberg AFB, California. The launch was marred by a series of anomalies which put the satellite in a retrograde orbit and a spinning condition. Defense Meteorological Satellite Program.

1977 June 16 - . 10:51 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

GOES 2 - . Payload: GOES B. Mass: 627 kg (1,382 lb). Nation: USA. Agency: NOAA. Class: Earth. Type: Weather satellite. Spacecraft: GOES. USAF Sat Cat: 10061 . COSPAR: 1977-048A. Apogee: 36,080 km (22,410 mi). Perigee: 35,985 km (22,360 mi). Inclination: 14.10 deg. Period: 1,448.70 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 75 deg W in 1977-1978 over the Americas at 100-110 deg W in 1979-1984 over the Americas at 112-114 deg W in 1984-1990 over the Atlantic Ocean 60 deg W in 1990-1992 over the Pacific Ocean 135 deg W in 1992-1995; over the Pacific Ocean 177 deg W in 1995-on. As of 4 September 2001 located at 147.59 deg W drifting at 3.154 deg W per day. As of 2007 Mar 8 located at 1.58W drifting at 3.141W degrees per day.

1977 July 14 - . 10:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

Himawari 1 - . Payload: GMS 1. Mass: 670 kg (1,470 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Weather satellite. Spacecraft: Himawari. Completed Operations Date: 1989-09-17 . USAF Sat Cat: 10143 . COSPAR: 1977-065A. Apogee: 36,148 km (22,461 mi). Perigee: 36,005 km (22,372 mi). Inclination: 11.10 deg. Period: 1,451.00 min.
Geostationary meteorological satellite. Positioned in geosynchronous orbit over the Pacific Ocean at 140 deg E in 1977-1981; over the Pacific Ocean 160 deg E in 1981-1984; over the Pacific Ocean 140 deg E in 1984; over the Pacific Ocean160 deg E in 1984-1989 As of 29 August 2001 located at 10.47 deg W drifting at 3.675 deg W per day. As of 2007 Mar 10 located at 112.63E drifting at 3.690W degrees per day.

1977 July 29 - . LV Family: Thor.

USAF AFSC to provider logistic support for the Thor launch vehicle. - . HQ USAF decided that AFSC should assume responsibility for providing logistic support to the Thor launch vehicle..

1977 August 25 - . 23:49 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2313.

Sirio 1 - . Mass: 220 kg (480 lb). Nation: Italy. Agency: CNR. Class: Technology. Type: Communications technology satellite. Spacecraft: Sirio. Completed Operations Date: 1989-09-28 . USAF Sat Cat: 10294 . COSPAR: 1977-080A. Apogee: 35,869 km (22,287 mi). Perigee: 35,755 km (22,217 mi). Inclination: 9.60 deg. Period: 1,437.40 min.
Experimental commsat. SIRIO (Satellite Italiano Ricerca Industriale Orientata). Launch time 2350:00 GMT. Geographical longitude of geostationary orbit 15 deg W. SIRIO is a spin stabilized geostationary experimental communications satellite. Characteristics of satellite: Weight at launch 398 kg, in orbit 218 kg. Configuration - cylindrical, height 1.981m, diameter 1.433 m, nominal life two years. Positioned in geosynchronous orbit over the Atlantic Ocean at 15 deg W in 1977-1981; over the Atlantic Ocean 25 deg W in 1981-1983; over the Indian Ocean 65 deg E in 1983-1985 As of 4 September 2001 located at 86.65 deg E drifting at 0.265 deg E per day. As of 2007 Mar 11 located at 75.38E drifting at 0.003E degrees per day.

1977 September 13 - . 23:31 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914. FAILURE: Vehicle exploded, probably SRM case.. Failed Stage: 0.

OTS 1 - . Mass: 865 kg (1,906 lb). Nation: Europe. Agency: ESA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ECS/OTS. Decay Date: 1977-09-13 . Orbital Test Satellite; failed to orbit..

1977 Oct - . LV Family: Thor.

Contract for two MB-3 propulsion systems for the Thor launch vehicle. - . Rocketdyne Division of Rockwell International went on contract to provide two MB-3 propulsion systems for the Thor launch vehicle..

1977 October 22 - . 13:53 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

ISEE 1 - . Payload: ISEE A. Mass: 340 kg (740 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Magnetosphere satellite. Spacecraft: ISEE. Decay Date: 1987-09-26 . USAF Sat Cat: 10422 . COSPAR: 1977-102A. Apogee: 137,806 km (85,628 mi). Perigee: 436 km (270 mi). Inclination: 12.70 deg. Period: 3,441.00 min. International Sun-Earth Explorer. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

ISEE 2 - . Payload: ISEE B. Mass: 166 kg (365 lb). Nation: Europe. Agency: ESA. Class: Earth. Type: Magnetosphere satellite. Spacecraft: ISEE. Decay Date: 1987-09-26 . USAF Sat Cat: 10423 . COSPAR: 1977-102B. Apogee: 137,765 km (85,603 mi). Perigee: 406 km (252 mi). Inclination: 13.50 deg. Period: 3,438.50 min. International Sun-Earth Explorer. .

1977 Nov - . LV Family: Thor.

Contract for logistic support to the Thor launch vehicle. - . The McDonnell Douglas Astronautics Company went on contract to provide logistic support to the Thor launch vehicle..

1977 November 23 - . 01:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 2914.

Meteosat 1 - . Mass: 697 kg (1,536 lb). Nation: Europe. Agency: ESA. Class: Earth. Type: Weather satellite. Spacecraft: Meteosat. Completed Operations Date: 1985-06-01 . USAF Sat Cat: 10489 . COSPAR: 1977-108A. Apogee: 35,854 km (22,278 mi). Perigee: 35,777 km (22,230 mi). Inclination: 11.90 deg. Period: 1,437.60 min.
European Space Agency satellite. Launch time 0135 GMT. Reached definitive position, 0 deg longitude over the Gulf of Guinea, on 7 December. Launched by United States Delta rocket. Positioned in geosynchronous orbit over the Atlantic Ocean at E-4 deg W in 1977-1981; 8E-12 deg E in 1981-1984; 2E-6 deg E in 1984-1985 As of 29 August 2001 located at 51.23 deg E drifting at 0.354 deg E per day. As of 2007 Mar 3 located at 11.52E drifting at 0.055W degrees per day.

1977 December 15 - . 00:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

Sakura - . Payload: CS-1A. Mass: 676 kg (1,490 lb). Nation: Japan. Agency: NASDA. Program: CS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CS-1. Completed Operations Date: 1985-11-19 . USAF Sat Cat: 10516 . COSPAR: 1977-118A. Apogee: 36,176 km (22,478 mi). Perigee: 36,169 km (22,474 mi). Inclination: 10.50 deg. Period: 1,455.90 min.
Medium-capacity Communications Satellite for Experimental Purposes . Launch vehicle Delta 2914-137. Launch time 0047 UT. Geographical longitude on geostationary orbit: 135 deg E. CS is a spin stabilized geostationary communications satellite. Characteris tics of satellite: Weight approx 340 kg at an early stage in orbit, configuration: cylindrical, height 3.48 m, diameter 2.18m, Expected life more than three years. Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg E in 1977-1983 over the Pacific Ocean 150 deg E in 1984-1985 As of 25 August 2001 located at 78.79 deg E drifting at 4.904 deg W per day. As of 2007 Mar 10 located at 94.72W drifting at 4.901W degrees per day.

1978 January 26 - . 17:36 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 2914.

IUE 1 - . Payload: IUE. Mass: 672 kg (1,481 lb). Nation: USA. Agency: ESA, NASA. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: IUE. Completed Operations Date: 1996-09-30 . USAF Sat Cat: 10637 . COSPAR: 1978-012A. Apogee: 41,296 km (25,660 mi). Perigee: 30,285 km (18,818 mi). Inclination: 34.30 deg. Period: 1,436.30 min.
International Ultraviolet Explorer. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Atlantic Ocean at 30 deg W in-60 deg W in 1978-1996 As of 3 September 2001 located at 35.66 deg E drifting at 0.773 deg W per day. As of 2007 Mar 8 located at 14.14W drifting at 0.700W degrees per day.

1978 February 16 - . 04:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1.

ISS 2 - . Payload: ISS b. Mass: 140 kg (300 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Ionosphere satellite. Spacecraft: JISS. USAF Sat Cat: 10674 . COSPAR: 1978-018A. Apogee: 1,216 km (755 mi). Perigee: 973 km (604 mi). Inclination: 69.40 deg. Period: 107.20 min.
Ionospheric sounding. Ionosphere Sounding Satellite-b . Launch time 0400 UT. Launch vehicle: N number 4. Spin-stabilized; Ionospheric Sounder, Radio Noise Receiver, Plasma Measuring Equipment, Ion Mass Spectrometer, and so on. The satellite is intended for regular observation of global distribution of critical frequencies of the ionosphere by means of radio waves. Weight about 141 kg. Shape: cylindrical, 3.9m diameter and 0.8m height. Expected life: probability of survival in 1.5 years is more than 70 percent.

1978 March 5 - . 17:54 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 2910.

Landsat 3 - . Payload: Landsat C. Mass: 960 kg (2,110 lb). Nation: USA. Agency: NASA Greenbelt. Program: Landsat. Class: Earth. Type: Earth resources satellite. Spacecraft Bus: Nimbus. Spacecraft: Landsat 1-2-3. USAF Sat Cat: 10702 . COSPAR: 1978-026A. Apogee: 915 km (568 mi). Perigee: 895 km (556 mi). Inclination: 98.90 deg. Period: 103.10 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

PIX - . Payload: PIX 1 / Delta 139. Mass: 350 kg (770 lb). Nation: USA. Agency: NASA Greenbelt. Class: Technology. Type: Navigation technology satellite. Spacecraft: PIX. Decay Date: 1981-01-27 . USAF Sat Cat: 10704 . COSPAR: 1978-026C. Apogee: 920 km (570 mi). Perigee: 903 km (561 mi). Inclination: 99.10 deg. Period: 103.20 min. Plasma Interaction Experiment. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

Oscar 8 - . Payload: Amsat-Oscar-8. Mass: 27 kg (59 lb). Nation: USA. Agency: AmSat. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Oscar. USAF Sat Cat: 10703 . COSPAR: 1978-026B. Apogee: 903 km (561 mi). Perigee: 894 km (555 mi). Inclination: 99.20 deg. Period: 103.00 min.
AMSAT-OSCAR 8 was launched piggyback with LandSat 3 (ERTS 3) and PIX. The third phase 2 satellite (Phase II-D). Weight 27.2 kg. Box shaped, 33 cm high, 38 x 38 cm. Circularly polarized VHF canted turnstile, UHF quarter wave monopole, and HF half-wave dipole antenna system. Another cooperative international effort (United States, Canada, Germany and Japan). AO-8 had a similar store-and-forward service as AO-7 and carried Mode A (145.850-900 MHz uplink and 29.400-500 MHz downlink) and Mode J (145.900-146.000 MHz uplink and 435.100 MHz downlink (inverted)) linear transponders and telemetry beacons on 435.095 MHz and 29.402 MHz. AO-8's primary mission was for educational applications and amateur communications. It was in operation for six years until the battery failed on June 24, 1983.

1978 April 7 - . 22:01 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

Yuri 1 - . Payload: BSE-1. Mass: 678 kg (1,494 lb). Nation: Japan. Agency: NASDA. Program: BS. Class: Technology. Type: Communications technology satellite. Spacecraft: Yuri. Completed Operations Date: 1982-01-28 . USAF Sat Cat: 10792 . COSPAR: 1978-039A. Apogee: 35,868 km (22,287 mi). Perigee: 35,736 km (22,205 mi). Inclination: 11.70 deg. Period: 1,436.90 min.
Experimental comsat. Medium-scale broadcasting satellite for experimental purposes (BSE). Launch vehicle Delta 2914-140. Launch time 2201 GMT. Location 110 deg E. Characteristics of satellite: Weight approx 355 kg in an early stage in orbit. Configuration - box shaped satelli te with 2 solar array panels with overall span of 8.95m. Height 3.09m, width 1.32m, length 1.19m. 3-axis stabilized attitude control. Expected life 3 years. Positioned in geosynchronous orbit over the Indian Ocean at 110 deg E in 1978-1982 As of 4 September 2001 located at 44.59 deg E drifting at 0.116 deg E per day. As of 2007 Mar 11 located at 108.19E drifting at 0.031E degrees per day.

1978 May 1 - . 03:05 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor DSV-2U.

AMS 3 - . Payload: DMSP 5D S-3 / OPS 6182. Mass: 513 kg (1,130 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft: DMSP Block 5D. USAF Sat Cat: 10820 . COSPAR: 1978-042A. Apogee: 799 km (496 mi). Perigee: 786 km (488 mi). Inclination: 98.70 deg. Period: 100.70 min. A Thor LV-2F was launched from Vandenberg AFB carrying the third DMSP Block 5D-1 satellite. The launch was successful, and the spacecraft and its sensors functioned normally once in orbit. Defense Meteorological Satellite Program..

1978 May 11 - . 22:59 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914.

OTS 2 - . Payload: OTS 2. Mass: 865 kg (1,906 lb). Nation: Europe. Agency: ESA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ECS/OTS. Completed Operations Date: 1991-01-02 . USAF Sat Cat: 10855 . COSPAR: 1978-044A. Apogee: 36,128 km (22,448 mi). Perigee: 36,085 km (22,422 mi). Inclination: 13.10 deg. Period: 1,452.50 min.
Orbital Test Satellite; replacement for OTS-A; communications experiments. European Space Agency satellite. Launch time 2259 GMT. Reached definitive position, 10 deg east longitude, on May 24 at 0800 GMT. Launch by US Delta rocket. Positioned in geosynchronous orbit over the Atlantic Ocean at 10 deg E in 1978-1982 over the Atlantic Ocean 5 deg E in 1982-1990 As of 30 August 2001 located at 18.51 deg W drifting at 4.070 deg W per day. As of 2007 Mar 9 located at 39.02E drifting at 4.083W degrees per day.

1978 June 16 - . 10:49 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

GOES 3 - . Payload: GOES C. Mass: 627 kg (1,382 lb). Nation: USA. Agency: NOAA. Class: Earth. Type: Weather satellite. Spacecraft: GOES. USAF Sat Cat: 10953 . COSPAR: 1978-062A. Apogee: 35,812 km (22,252 mi). Perigee: 35,767 km (22,224 mi). Inclination: 9.80 deg. Period: 1,436.30 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg W in 1978-1981 over the Americas at 90 deg W in 1982-1984 over the Pacific Ocean 135 deg W in 1985-1987 over the Americas at129 deg W in 1987-1990 over the Pacific Ocean 175 deg W in 1990-1995 over the Americas at 102-110 deg W in 1996-on. As of 5 September 2001 located at 101.78 deg W drifting at 0.017 deg W per day. As of 2007 Mar 9 located at 105.91W drifting at 0.030W degrees per day.

1978 July 14 - . 10:43 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 2914.

ESA-Geos 2 - . Payload: ESA GEOS 2. Mass: 573 kg (1,263 lb). Nation: Europe. Agency: ESA. Class: Earth. Type: Magnetosphere satellite. Spacecraft: ESA-Geos. Completed Operations Date: 1984-01-24 . USAF Sat Cat: 10981 . COSPAR: 1978-071A. Apogee: 36,049 km (22,399 mi). Perigee: 36,027 km (22,386 mi). Inclination: 14.60 deg. Period: 1,449.00 min.
Magnetospheric research. European Space Agency satellite. Launch time 1043 GMT. Reached initial operational position of 6 deg East on 26 Jul 1978. During the two years of its mission, it will be maintained in position between longitude 0 and 35 deg east in geosynchronous orbit. Positioned in geosynchronous orbit over the Atlantic Ocean at 36 deg E in 1978-1979 over the Atlantic Ocean 6-36 deg E in 1979-1981; over the Atlantic Ocean 24 deg E in 1981; over the Atlantic Ocean 33-37 deg E in 1981-1984 As of 3 September 2001 located at 177.77 deg W drifting at 3.212 deg W per day. As of 2007 Mar 9 located at 179.12E drifting at 3.212W degrees per day.

1978 August 12 - . 15:12 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

ISEE 3 - . Payload: ISEE C. Mass: 479 kg (1,056 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Magnetosphere satellite. Spacecraft: ISEE. USAF Sat Cat: 11004 . COSPAR: 1978-079A. Apogee: 1,089,200 km (676,700 mi). Perigee: 181 km (112 mi). Inclination: 1.00 deg. Period: 67,852.90 min.
International Sun-Earth Explorer; later renamed the International Cometary Explorer. Measured interaction between solar wind and Earth; rendezvoused with comet Giacobini-Zinner September 11, 1985. After several passes through the Earth's magnetotail, with gravity assists from lunar flybys in March, April, September and October of 1983, a final close lunar flyby (119.4 km above the moon's surface) on December 22, 1983, ejected the spacecraft out of the Earth-Moon system and into a heliocentric orbit ahead of the Earth, on a trajectory intercepting that of Comet Giacobini-Zinner. A total of fifteen propulsive maneuvers (four of which were planned) and five lunar flybys were needed to carry out the transfer from the halo orbit to an escape trajectory from the earth-moon system into a heliocentric orbit. The primary scientific objective of ICE was to study the interaction between the solar wind and a cometary atmosphere. As planned, the spacecraft traversed the plasma tail of Comet Giacobini-Zinner on September 11, 1985, and made in situ measurements of particles, fields, and waves. It also transited between the Sun and Comet Halley in late March 1986, when other spacecraft (Giotto, Planet-A, MS-T5, VEGA) were also in the vicinity of Comet Halley on their comet rendezvous missions. ICE became the first spacecraft to directly investigate two comets. An update to the ICE mission was approved by NASA headquarters in 1991. It defined a Heliospheric mission for ICE consisting of investigations of coronal mass ejections in coordination with ground-based observations, continued cosmic ray studies, and special period observations such as when ICE and Ulysses are on the same solar radial line. As of January 1990, ICE was in a 355 day heliocentric orbit with an aphelion of 1.03 AU, a perihelion of 0.93 AU and an inclination of 0.1 degree. This will bring it back to the vicinity of the earth-moon system in August, 2014. Termination of operations of ISEE 3 was authorized May 5, 1997.
International Sun-Earth Explorer 3 spacecraft, also known as the International Cometary Explorer after its trip to P/Giacobini-Zinner in 1985, returned to the vicinity of the Earth in August 2014 following 30 years in solar orbit. On April 18 ISEE 3 was in a 0.927 x 1.034 AU x 0.06 deg solar orbit at a distance of 28.9 million km from Earth. A group of enthusiasts attempted to revive the spacecraft. ISEE 3 was the first spacecraft at the Earth-Sun L1 Lagrange point. However, in a special 1986 ceremony NASA Administrator James Fletcher transferred ownership of the spacecraft from NASA to the Smithsonian Institution. Additional Details: here....

1978 October 24 - . 08:15 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 2910.

Nimbus 7 - . Payload: Nimbus G. Mass: 907 kg (1,999 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Weather satellite. Spacecraft: Nimbus. USAF Sat Cat: 11080 . COSPAR: 1978-098A. Apogee: 957 km (594 mi). Perigee: 943 km (585 mi). Inclination: 99.00 deg. Period: 104.10 min.
Environmental research. The experiments carried were a limb infrared monitoring of the stratosphere (LIMS), stratospheric and mesopheric sounder (SAMS), coastal-zone color scanner (CZCS), stratospheric aerosol measurement (SAM II), earth radiation budget (ERB), scanning multichannel microwave radiometer (SMMR), solar backscatter UV and total ozone mapping spectrometer (SBUV/TOMS), and temperature-humidity infrared radiometer (THIR). These sensors were capable of observing several parameters at and below the mesospheric levels. After 11 years in orbit, three experiments, SAM II, SBUV/TOMS, and ERB, were still functioning successfully.

CAMEO - . Payload: CAMEO Li Canister/CAMEO Ba Canister. Mass: 350 kg (770 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Magnetosphere satellite. Spacecraft: CAMEO. USAF Sat Cat: 11081 . COSPAR: 1978-098B. Apogee: 968 km (601 mi). Perigee: 924 km (574 mi). Inclination: 99.40 deg. Period: 104.00 min. Released barium cloud..

1978 November 19 - . 00:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

NATO 3C - . Mass: 720 kg (1,580 lb). Nation: NATO. Agency: NATO. Program: NATO. Class: Communications. Type: Military communications satellite. Spacecraft: NATO 3. Completed Operations Date: 1992-06-15 . USAF Sat Cat: 11115 . COSPAR: 1978-106A. Apogee: 36,299 km (22,555 mi). Perigee: 36,289 km (22,548 mi). Inclination: 11.80 deg. Period: 1,462.10 min.
A Delta 2914 booster was launched from Cape Canaveral carrying the NATO IIIC satellite. The launch was successful, and the satellite performed satisfactorily in orbit. Positioned in geosynchronous orbit over the Atlantic Ocean at 50 deg W in 1979-1982 over the Atlantic Ocean 21 deg W in 1983-1986 over the Atlantic Ocean 18 deg W in 1987-1991 over the Atlantic Ocean21 deg W in 1991-1992 As of 31 August 2001 located at 122.29 deg E drifting at 6.431 deg W per day. As of 2007 Mar 10 located at 114.22E drifting at 6.438W degrees per day.

1978 December 16 - . 00:21 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914.

Anik B1 (Telesat 4) - . Payload: Anik B1. Mass: 900 kg (1,980 lb). Nation: Canada. Agency: Telesat. Program: Anik. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: AS 3000. Spacecraft: Anik satellite. Completed Operations Date: 1986-12-17 . USAF Sat Cat: 11153 . COSPAR: 1978-116A. Apogee: 35,927 km (22,323 mi). Perigee: 35,900 km (22,300 mi). Inclination: 6.60 deg. Period: 1,442.60 min.
Longitude 109.0. Function - telecommunications. Operating entity - Telesat Canada. Positioned in geosynchronous orbit over the Americas at 109 deg W in 1978-1986 As of 29 August 2001 located at 59.48 deg E drifting at 1.672 deg W per day. As of 2007 Mar 9 located at 13.64W drifting at 1.622W degrees per day.

DRIMS - . Mass: 900 kg (1,980 lb). Nation: Canada. Agency: NASA Greenbelt. Program: Anik. Decay Date: 1979-04-23 . USAF Sat Cat: 11154 . COSPAR: 1978-116B. Apogee: 1,832 km (1,138 mi). Perigee: 181 km (112 mi). Inclination: 28.30 deg. Period: 105.26 min.
First use of the Delta Redundant Inertial Measurement System (DRIMS). DRIMS improved the inertial measurement unit introduced with DIGS, but kept the DIGS guidance computer. DRIMS added redundancy on all axes of motion. The Delta upper stage was tracked as a separate functional object with this designation on this launch.

1979 January 30 - . 21:42 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 2914.

SCATHA - . Payload: P 78-2. Mass: 360 kg (790 lb). Nation: USA. Agency: USAF. Class: Technology. Type: Communications technology satellite. Spacecraft Bus: Space Test Program Payloads. Spacecraft: SCATHA. Completed Operations Date: 1991-05-28 . USAF Sat Cat: 11256 . COSPAR: 1979-007A. Apogee: 42,860 km (26,630 mi). Perigee: 28,018 km (17,409 mi). Inclination: 10.20 deg. Period: 1,418.40 min.
Flight P78-2 was successfully launched by SAMSO's Space Test Program. The mission was designated SCATHA (Spacecraft Charging at High Altitudes) and gathered data on the build-up of electrical charges on satellites operating at geosynchronous altitude. It was sponsored jointly by NASA and the Air Force. Spacecraft charging experiments. The SCATHA spacecraft had two charged particle injection systems, one of which was the Satellite Positive-Ion-Beam System (SPIBS). This was a xenon ion source which included some of the technologies used in thrusters: however, the discharge chamber was not performance optimized as was done with ion engines. Maximum operating power was 0.045 kW, and the ion source could produce a thrust of about 0.14 mN at a specific impulse of 350 s. Ions could be ejected at 1 keV or 2 keV. Neutralization was accomplished by a tantalum filament. The specific impulse was low because there was no attempt to optimize the propellant efficiency. The SPIBS system was ground-tested for a period of 600 hours. The SCATHA spacecraft was placed in a near geosynchronous orbit. Ion beam operations were performed intermittently over a 247 day period. The SCATHA flight demonstrated that a charged spacecraft, and the dielectric surfaces on it, could be safely discharged by emitting a very low energy (<50 eV) neutral plasma -- in effect shorting the spacecraft to the ambient plasma before dangerous charging levels could be reached. As of 28 August 2001 located at 153.98 deg W drifting at 4.513 deg E per day. As of 2007 Mar 8 located at 19.65W drifting at 4.513E degrees per day.

1979 February 6 - . 08:46 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1. FAILURE: Third stage collided with ECS a.. Failed Stage: 3.

Ayame 1 - . Payload: ECS a; ECS 1. Mass: 260 kg (570 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Communications technology satellite. Spacecraft: Ayame. Completed Operations Date: 1979-02-09 . USAF Sat Cat: 11261 . COSPAR: 1979-009A. Apogee: 37,278 km (23,163 mi). Perigee: 29,407 km (18,272 mi). Inclination: 5.60 deg. Period: 1,313.10 min.
Experimental Communications Satellite. Experimental Communications Satellite (ECS). Launch time 0846 GMT. ECS was injected into the planned transfer orbit. On 9 Feb, however, ECS ceased radio transmissions about 10 seconds after the apogee kick motor was fired. Communicat ions and propagation experiments of satellite-communication systems. Operation and control experiment for geostationary satellites. Mass at launch 260 kg. Configuration - cylindrical. Height 1.9m including antenna. Diameter 1.4m. Spin stabilized. Last known longitude (13 June 1995) 146.23 deg W drifting at 33.817 deg E per day.

1979 June 6 - . 18:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor DSV-2U.

AMS 4 - . Payload: DMSP 5D S-5 / OPS 5390. Mass: 513 kg (1,130 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft: DMSP Block 5D. USAF Sat Cat: 11389 . COSPAR: 1979-050A. Apogee: 826 km (513 mi). Perigee: 805 km (500 mi). Inclination: 98.60 deg. Period: 101.20 min. A Thor LV-2F booster successfully launched the fourth DMSP Block 5D-1 satellite into low earth orbit. The launch site was Space Launch Complex 10, Vandenberg AFB, California. Defense Meteorological Satellite Program..

1979 August 10 - . 00:20 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 2914.

Westar 3 - . Mass: 572 kg (1,261 lb). Nation: USA. Agency: WUTC. Program: Westar. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 333. Completed Operations Date: 1990-01-24 . USAF Sat Cat: 11484 . COSPAR: 1979-072A. Apogee: 35,883 km (22,296 mi). Perigee: 35,868 km (22,287 mi). Inclination: 10.20 deg. Period: 1,440.60 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 91 deg W in 1979-1990 As of 2 September 2001 located at 7.26 deg W drifting at 1.139 deg W per day. As of 2007 Mar 9 located at 158.25E drifting at 1.129W degrees per day.

1979 December 7 - . 01:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914.

RCA Satcom 3 - . Payload: Satcom 3. Mass: 463 kg (1,020 lb). Nation: USA. Agency: RCA Amer. Manufacturer: Lockheed. Program: Satcom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 1000. USAF Sat Cat: 11635 . COSPAR: 1979-101A. Apogee: 35,502 km (22,059 mi). Perigee: 8,306 km (5,161 mi). Inclination: 8.10 deg. Period: 788.90 min. Failed before reaching geosynchronous orbit..

1980 February 14 - . 15:57 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3910.

SMM - . Payload: Solar Maximum Mission. Mass: 2,315 kg (5,103 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: Solar satellite. Spacecraft Bus: MMS. Spacecraft: SMM. Decay Date: 1989-12-02 . USAF Sat Cat: 11703 . COSPAR: 1980-014A. Apogee: 408 km (253 mi). Perigee: 405 km (251 mi). Inclination: 28.50 deg. Period: 92.70 min. Solar Maximum Mission; solar observatory; repaired 4/9/84 by STS-41C in orbit. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1980 February 22 - . 08:35 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1.

Ayame 2 - . Payload: ECS b; ECS 2. Mass: 260 kg (570 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Communications technology satellite. Spacecraft: Ayame. Completed Operations Date: 1980-02-24 . USAF Sat Cat: 11715 . COSPAR: 1980-018A. Apogee: 36,839 km (22,890 mi). Perigee: 32,785 km (20,371 mi). Inclination: 1.40 deg. Period: 1,386.60 min. Last known longitude (17 November 1988) 146.47 deg W drifting at 12.888 deg E per day..

1980 July 15 - . 02:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC10W. LV Family: Thor. Launch Vehicle: Thor DSV-2U. FAILURE: Separation problem gutted wiring from spacecraft.. Failed Stage: 2.

AMS 5 - . Payload: DMSP 5D S-4. Mass: 513 kg (1,130 lb). Nation: USA. Agency: USAF. Program: DMSP. Class: Earth. Type: Weather satellite. Spacecraft: DMSP Block 5D. Decay Date: 1980-07-14 .
Defense Meteorological Satellite Program. Although there was a press release immediately after the launch (by the spacecraft SPO) that said the 2nd stage motor exploded, in reality the problem was found to be due to poor design of the electrical connectors between the 2nd and third stages and a separation problem that ripped the wiring out of the spacecraft.

1980 September 9 - . 22:27 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914.

GOES 4 - . Payload: GOES D. Mass: 627 kg (1,382 lb). Nation: USA. Agency: NOAA. Class: Earth. Type: Weather satellite. Spacecraft: GOES. Completed Operations Date: 1988-11-09 . USAF Sat Cat: 11964 . COSPAR: 1980-074A. Apogee: 36,213 km (22,501 mi). Perigee: 35,948 km (22,337 mi). Inclination: 9.40 deg. Period: 1,451.20 min.
Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Positioned in geosynchronous orbit at 98 deg W in 1980-1981; 135 deg W in 1981-1983; 135-143 deg W in 1983; 139 deg W in 1984-1985; 10 deg W in 1985; 44 deg W in 1985-1988 As of 5 September 2001 located at 37.03 deg E drifting at 3.758 deg W per day. As of 2007 Mar 10 located at 45.89E drifting at 3.763W degrees per day.

1980 November 15 - . 22:49 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3910/PAM.

SBS 1 - . Mass: 550 kg (1,210 lb). Nation: USA. Agency: SBS. Program: SBS. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1990-06-22 . USAF Sat Cat: 12065 . COSPAR: 1980-091A. Apogee: 35,928 km (22,324 mi). Perigee: 35,895 km (22,304 mi). Inclination: 6.10 deg. Period: 1,442.50 min.
Satellite Business Systems. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 100 deg W in 1981-1984; 99 deg W in 1984-1990 As of 4 September 2001 located at 115.72 deg E drifting at 1.627 deg W per day. As of 2007 Mar 10 located at 96.16E drifting at 1.647W degrees per day.

1981 February 11 - . 08:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-2.

Kiku 3 - . Payload: ETS 4. Mass: 640 kg (1,410 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 12295 . COSPAR: 1981-012A. Apogee: 16,237 km (10,089 mi). Perigee: 305 km (189 mi). Inclination: 28.50 deg. Period: 294.10 min.
Kiku 3 (ETS-IV). Launching organization NASDA. Acquisition of the technology to handle a large-scale heavy satellite and test of the functions of on-board equipment and devices, as well as confirmation of the launching capacity of the N-II launch vehicle. Also tested ion thruster.

1981 May 22 - . 22:29 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914.

GOES 5 - . Payload: GOES E. Mass: 836 kg (1,843 lb). Nation: USA. Agency: NOAA. Class: Earth. Type: Weather satellite. Spacecraft: GOES. Completed Operations Date: 1990-07-01 . USAF Sat Cat: 12472 . COSPAR: 1981-049A. Apogee: 35,810 km (22,250 mi). Perigee: 35,775 km (22,229 mi). Inclination: 6.50 deg. Period: 1,436.40 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 85 deg W in 1981; 75 deg W in 1981-1987; 106 deg W in 1987-1988; 65 deg W in 1988-1989 As of 31 August 2001 located at 107.28 deg W drifting at 0.248 deg W per day. As of 2007 Mar 9 located at 110.88W drifting at 0.246W degrees per day.

1981 August 3 - . 09:56 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 3913. FAILURE: Partial Failure.. Failed Stage: U.

Dynamics Explorer 1 - . Payload: DE A. Mass: 403 kg (888 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Dynamics Explorer. USAF Sat Cat: 12624 . COSPAR: 1981-070A. Apogee: 23,232 km (14,435 mi). Perigee: 528 km (328 mi). Inclination: 88.60 deg. Period: 409.20 min. Dynamics Explorer 1..

Dynamics Explorer 2 - . Payload: DE B. Mass: 403 kg (888 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Dynamics Explorer. Decay Date: 1983-02-19 . USAF Sat Cat: 12625 . COSPAR: 1981-070B. Apogee: 1,002 km (622 mi). Perigee: 304 km (188 mi). Inclination: 90.00 deg. Period: 97.80 min. Dynamics Explorer 2..

1981 August 10 - . 20:03 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-2.

Himawari 2 - . Payload: GMS 2. Mass: 670 kg (1,470 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Weather satellite. Spacecraft: Himawari. Completed Operations Date: 1988-02-01 . USAF Sat Cat: 12677 . COSPAR: 1981-076A. Apogee: 36,034 km (22,390 mi). Perigee: 35,943 km (22,333 mi). Inclination: 12.90 deg. Period: 1,446.40 min.
Geostationary meteorological satellite. N launch vehicle flight number 8 (N-II launch vehicle). Launch time 2003 UT. Launching organization: National Space Development Agency of Japan (NASDA). Geostationary longitude 140 deg E. Function: 1) Observation of meteorological phenomena by the visible and infra-red spin scan radiometer. 2) Collection of weather data from various stations. 3) Distribution of weather data to earth stations. 4) Monitoring of solar particles. Positioned in geosynchronous orbit at 160 deg E in 1981; 140 deg E in 1981-1984; 145 deg E in 1984-1985; 120 deg E in 1985-1988 As of 31 August 2001 located at 33.93 deg E drifting at 2.598 deg W per day. As of 2007 Mar 9 located at 153.66W drifting at 2.594W degrees per day.

1981 September 24 - . 23:09 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3910/PAM.

SBS 2 - . Mass: 550 kg (1,210 lb). Nation: USA. Agency: SBS. Program: SBS. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1996-09-07 . USAF Sat Cat: 12855 . COSPAR: 1981-096A. Apogee: 35,854 km (22,278 mi). Perigee: 35,781 km (22,233 mi). Inclination: 10.10 deg. Period: 1,437.70 min.
Positioned in geosynchronous orbit at 97 deg W in 1981-1983; 104 deg W in 1983; 97 deg W in 1983-1988; 99 deg W in 1988-1990; 97 deg W in 1990-1994; 71 deg W in 1994-1996 As of 31 August 2001 located at 125.63 deg E drifting at 0.458 deg W per day. As of 2007 Mar 9 located at 125.97W drifting at 0.561W degrees per day. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C).

1981 October 6 - . 11:27 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 2310.

SME - . Payload: Solar Mesosphere Explorer. Mass: 437 kg (963 lb). Nation: USA. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: SME. Decay Date: 1991-03-05 . USAF Sat Cat: 12887 . COSPAR: 1981-100A. Apogee: 337 km (209 mi). Perigee: 335 km (208 mi). Inclination: 97.60 deg. Period: 91.30 min. Solar Mesosphere Explorer. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

Oscar 9 - . Payload: UoSAT 1. Mass: 52 kg (114 lb). Nation: UK. Agency: Surrey. Manufacturer: Surrey. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: SSTL-70. Decay Date: 1989-10-13 . USAF Sat Cat: 12888 . COSPAR: 1981-100B. Apogee: 374 km (232 mi). Perigee: 372 km (231 mi). Inclination: 97.60 deg. Period: 92.00 min.
University of Surrey research microsatellite. Radio science; also carried amateur radio package. Communication and geophysics research satellite. Launch time 1127 GMT. Also registered by the United States in ST/SG/SER.E/59, with category D and orbital parameters 95.3 min, 531 x 533 km x 97.5 deg. UoSAT-OSCAR 9 was launched piggyback with Solar Mesosphere Explorer satellite. Weight 52 kg. Box shaped 740 x 420 x 420 mm. Deployable gravity gradient boom. Firsts: First on-board computer (IHU - Integrated Housekeeping Unit) for battery and attitude management, remote control, and experiments. Built by the University of Surrey in the United Kingdom, UO-9 was UoSAT's first experimental satellite. It was a scientific and educational low-Earth orbit satellite containing many experiments and beacons but no amateur transponders. UO-9 was fully operational until it re-entered October 13, 1989 from a decaying orbit after nine years of service.

1981 November 20 - . 01:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3910/PAM.

RCA Satcom 3R - . Payload: Satcom 3R. Mass: 1,078 kg (2,376 lb). Nation: USA. Agency: RCA Amer. Manufacturer: Lockheed. Program: Satcom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1991-04-10 . USAF Sat Cat: 12967 . COSPAR: 1981-114A. Apogee: 35,840 km (22,260 mi). Perigee: 35,824 km (22,259 mi). Inclination: 8.20 deg. Period: 1,438.40 min. Positioned in geosynchronous orbit at 131 deg W in 1981-1991 As of 3 September 2001 located at 86.96 deg W drifting at 0.634 deg W per day. As of 2007 Mar 11 located at 140.04W drifting at 0.601W degrees per day..

1982 January 16 - . 01:55 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3910/PAM.

RCA Satcom 4 - . Payload: Satcom 4. Mass: 1,082 kg (2,385 lb). Nation: USA. Agency: RCA Amer. Manufacturer: Lockheed. Program: Satcom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1991-12-06 . USAF Sat Cat: 13035 . COSPAR: 1982-004A. Apogee: 35,994 km (22,365 mi). Perigee: 35,964 km (22,346 mi). Inclination: 1.90 deg. Period: 1,446.00 min. Positioned in geosynchronous orbit at 83 deg W in 1982-1987; 82 deg W in 1987-1991 As of 2 September 2001 located at 171.96 deg E drifting at 2.443 deg W per day. As of 2007 Mar 9 located at 101.04W drifting at 2.479W degrees per day..

1982 February 26 - . 00:04 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3910/PAM.

Westar 4 - . Mass: 1,072 kg (2,363 lb). Nation: USA. Agency: WUTC. Program: Westar. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1991-11-09 . USAF Sat Cat: 13069 . COSPAR: 1982-014A. Apogee: 35,943 km (22,333 mi). Perigee: 35,915 km (22,316 mi). Inclination: 2.00 deg. Period: 1,443.40 min.
TV, telephone. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 99 deg W in 1982-1991 As of 2 September 2001 located at 83.31 deg W drifting at 1.825 deg W per day. As of 2007 Mar 8 located at 112.98W drifting at 1.830W degrees per day.

1982 April 10 - . 06:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3910/PAM.

Insat 1A - . Mass: 1,152 kg (2,539 lb). Nation: India. Agency: ISRO. Program: Insat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Insat 1. Completed Operations Date: 1982-09-04 . USAF Sat Cat: 13129 . COSPAR: 1982-031A. Apogee: 35,829 km (22,263 mi). Perigee: 35,734 km (22,204 mi). Inclination: 13.30 deg. Period: 1,435.80 min.
Also carried transponders for domestic communications. Operational multipurpose satellite for telecommunications, meteorological, imaging and data relay, radio and television programme distribution and direct television broadcasting for community reception. Geosynchronous orbit longitude 74 E. A/AC.105/INF.391 was reissued as ST/SG/SER.E/79. Also registered by the United States as 1982-31A in ST/SG/SER.E/67, with category C and orbital parameters 1416.7 min, 35032 x 35783 km x 0.5 deg. Positioned in geosynchronous orbit at 73 deg E in 1982 As of 29 August 2001 located at 82.99 deg E drifting at 0.337 deg W per day. As of 2007 Mar 10 located at 39.55E drifting at 0.205W degrees per day.

1982 June 9 - . 00:24 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3910/PAM.

Westar 5 - . Mass: 1,072 kg (2,363 lb). Nation: USA. Agency: WUTC. Program: Westar. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1992-05-25 . USAF Sat Cat: 13269 . COSPAR: 1982-058A. Apogee: 36,157 km (22,466 mi). Perigee: 36,017 km (22,379 mi). Inclination: 1.40 deg. Period: 1,451.50 min.
Voice, TV coverage for Alaska, Hawaii, Puerto Rico, Virgin Islands. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 123 deg W in 1982-1992 As of 5 September 2001 located at 132.07 deg W drifting at 3.816 deg W per day. As of 2007 Mar 10 located at 135.75E drifting at 3.802W degrees per day.

1982 July 16 - . 17:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 3920.

Landsat 4 - . Payload: Landsat D. Mass: 1,942 kg (4,281 lb). Nation: USA. Agency: NASA Greenbelt. Program: Landsat. Class: Earth. Type: Earth resources satellite. Spacecraft Bus: MMS. Spacecraft: Landsat 4-5. USAF Sat Cat: 13367 . COSPAR: 1982-072A. Apogee: 705 km (438 mi). Perigee: 693 km (430 mi). Inclination: 98.20 deg. Period: 98.80 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

1982 August 26 - . 23:10 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 3920/PAM.

Anik D1 (Telesat 5) - . Payload: Anik D1. Mass: 2,800 kg (6,100 lb). Nation: Canada. Agency: Telesat. Program: Anik. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1991-12-16 . USAF Sat Cat: 13431 . COSPAR: 1982-082A. Apogee: 35,846 km (22,273 mi). Perigee: 35,820 km (22,250 mi). Inclination: 8.00 deg. Period: 1,438.50 min.
Telecommunications. Operating entity Telesat Canada. Longitude 104.5W. Anik D-1 Transmit frequencies (MHz): 3720, 3740, 3760, 3780, 3800, 3820, 3840, 3860, 3880, 3900, 3920, 3940, 3960, 3980, 4000, 4020, 4040, 4060, 4080, 4100, 4120, 4140, 4160, 4180. Power 8.9 watts on each frequency. Positioned in geosynchronous orbit at 104 deg W in 1982-1991 As of 2 September 2001 located at 94.37 deg E drifting at 0.637 deg W per day. As of 2007 Mar 10 located at 52.18E drifting at 0.631W degrees per day.

1982 September 3 - . 05:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1.

Kiku 4 - . Payload: ETS 3. Mass: 385 kg (848 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 13492 . COSPAR: 1982-087A. Apogee: 1,006 km (625 mi). Perigee: 988 km (613 mi). Inclination: 44.60 deg. Period: 105.10 min.
Engineering test satellite. Engineering Test Satellite III (ETS-III) launched 0500 GMT 3 Sep 1982 from Osaki launch site, Tanegashima. Launching organization: National Space Development Agency of Japan (NASDA). Verification of three axis attitude control function; verification of so lar array paddle deployment function; verification of active thermal control function; functional test of mission equipment in the space. N launch vehicle flight no 9.

1982 October 28 - . 01:28 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 3924.

RCA Satcom 5 - . Payload: Aurora 1. Mass: 590 kg (1,300 lb). Nation: USA. Agency: RCA Alas. Manufacturer: Lockheed. Program: Satcom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1992-09-23 . USAF Sat Cat: 13631 . COSPAR: 1982-105A. Apogee: 35,791 km (22,239 mi). Perigee: 35,782 km (22,233 mi). Inclination: 8.10 deg. Period: 1,436.10 min. Positioned in geosynchronous orbit at 143 deg W in 1982-1991; 105 deg W in 1992-2007..

1983 January 26 - . 02:17 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 3910.

IRAS - . Payload: IRAS / PIX 2 #. Mass: 1,073 kg (2,365 lb). Nation: USA. Agency: JPL, NIVR. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: IRAS. USAF Sat Cat: 13777 . COSPAR: 1983-004A. Apogee: 903 km (561 mi). Perigee: 885 km (549 mi). Inclination: 99.00 deg. Period: 102.90 min. All-sky survey of astronomical IR bodies. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

PIX 2 - . Payload: PIX II. Mass: 1,073 kg (2,365 lb). Nation: USA. Agency: NASA Greenbelt. Spacecraft: IRAS. USAF Sat Cat: 13778 . COSPAR: 1983-004B. Apogee: 887 km (551 mi). Perigee: 856 km (532 mi). Inclination: 100.03 deg. Period: 102.30 min.

1983 February 4 - . 08:37 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-2.

Sakura 2A - . Payload: CS-2A. Mass: 772 kg (1,701 lb). Nation: Japan. Agency: NASDA. Program: CS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CS-2. Completed Operations Date: 1990-12-04 . USAF Sat Cat: 13782 . COSPAR: 1983-006A. Apogee: 36,070 km (22,410 mi). Perigee: 35,994 km (22,365 mi). Inclination: 10.60 deg. Period: 1,448.70 min.
Business communications. Launch time 0837 GMT. Launching organization NASDA (National Space Development Agency of Japan). N launch vehicle No. 10(F) (N-II launch vehicle). Osaki launch site, NASDA Tanegashima Space Center, Kagoshima, Japan. Geostationary position 132 deg E. Estab lishment of domestic satellite telecommunications network mainly for natural disaster, emergency and for remote islands using submillimetre wavelength and microwavelength signals. Development of the technology of communications satellite. Positioned in geosynchronous orbit at 132 deg E in 1983-1988; 128 deg E in 1988-1990 As of 30 August 2001 located at 140.81 deg E drifting at 3.111 deg W per day. As of 2007 Mar 10 located at 31.02W drifting at 3.113W degrees per day.

1983 April 11 - . 21:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 3924.

RCA Satcom 6 - . Payload: Satcom 1R. Mass: 2,385 kg (5,258 lb). Nation: USA. Agency: RCA Amer. Manufacturer: Lockheed. Program: Satcom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1992-12-27 . USAF Sat Cat: 13984 . COSPAR: 1983-030A. Apogee: 35,953 km (22,340 mi). Perigee: 35,851 km (22,276 mi). Inclination: 7.00 deg. Period: 1,442.00 min. Positioned in geosynchronous orbit at 139 deg W in 1983-1991; 131 deg W in 1991-1992 As of 5 September 2001 located at 148.59 deg W drifting at 1.499 deg W per day. As of 2007 Mar 10 located at 90.26E drifting at 1.535W degrees per day..

1983 April 28 - . 22:26 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914.

GOES 6 - . Payload: GOES F. Mass: 836 kg (1,843 lb). Nation: USA. Agency: NOAA. Class: Earth. Type: Weather satellite. Spacecraft: GOES. Completed Operations Date: 1992-05-19 . USAF Sat Cat: 14050 . COSPAR: 1983-041A. Apogee: 35,820 km (22,250 mi). Perigee: 35,778 km (22,231 mi). Inclination: 10.10 deg. Period: 1,436.70 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 135 deg W in 1983-1984; 97 deg W in-108 deg W in 1984-1987; 135 deg W in 1987-1992 As of 5 September 2001 located at 75.78 deg W drifting at 0.054 deg W per day. As of 2007 Mar 10 located at 83.60W drifting at 0.139W degrees per day.

1983 May 26 - . 15:18 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 3914.

Exosat - . Mass: 510 kg (1,120 lb). Nation: Europe. Agency: ESA. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: Exosat. Decay Date: 1986-05-06 . USAF Sat Cat: 14095 . COSPAR: 1983-051A. Apogee: 191,878 km (119,227 mi). Perigee: 340 km (210 mi). Inclination: 72.50 deg. Period: 5,442.10 min.
X-ray experiments. Launch time 1518 UT. Launching agency ESA. EXOSAT is a space research satellite of the European Space Agency. The scientific objectives of the EXOSAT mission are to measure the position, structural features, spectral and temporal characteristics of cosmic X-ray sources in the energy range from less than 0.1 keV to greater than 50 keV.

1983 June 28 - . 23:08 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 3920/PAM.

Galaxy 1 - . Payload: HS 376. Mass: 1,218 kg (2,685 lb). Nation: USA. Agency: HCI. Program: Galaxy. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1994-03-10 . USAF Sat Cat: 14158 . COSPAR: 1983-065A. Apogee: 35,841 km (22,270 mi). Perigee: 35,815 km (22,254 mi). Inclination: 6.30 deg. Period: 1,438.20 min.
TV. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 134 deg W in 1983-1991; 133 deg W in 1991-1994 As of 31 August 2001 located at 92.66 deg W drifting at 0.600 deg W per day. As of 2007 Mar 9 located at 46.95W drifting at 0.505W degrees per day.

1983 July 28 - . 22:49 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3920/PAM.

Telstar 3A - . Payload: Telstar 301 -> Arabsat 1E. Mass: 625 kg (1,377 lb). Nation: USA. Agency: ATT. Program: Telstar series. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1996-09-29 . USAF Sat Cat: 14234 . COSPAR: 1983-077A. Apogee: 36,108 km (22,436 mi). Perigee: 35,885 km (22,297 mi). Inclination: 6.50 deg. Period: 1,446.80 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 96 deg W in 1983-1985; 105 deg W in 1985; 96 deg W in 1985-1994; 107 deg W in 1994; 20 deg E in 1995-1996 As of 5 September 2001 located at 143.88 deg W drifting at 2.714 deg W per day. As of 2007 Mar 11 located at 158.94W drifting at 2.690W degrees per day.

1983 August 5 - . 20:29 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-2.

Sakura 2B - . Payload: CS-2B. Mass: 670 kg (1,470 lb). Nation: Japan. Agency: NASDA. Program: CS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CS-2. Completed Operations Date: 1990-01-01 . USAF Sat Cat: 14248 . COSPAR: 1983-081A. Apogee: 36,210 km (22,490 mi). Perigee: 36,191 km (22,488 mi). Inclination: 5.10 deg. Period: 1,457.30 min.
CS-2b (Sakura 2b). Launch time 2029 GMT. Launching organization NASDA (National Space Development Agency of Japan). N launch vehicle flight no. 11 (N-II launch vehicle). Domestic satellite communications; development of communications satellite technolog y. Positioned in geosynchronous orbit at 136 deg E in 1983-1989; 128 deg E in 1989-1990 As of 4 September 2001 located at 154.41 deg E drifting at 5.251 deg W per day. As of 2007 Mar 10 located at 13.72E drifting at 5.257W degrees per day.

1983 September 8 - . 22:52 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 3924.

RCA Satcom 7 - . Payload: Satcom 2R. Mass: 1,121 kg (2,471 lb). Nation: USA. Agency: RCA Amer. Manufacturer: Lockheed. Program: Satcom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1995-03-05 . USAF Sat Cat: 14328 . COSPAR: 1983-094A. Apogee: 36,095 km (22,428 mi). Perigee: 35,963 km (22,346 mi). Inclination: 5.70 deg. Period: 1,448.50 min. Positioned in geosynchronous orbit at 72 deg W in 1983-1995 As of 4 September 2001 located at 143.00 deg E drifting at 3.084 deg W per day. As of 2007 Mar 10 located at 40.27E drifting at 3.104W degrees per day..

1983 September 22 - . 22:16 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3920/PAM.

Galaxy 2 - . Payload: HS 376. Mass: 1,218 kg (2,685 lb). Nation: USA. Agency: HCI. Program: Galaxy. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1994-05-21 . USAF Sat Cat: 14365 . COSPAR: 1983-098A. Apogee: 35,791 km (22,239 mi). Perigee: 35,785 km (22,235 mi). Inclination: 0.10 deg. Period: 1,436.20 min.
Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 74 deg W in 1983-1994 As of 4 September 2001 located at 110.16 deg W drifting at 0.457 deg W per day. As of 2007 Mar 10 located at 57.56E drifting at 0.460W degrees per day.

1984 January 23 - . 07:58 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-2.

Yuri 2A - . Payload: BS-2a. Mass: 670 kg (1,470 lb). Nation: Japan. Agency: NASDA. Manufacturer: Lockheed. Program: BS. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1989-07-01 . USAF Sat Cat: 14659 . COSPAR: 1984-005A. Apogee: 36,191 km (22,488 mi). Perigee: 36,072 km (22,414 mi). Inclination: 4.90 deg. Period: 1,453.80 min.
TV. BS-2a (Yuri-2a). Domestic satellite broadcasting; development of broadcasting satellite technology. Launch 0758 GMT. N launch vehicle flight no 12. Launching organization NASDA. Positioned in geosynchronous orbit at 110 deg E in 1984-1985; 108 deg E in 1985-1987; 110 deg E in 1987-1988 As of 28 August 2001 located at 69.57 deg E drifting at 4.403 deg W per day. As of 2007 Mar 10 located at 153.52W drifting at 4.395W degrees per day.

1984 March 1 - . 17:59 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 3920.

Landsat 5 - . Payload: Landsat D'. Mass: 1,938 kg (4,272 lb). Nation: USA. Agency: NOAA. Program: Landsat. Class: Earth. Type: Earth resources satellite. Spacecraft Bus: MMS. Spacecraft: Landsat 4-5. USAF Sat Cat: 14780 . COSPAR: 1984-021A. Apogee: 703 km (436 mi). Perigee: 702 km (436 mi). Inclination: 98.20 deg. Period: 98.80 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C)..

Oscar 11 - . Payload: UoSAT 2. Mass: 52 kg (114 lb). Nation: UK. Agency: Surrey. Manufacturer: Surrey. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: SSTL-70. USAF Sat Cat: 14781 . COSPAR: 1984-021B. Apogee: 670 km (410 mi). Perigee: 651 km (404 mi). Inclination: 97.80 deg. Period: 98.00 min.
University of Surrey experimental microsatellite. Built in only 6 months, UoSAT-2 carried the first modern digital store and forward (S&F) communications payload and a prototype CCD camera. Also performed magnetospheric studies. Launch time 1759 GMT. Still operational in 2000.

1984 August 2 - . 20:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-2.

Himawari 3 - . Payload: GMS 3. Mass: 303 kg (668 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Weather satellite. Spacecraft: Himawari. Completed Operations Date: 1995-06-22 . USAF Sat Cat: 15152 . COSPAR: 1984-080A. Apogee: 35,942 km (22,333 mi). Perigee: 35,877 km (22,292 mi). Inclination: 9.80 deg. Period: 1,442.40 min.
Stationed at 140 deg E; also studied alpha particles, electrons. GMS-3 (Himawari-3). Launch 2030 GMT. Improvement of meteorological observation. Development of meteorological satellite technology. N Launch vehicle flight no 13. Launching organization NASDA. Positioned in geosynchronous orbit at 140 deg E in 1984-1989; 120 deg E in 1989-1995 As of 28 August 2001 located at 146.92 deg E drifting at 1.558 deg W per day. As of 2007 Mar 11 located at 168.90W drifting at 1.566W degrees per day.

1984 August 16 - . 14:48 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3924.

CCE-1 - . Payload: Charge Composition Explorer 1. Mass: 242 kg (533 lb). Nation: USA. Agency: NASA. Class: Earth. Type: Magnetosphere satellite. Spacecraft: AMPTE. USAF Sat Cat: 15199 . COSPAR: 1984-088A. Apogee: 49,671 km (30,864 mi). Perigee: 1,121 km (696 mi). Inclination: 4.80 deg. Period: 939.50 min. Charge Composition Explorer; detected tracer ions released into magnetosphere by IRM. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

AMPTE 3 - . Payload: AMPTE-UKS UK Subsatellite. Mass: 77 kg (169 lb). Nation: UK. Agency: SRC. Class: Earth. Type: Magnetosphere satellite. Spacecraft: AMPTE. Decay Date: 1990-02-21 . USAF Sat Cat: 15201 . COSPAR: 1984-088C. Apogee: 113,417 km (70,473 mi). Perigee: 1,002 km (622 mi). Inclination: 26.90 deg. Period: 2,659.60 min. Detected tracer ions released into magnetosphere by IRM. Magnetosphere research satellite. Launch time 1447 GMT. (Document quotes geocentric distances, which have been converted to orbital heights.).

AMPTE 2 - . Payload: AMPTE-IRM Ion Release Module 1. Mass: 605 kg (1,333 lb). Nation: Germany. Agency: DLR. Class: Earth. Type: Magnetosphere satellite. Spacecraft: AMPTE. Decay Date: 1987-12-08 . USAF Sat Cat: 15200 . COSPAR: 1984-088B. Apogee: 113,818 km (70,723 mi). Perigee: 402 km (249 mi). Inclination: 27.00 deg. Period: 2,653.40 min.
Released barium, lithium ions into magnetosphere for detection by CCE, UKS. AMPTE-Ion Release Module, reg. no. D-R 002. Scientific research on the Earth's magnetosphere and plasma physics, in particular active experimentation by releasing ion clouds of lithium or barium (total of 7) in and outside the magnetosphere. Creation of a n artificial comet (1 barium cloud inside the magnetosheath). Diagnosis and experimentation in conjunction with the simultaneously launched satellites CCE (United States) and UKS (United Kingdom).

Solar Cell Experiment - . Payload: STP. Nation: USA. Agency: NASA Greenbelt. Spacecraft: AMPTE. USAF Sat Cat: 15202 . COSPAR: 1984-088D. Apogee: 4,019 km (2,497 mi). Perigee: 546 km (340 mi). Inclination: 28.92 deg. Period: 133.62 min.

1984 September 21 - . 22:18 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 3920/PAM.

Galaxy 3 - . Payload: HS 376. Mass: 1,218 kg (2,685 lb). Nation: USA. Agency: HCI. Program: Galaxy. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1995-10-03 . USAF Sat Cat: 15308 . COSPAR: 1984-101A. Apogee: 35,931 km (22,326 mi). Perigee: 35,885 km (22,297 mi). Inclination: 5.70 deg. Period: 1,442.30 min.
Geostationary at 3.5 deg W. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 94 deg W in 1984-1995 As of 1 September 2001 located at 138.23 deg E drifting at 1.543 deg W per day. As of 2007 Mar 10 located at 125.04W drifting at 1.587W degrees per day.

1984 November 14 - . 00:34 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914.

NATO 3D - . Mass: 320 kg (700 lb). Nation: NATO. Agency: NATO. Program: NATO. Class: Communications. Type: Military communications satellite. Spacecraft: NATO 3. USAF Sat Cat: 15391 . COSPAR: 1984-115A. Apogee: 35,796 km (22,242 mi). Perigee: 35,779 km (22,231 mi). Inclination: 2.20 deg. Period: 1,436.20 min.
Stationed at 138 deg W. Positioned in geosynchronous orbit at 30 deg W in 1985; 50 deg W in 1985-1986; 21 deg W in 1986-1991; 30 deg W in 1991-1993; 21 deg W in1993-1997; 18 deg W in 1997-1999 As of 31 August 2001 located at 19.33 deg W drifting at 0.021 deg W per day. As of 2007 Mar 10 located at 120.20W drifting at 19.149W degrees per day.

1986 February 12 - . 07:55 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-2.

Yuri 2B - . Payload: BS-2b. Mass: 677 kg (1,492 lb). Nation: Japan. Agency: NASDA. Manufacturer: Lockheed. Program: BS. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1991-10-24 . USAF Sat Cat: 16597 . COSPAR: 1986-016A. Apogee: 36,135 km (22,453 mi). Perigee: 35,996 km (22,366 mi). Inclination: 2.70 deg. Period: 1,450.40 min.
Stationed at 117 deg E. BS-2b (Yuri-2b). Domestic satellite broadcasting; development of broadcasting satellite technology. Launching organization NASDA. N launch vehicle flight no 14. Launch time 0755 GMT. Positioned in geosynchronous orbit at 110 deg E in 1986-1991 As of 5 September 2001 located at 13.60 deg W drifting at 3.524 deg W per day. As of 2007 Mar 11 located at 77.04E drifting at 3.551W degrees per day.

1986 May 3 - . 22:18 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3914. FAILURE: Stage one main engine shutdown at T+71 seconds due to electrical failure.. Failed Stage: 1.

GOES G - . Payload: GOES G. Mass: 836 kg (1,843 lb). Nation: USA. Agency: NOAA. Class: Earth. Type: Weather satellite. Spacecraft: GOES. Decay Date: 1986-04-26 .

1986 August 12 - . 20:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: H-1.

EGS - . Payload: EGP. Mass: 685 kg (1,510 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Geodetic satellite. Spacecraft: EGS. USAF Sat Cat: 16908 . COSPAR: 1986-061A. Apogee: 1,497 km (930 mi). Perigee: 1,479 km (919 mi). Inclination: 50.00 deg. Period: 115.70 min.
Experimental Geophysical Payload; new launch vehicle test flight. EGS (Ajisai). Improvement of the accuracy of domestic geodetic triangulation network. Determination of accurate location of remote islands. Clarification of the relationship between Japanese geodetic system network and those of other areas of the world. L aunch vehicle H-I (two-stage) test flight no. 1. Launch time 2045 GMT. Launching organization NASDA.

Oscar 12 - . Payload: JAS-1. Mass: 50 kg (110 lb). Nation: Japan. Agency: JARL. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Oscar. USAF Sat Cat: 16909 . COSPAR: 1986-061B. Apogee: 1,497 km (930 mi). Perigee: 1,479 km (919 mi). Inclination: 50.00 deg. Period: 115.70 min.
Japanese Amateur Satellite. JAS-1 (Fuji). Amateur satellite communications. Development of amateur satellite technology. Launch vehicle H-I (two-stage) test flight no. 1. Launch time 2045 GMT. Launching organization NASDA. Fuji-OSCAR 12 was launched piggyback with a Japanese experimental geodetic satellite Ajisai (EGS). Weight 50 kg. 26-sided polyhedron, 40 x 40 x 47 cm. FO-12 was the first Japanese amateur satellite developed by the Japan Amateur Radio League (English version) with system design and integration performed at NEC. FO-12 was taken out of service November 5, 1989 because of battery failure.

MABES - . Payload: Jindai/LE-5. Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: MABES. USAF Sat Cat: 16910 . COSPAR: 1986-061C. Apogee: 1,604 km (996 mi). Perigee: 1,483 km (921 mi). Inclination: 50.00 deg. Period: 117.00 min. MABES (Jindai). Experiment on the levitation of the magnetic bearing flywheel under zero-g condition. .

1986 September 5 - . 15:08 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 3920.

USA 19 - . Payload: Delta 180 / Payload Adapter System. Mass: 6,000 kg (13,200 lb). Nation: USA. Agency: SDIO. Class: Military. Type: Strategic defense satellite. Spacecraft: SDI. Decay Date: 1986-09-28 . USAF Sat Cat: 16937 . COSPAR: 1986-069A. Apogee: 748 km (464 mi). Perigee: 213 km (132 mi). Inclination: 39.10 deg. Period: 94.20 min. SDIO sensor tests. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

Delta 180 Sensor Module - . Payload: DM 43 Sensor Module. Mass: 6,000 kg (13,200 lb). Nation: USA. Agency: SDIO. Spacecraft: SDI. Decay Date: 1986-11-25 . USAF Sat Cat: 16938 . COSPAR: 1986-069B. Apogee: 539 km (334 mi). Perigee: 215 km (133 mi). Inclination: 22.70 deg. Period: 92.09 min.

1987 February 19 - . 01:23 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-2.

MOS-1 - . Payload: Momo 1. Mass: 745 kg (1,642 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Sea satellite. Spacecraft: Marine Observation Satellite. USAF Sat Cat: 17527 . COSPAR: 1987-018A. Apogee: 909 km (564 mi). Perigee: 907 km (563 mi). Inclination: 99.10 deg. Period: 103.20 min. Ocean remote sensing. MOS-1 (Momo-1). Observation of marine phenomena such as sea color and temperature. Establishment of common technology necessary for Earth observation satellites. Launching organization NASDA. Launch time 0123 GMT..

1987 February 26 - . 23:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 3924.

GOES 7 - . Payload: GOES H. Mass: 399 kg (879 lb). Nation: USA. Agency: NOAA. Class: Earth. Type: Weather satellite. Spacecraft: GOES. Completed Operations Date: 1998-01-01 . USAF Sat Cat: 17561 . COSPAR: 1987-022A. Apogee: 35,797 km (22,243 mi). Perigee: 35,777 km (22,230 mi). Inclination: 1.20 deg. Period: 1,436.20 min.
Stationed at 83 deg W. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 75 deg W in 1987-1988; 108 deg W in-98 deg W in 1989-1992; 111 deg W in 1992; 112 deg W in 1993-1994; 135 deg W in 1995; 98 deg W in 1996-1998 As of 5 September 2001 located at 179.83 deg E drifting at 0.023 deg W per day. As of 2007 Mar 9 located at 176.12W drifting at 0.061W degrees per day.

1987 March 20 - . 22:22 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 3920/PAM.

Palapa B2P - . Mass: 1,200 kg (2,600 lb). Nation: Indonesia. Agency: Perumtel. Program: Palapa. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1998-01-18 . USAF Sat Cat: 17706 . COSPAR: 1987-029A. Apogee: 35,906 km (22,310 mi). Perigee: 35,868 km (22,287 mi). Inclination: 5.00 deg. Period: 1,441.20 min.
Stationed at 113 deg W. Positioned in geosynchronous orbit at 113 deg E in 1987-1996; 144 deg E in 1996-1998 As of 28 August 2001 located at 130.30 deg W drifting at 1.327 deg W per day. As of 2007 Mar 3 located at 141.38E drifting at 1.274W degrees per day.

1987 August 27 - . 09:20 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: H-1.

Kiku 5 - . Payload: ETS 5. Mass: 550 kg (1,210 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. Completed Operations Date: 1997-09-10 . USAF Sat Cat: 18316 . COSPAR: 1987-070A. Apogee: 36,072 km (22,414 mi). Perigee: 36,029 km (22,387 mi). Inclination: 7.90 deg. Period: 1,449.60 min.
Stationed at 150 deg E. ETS-V (Kiku-5). Establishment of basic technology for bus systems needed for 3-axis stabilized geostationary satellites. Accumulation of key technologies required for high performance in the next generation of applications satellites; Experiment of mobile satellite communications for the control of aircrafts over the Pacific Ocean, and for the communication, navigational aid, search and rescue of ships. H-I (3-stage) launch vehicle. Launching organization NASDA. Launch time 0920 GMT. Positioned in geosynchronous orbit at 150 deg E in 1987-1997 As of 5 September 2001 located at 92.55 deg W drifting at 3.394 deg W per day. As of 2007 Mar 10 located at 49.74W drifting at 3.380W degrees per day.

1988 February 8 - . 22:08 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 3910.

USA 30 - . Payload: Delta 181 Canister Cluster. Mass: 6,000 kg (13,200 lb). Nation: USA. Agency: SDIO. Class: Military. Type: Strategic defense satellite. Spacecraft: SDI. Decay Date: 1988-03-01 . USAF Sat Cat: 18847 . COSPAR: 1988-008A. Apogee: 342 km (212 mi). Perigee: 225 km (139 mi). Inclination: 28.60 deg. Period: 90.20 min. Military tracking exercise; released subsatellites. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

Delta 181 Subsatellite 4 - . Payload: Group 1 Test Object. Nation: USA. Agency: NASA. Spacecraft: SDI. COSPAR: 1988-008xx.

Solid Motor Subsatellite - . Payload: Group 2 Test Object. Nation: USA. Agency: NASA. Spacecraft: SDI. COSPAR: 1988-008xx.

Delta 181 Subsatellite 11 - . Payload: Group 2 Test Object. Nation: USA. Agency: NASA. Spacecraft: SDI. Decay Date: 1988-03-01 . USAF Sat Cat: 18847 . COSPAR: 1988-008xx. Apogee: 195 km (121 mi). Perigee: 168 km (104 mi). Inclination: 28.60 deg. Period: 88.10 min.

Delta 181 Subsatellite 10 - . Payload: Group 2 Test Object. Nation: USA. Agency: NASA. Spacecraft: SDI. Decay Date: 1988-03-01 . USAF Sat Cat: 18847 . COSPAR: 1988-008xx. Apogee: 195 km (121 mi). Perigee: 168 km (104 mi). Inclination: 28.60 deg. Period: 88.10 min.

Delta 181 Subsatellite 9 - . Payload: Group 2 Test Object. Nation: USA. Agency: NASA. Spacecraft: SDI. COSPAR: 1988-008xx.

Delta 181 Subsatellite 8 - . Payload: Group 2 Test Object. Nation: USA. Agency: NASA. Spacecraft: SDI. COSPAR: 1988-008xx.

Delta 181 Subsatellite 5 - . Payload: Group 1 Test Object. Nation: USA. Agency: NASA. Spacecraft: SDI. COSPAR: 1988-008xx.

Delta 181 Sensor Module - . Payload: Thrusted Vector Sensor Mo. Mass: 6,000 kg (13,200 lb). Nation: USA. Agency: SDIO. Spacecraft: SDI. Decay Date: 1988-04-02 . USAF Sat Cat: 18848 . COSPAR: 1988-008B. Apogee: 314 km (195 mi). Perigee: 287 km (178 mi). Inclination: 30.70 deg. Period: 90.53 min.

Delta 181 Subsatellite 3 - . Payload: Group 1 Test Object. Nation: USA. Agency: NASA. Spacecraft: SDI. COSPAR: 1988-008xx.

Delta 181 Subsatellite 2 - . Payload: Group 1 Test Object. Nation: USA. Agency: NASA. Spacecraft: SDI. COSPAR: 1988-008xx.

Sensor Cal Reference Subsat - . Payload: Group 1 Cal Object. Nation: USA. Agency: NASA. Spacecraft: SDI. COSPAR: 1988-008xx.

Delta 181 Subsatellite 7 - . Payload: Group 2 Test Object. Nation: USA. Agency: NASA. Spacecraft: SDI. COSPAR: 1988-008xx.

SPX - . Mass: 6,000 kg (13,200 lb). Nation: USA. Agency: NASA. Spacecraft: SDI. COSPAR: 1988-008xx.

Delta 181 Subsatellite 1 - . Payload: Group 1 Test Object. Nation: USA. Agency: NASA. Spacecraft: SDI. Decay Date: 1988-03-01 . USAF Sat Cat: 18847 . COSPAR: 1988-008xx. Apogee: 195 km (121 mi). Perigee: 168 km (104 mi). Inclination: 28.60 deg. Period: 88.10 min.

1988 February 19 - . 10:05 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: H-1.

Sakura 3A - . Payload: CS-3A. Mass: 1,100 kg (2,400 lb). Nation: Japan. Program: CS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CS-3. Completed Operations Date: 1996-09-28 . USAF Sat Cat: 18877 . COSPAR: 1988-012A. Apogee: 36,415 km (22,627 mi). Perigee: 36,376 km (22,602 mi). Inclination: 4.90 deg. Period: 1,467.30 min.
Stationed at 132 deg E. CS-3A (Sakura 3-A). To continue communications services provided by the communications satellite 2 (CS-2). To meet increasing and diversifying demands for communications. To develop technologies for communications satellites. Launch vehicle H18F. Launchin g organization NASDA. Launch time 1005 GMT. Positioned in geosynchronous orbit at 132 deg E in 1988-1996 As of 2 September 2001 located at 85.60 deg E drifting at 7.699 deg W per day. As of 2007 Mar 10 located at 71.73E drifting at 7.700W degrees per day.

1988 September 16 - . 09:59 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: H-1.

Sakura 3B - . Payload: CS-3B. Mass: 1,100 kg (2,400 lb). Nation: Japan. Program: CS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CS-3. Completed Operations Date: 1997-11-10 . USAF Sat Cat: 19508 . COSPAR: 1988-086A. Apogee: 36,093 km (22,427 mi). Perigee: 36,071 km (22,413 mi). Inclination: 4.00 deg. Period: 1,451.20 min.
Telephone communications; 136 deg E. CS-3B (Sakura 3-B). To continue communications services provided by the communications satellite 2 (CS-2). To meet increasing and diversifying demands for communications; to develop technologies for communications satellites. Launch vehicle H-I (H19F). La unching organization NASDA. Launch time 0959 GMT. Positioned in geosynchronous orbit at 149 deg E in 1988; 136 deg E in 1988-1997; 154 deg E in 1997 As of 28 August 2001 located at 128.96 deg W drifting at 3.783 deg W per day. As of 2007 Mar 10 located at 177.82E drifting at 3.765W degrees per day.

1989 February 14 - . 18:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 6925.

USA 35 - . Payload: GPS 2-1 / GPS SVN 14. Mass: 1,665 kg (3,670 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 19802 . COSPAR: 1989-013A. Apogee: 21,758 km (13,519 mi). Perigee: 21,480 km (13,340 mi). Inclination: 56.60 deg. Period: 777.00 min. First launch of second generation / operational Global Positioning System. Placed in Plane E Slot 1 of the constellation. Suffered a shutdown of its onboard reaction wheels on March 26, 2000. Decommissioned on April 14, 2000 and replaced by GPS 2R-4..

1989 March 24 - . 21:50 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 3920-8.

USA 36 - . Payload: Delta Star. Mass: 6,000 kg (13,200 lb). Nation: USA. Agency: SDIO. Class: Military. Type: Strategic defense satellite. Spacecraft: SDI. Decay Date: 1992-06-23 . USAF Sat Cat: 19911 . COSPAR: 1989-026A. Apogee: 312 km (193 mi). Perigee: 307 km (190 mi). Inclination: 47.70 deg. Period: 90.70 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). .

1989 June 10 - . 22:19 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 6925.

USA 38 - . Payload: GPS 2-2 / GPS SVN 13. Mass: 1,665 kg (3,670 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 20061 . COSPAR: 1989-044A. Apogee: 20,514 km (12,746 mi). Perigee: 19,849 km (12,333 mi). Inclination: 54.80 deg. Period: 718.00 min. Global Positioning System. Placed in Plane B Slot 3..

1989 August 18 - . 05:58 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 6925.

USA 42 - . Payload: GPS 2-3 / GPS SVN 16. Mass: 1,665 kg (3,670 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 20185 . COSPAR: 1989-064A. Apogee: 21,576 km (13,406 mi). Perigee: 21,509 km (13,365 mi). Inclination: 56.40 deg. Period: 773.80 min. Global Positioning System. Retired..

1989 August 27 - . 22:59 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 4925-8.

BSB-1A - . Payload: Marco Polo 1. Mass: 1,233 kg (2,718 lb). Nation: UK. Agency: BSB. Program: BSB. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 20193 . COSPAR: 1989-067A. Apogee: 35,795 km (22,241 mi). Perigee: 35,782 km (22,233 mi). Inclination: 0.10 deg. Period: 1,436.20 min.
British DBS; 31 deg W. Direct broadcasting system. Expected operational life, 10 years. Owner/operator: British Satellite Broadcasting Ltd, The Marcopolo Building, Chelsea Bridge, Queenstown Rd, London SW8 4NQ. Positioned in geosynchronous orbit at 31 deg W in 1989-1993; 5 deg E in 1994-2000; 13 deg W in 2000. As of 31 August 2001 located at 12.98 deg W drifting at 0.008 deg W per day. As of 2007 Mar 9 located at 45.02W drifting at 3.908W degrees per day.

1989 September 5 - . 19:11 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: H-1.

Himawari 4 - . Payload: GMS 4. Mass: 725 kg (1,598 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Weather satellite. Spacecraft: Himawari. Completed Operations Date: 2000-02-24 . USAF Sat Cat: 20217 . COSPAR: 1989-070A. Apogee: 36,807 km (22,870 mi). Perigee: 36,410 km (22,620 mi). Inclination: 6.20 deg. Period: 1,478.30 min.
Stationed at 140 deg E. GMS-4 (Himawari-4). Improvement of meteorological observation. Development of meteorological satellite technology. Launch vehicle H-I (H20F). Launching organization NASDA. Launch time 1911 GMT. Positioned in geosynchronous orbit at 160 deg E in 1989; 140 deg E in 1989-1995; 120 deg E in 1995-1999 As of 4 September 2001 located at 126.83 deg E drifting at 10.301 deg W per day. As of 2007 Mar 9 located at 71.28W drifting at 10.305W degrees per day.

1989 October 21 - . 09:31 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 6925.

USA 47 - . Payload: GPS 2-4 / GPS SVN 19. Mass: 1,665 kg (3,670 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 20302 . COSPAR: 1989-085A. Apogee: 21,236 km (13,195 mi). Perigee: 21,190 km (13,160 mi). Inclination: 53.30 deg. Period: 760.20 min. Global Positioning System. Placed in Plane A Slot 5..

1989 November 18 - . 14:34 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 5920-8.

COBE - . Mass: 2,265 kg (4,993 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: COBE. USAF Sat Cat: 20322 . COSPAR: 1989-089A. Apogee: 886 km (550 mi). Perigee: 873 km (542 mi). Inclination: 98.90 deg. Period: 102.60 min. Cosmic Background Explorer; measured background galactic infrared radiation. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

1989 December 11 - . 18:10 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 6925.

USA 49 - . Payload: GPS 2-5 / GPS SVN 17. Mass: 1,665 kg (3,670 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 20361 . COSPAR: 1989-097A. Apogee: 20,371 km (12,657 mi). Perigee: 19,992 km (12,422 mi). Inclination: 55.40 deg. Period: 718.00 min. Global Positioning System. Placed in Plane D Slot 3..

1990 January 24 - . 22:55 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 6925.

USA 50 - . Payload: GPS 2-6 / GPS SVN 18. Mass: 1,665 kg (3,670 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 20452 . COSPAR: 1990-008A. Apogee: 21,226 km (13,189 mi). Perigee: 21,168 km (13,153 mi). Inclination: 55.00 deg. Period: 759.50 min. Global Positioning System. Retired..

1990 February 7 - . 01:33 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: H-1.

MOS-1b - . Payload: Momo 1B. Mass: 740 kg (1,630 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Sea satellite. Spacecraft: Marine Observation Satellite. USAF Sat Cat: 20478 . COSPAR: 1990-013A. Apogee: 909 km (564 mi). Perigee: 908 km (564 mi). Inclination: 99.10 deg. Period: 103.20 min. Marine observation. Continuation of Earth observation functions of MOS-1; establishment of common technology necessary for Earth-observation satellites. Launching organization NASDA. Name MOS-1b 'Momo-1b'. Launch time 0133 UT..

Debut - . Payload: Orizuru. Mass: 50 kg (110 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: Debut. USAF Sat Cat: 20479 . COSPAR: 1990-013B. Apogee: 1,743 km (1,083 mi). Perigee: 911 km (566 mi). Inclination: 99.00 deg. Period: 112.20 min. Boom, umbrella test. DEBUT 'Orizuru'. Experiment of extending and contracting boom; experiment of expanding and contracting aerodynamic brake. Launching organization NASDA. Launch time 0133 UT..

Oscar 20 - . Payload: JAS 1b. Mass: 50 kg (110 lb). Nation: Japan. Agency: JARL. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Oscar. USAF Sat Cat: 20480 . COSPAR: 1990-013C. Apogee: 1,745 km (1,084 mi). Perigee: 912 km (566 mi). Inclination: 99.00 deg. Period: 112.20 min. JAS-1b 'Fuji-2'. Continuation of amateurradio services of JAS-1; extension of amateur radio communications area; advancement of amateur radio technology. Launching organization NASDA. Launch time 0133 UT..

1990 February 14 - . 16:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 6920-8.

USA 51 - . Payload: LACE. Mass: 1,430 kg (3,150 lb). Nation: USA. Agency: SDIO. Class: Military. Type: Strategic defense satellite. Spacecraft: LACE. Decay Date: 2000-05-24 . USAF Sat Cat: 20496 . COSPAR: 1990-015A. Apogee: 480 km (290 mi). Perigee: 463 km (287 mi). Inclination: 43.10 deg. Period: 94.00 min.
Low-power Atmospheric Compensation Experiment for SDIO. Research and exploration of the upper atmosphere and outer space. The McDonnell Douglas Corporation has provided the following information for its launch of the Losat spacecraft on 14 Feb 1990: LACE spacecraft (Losat-L), launch time 1615:00.626 GMT, ETR Launch Complex 17. Programmed orbital parameters 95.6 min, apogee 551 km, inc. 43.1 deg. Evaluate laser beam distortion in space.

USA 52 - . Payload: RME. Mass: 1,040 kg (2,290 lb). Nation: USA. Agency: SDIO. Class: Military. Type: Strategic defense satellite. Spacecraft: RME. Decay Date: 1992-05-24 . USAF Sat Cat: 20497 . COSPAR: 1990-015B. Apogee: 281 km (174 mi). Perigee: 261 km (162 mi). Inclination: 43.10 deg. Period: 89.90 min.
Relay Mirror Experiment; also known as Losat-R. RME validated stabilization, tracking, and pointing technologies for Strategic Defense Initiative (SDI) missions through a credible demonstration of a space-based relay mirror system. The Wideband Angular Vibration Experiment (WAVE) measured low-level angular vibrations affecting performance of acquisition, tracking, and pointing systems. The experiment demonstrated that a laser beam can be accurately relayed from the earth to an orbiting satellite 450 kilometers away and then back to a 3-meter target on the ground. It achieved relay beam pointing accuracy which was 16 times better than the technical requirement. WAVE demonstrated the capability to discern platform disturbance amplitudes of a few nanoradians at discrete frequencies and is therefore a candidate to fulfill similar requirements for future ATP experiments.

1990 March 26 - . 02:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 6925.

USA 54 - . Payload: GPS 2-7 / GPS SVN 20. Mass: 1,665 kg (3,670 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 20533 . COSPAR: 1990-025A. Apogee: 21,156 km (13,145 mi). Perigee: 20,960 km (13,020 mi). Inclination: 53.70 deg. Period: 753.80 min. Global Positioning System. Declared unusable on 21 May 1996 at 22:42 following two uncommanded changes in frequency standards..

1990 April 13 - . 22:28 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 6925-8.

Palapa B2R - . Mass: 1,200 kg (2,600 lb). Nation: Indonesia. Agency: Perumtel. Program: Palapa. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 20570 . COSPAR: 1990-034A. Apogee: 35,795 km (22,241 mi). Perigee: 35,784 km (22,235 mi). Inclination: 0.00 deg. Period: 1,436.30 min.
Refurbished Palapa B2 retrieved by STS-51A; 107.7 deg E. Communication services for Indonesia, the Association of South-East Asian Nations (ASEAN), and Papua New Guinea. Launch time 2227:59.719 Z. Launch complex 17, ETR. Positioned in geosynchronous orbit at 108 deg E in 1990-1999 As of 29 August 2001 located at 42.49 deg E drifting at 0.002 deg E per day. As of 2007 Mar 9 located at 163.55E drifting at 2.663W degrees per day.

1990 June 1 - . 21:48 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 6920-10.

ROSAT - . Mass: 2,426 kg (5,348 lb). Nation: Germany. Agency: DLR. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: ROSAT. Decay Date: 2011-10-23 . USAF Sat Cat: 20638 . COSPAR: 1990-049A. Apogee: 554 km (344 mi). Perigee: 539 km (334 mi). Inclination: 53.00 deg. Period: 95.60 min. West German extreme UV, X-ray telescope; all-sky survey..

1990 June 12 - . 05:52 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 4925-8.

Insat 1D - . Mass: 1,190 kg (2,620 lb). Nation: India. Agency: ISRO. Program: Insat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Insat 1. USAF Sat Cat: 20643 . COSPAR: 1990-051A. Apogee: 35,851 km (22,276 mi). Perigee: 35,729 km (22,200 mi). Inclination: 3.70 deg. Period: 1,436.30 min.
Also performed Indian domestic communications tasks; 83.1 E. Operational multi-purpose satellite for telecommunications, meteorological imaging and data relay, radio and television programme distribution and direct television broadcasting for community reception. Orbital position 83 deg E. Also registered as 1990-5 1A in ST/SG/SER.E/250 by the United States, with category B and orbital parameters 1426.3 min, 35768 x 35811 km x 0.2 deg. Positioned in geosynchronous orbit at 83 deg E in 1990-1999; 74 deg E in 1999-2000 As of 5 September 2001 located at 73.85 deg E drifting at 0.000 deg E per day. As of 2007 Mar 10 located at 71.63E drifting at 0.039E degrees per day.

1990 August 2 - . 05:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 6925.

USA 63 - . Payload: GPS 2-8 / GPS SVN 21. Mass: 1,665 kg (3,670 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 20724 . COSPAR: 1990-068A. Apogee: 20,468 km (12,718 mi). Perigee: 19,896 km (12,362 mi). Inclination: 54.70 deg. Period: 718.00 min. Global Positioning System. Placed in Plane E Slot 2..

1990 August 18 - . 00:42 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 6925.

Thor 1 / BSB-R2 - . Payload: Marco Polo 2. Mass: 1,220 kg (2,680 lb). Nation: Norway. Agency: BSB. Program: Thor Comsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 20762 . COSPAR: 1990-074A. Apogee: 35,794 km (22,241 mi). Perigee: 35,779 km (22,231 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
UK DBS; 31 deg W. Direct broadcasting system. Expected operational life 12.5 yr. Owner/operator: British Sky Broadcasting Ltd, 6 Centaurs Business Park, Grant Way, Isleworth, Middlesex TW7 5QD. Sold on-orbit in 1992 to Telenor Norway and redesignated Thor 1. Positioned in geosynchronous orbit at 50 deg W in 1990; 31 deg W in 1991-1992; 1 deg W in 1992-1999 As of 3 September 2001 located at 0.72 deg W drifting at 0.001 deg E per day. As of 2007 Mar 9 located at 61.51W drifting at 3.830W degrees per day.

1990 August 28 - . 09:05 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: H-1.

Yuri 3A - . Payload: BS-3a. Mass: 1,115 kg (2,458 lb). Nation: Japan. Manufacturer: Lockheed. Program: BS. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1998-04-20 . USAF Sat Cat: 20771 . COSPAR: 1990-077A. Apogee: 36,245 km (22,521 mi). Perigee: 36,157 km (22,466 mi). Inclination: 3.50 deg. Period: 1,457.30 min.
Japanese DBS; 110 deg E. Continuation of broadcasting services by BS-2; accommodations to increasing and diversifying demands for broadcasting; establishment of common technology necessary for broadcasting satellite. Launching organization NASDA. Launch time 0905 GMT. BS-3a 'Yuri -3a'. Positioned in geosynchronous orbit at 110 deg E in 1990-1998 As of 2 September 2001 located at 84.62 deg E drifting at 5.278 deg W per day. As of 2007 Mar 10 located at 83.70W drifting at 5.275W degrees per day.

1990 October 1 - . 21:56 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 6925.

USA 64 - . Payload: GPS 2-9 / GPS SVN 15. Mass: 1,665 kg (3,670 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 20830 . COSPAR: 1990-088A. Apogee: 20,363 km (12,652 mi). Perigee: 20,002 km (12,428 mi). Inclination: 55.40 deg. Period: 718.00 min. Global Positioning System. Placed in Plane D Slot 5..

1990 October 30 - . 23:16 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 6925.

Inmarsat 2 F1 - . Mass: 1,385 kg (3,053 lb). Nation: International. Agency: Inmarsat. Manufacturer: Toulouse. Program: Inmarsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Eurostar 1000. USAF Sat Cat: 20918 . COSPAR: 1990-093A. Apogee: 35,800 km (22,200 mi). Perigee: 35,775 km (22,229 mi). Inclination: 1.70 deg. Period: 1,436.20 min.
Mobile communications; 64.5 deg E. Positioned in geosynchronous orbit at 65 deg E in 1990-1996; 179 deg E in 1996-1999 As of 5 September 2001 located at 178.97 deg E drifting at 0.004 deg W per day. As of 2007 Mar 8 located at 143.50E drifting at 0.015W degrees per day.

1990 November 26 - . 21:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 66 - . Payload: GPS 2A-10 / GPS SVN 23. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 20959 . COSPAR: 1990-103A. Apogee: 20,384 km (12,666 mi). Perigee: 19,978 km (12,413 mi). Inclination: 54.90 deg. Period: 717.90 min. Global Positioning System. Placed in Plane E Slot 5..

1991 January 8 - . 00:53 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

NATO 4A - . Payload: NATO 4A. Mass: 1,433 kg (3,159 lb). Nation: NATO. Agency: NATO. Program: NATO. Class: Communications. Type: Military communications satellite. Spacecraft: ECS/OTS. USAF Sat Cat: 21047 . COSPAR: 1991-001A. Apogee: 35,800 km (22,200 mi). Perigee: 35,775 km (22,229 mi). Inclination: 2.60 deg. Period: 1,436.10 min.
NATO communications; 18 deg W. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 18 deg W in 1991-1999 As of 5 September 2001 located at 17.81 deg W drifting at 0.007 deg W per day. As of 2007 Mar 10 located at 16.26W drifting at 0.003W degrees per day.

1991 March 8 - . 23:03 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 6925.

Inmarsat 2 F2 - . Mass: 1,385 kg (3,053 lb). Nation: International. Agency: Inmarsat. Manufacturer: Toulouse. Program: Inmarsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Eurostar 1000. USAF Sat Cat: 21149 . COSPAR: 1991-018A. Apogee: 35,793 km (22,240 mi). Perigee: 35,780 km (22,230 mi). Inclination: 2.20 deg. Period: 1,436.10 min.
Mobile and maritime communications; 15.5 deg W. Positioned in geosynchronous orbit at 15 deg W in 1991-1996; 55 deg W in 1997-1999; DRIFT As of 6 September 2001 located at 97.95 deg W drifting at 0.002 deg W per day. As of 2007 Mar 11 located at 97.96W drifting at 0.006W degrees per day.

1991 April 13 - . 00:09 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

ASC-2 / Spacenet F4 - . Mass: 1,350 kg (2,970 lb). Nation: USA. Agency: Contel. Program: GTE. Class: Communications. Type: Civilian communications satellite. Spacecraft Bus: AS 3000. Spacecraft: ASC. USAF Sat Cat: 21227 . COSPAR: 1991-028A. Apogee: 35,794 km (22,241 mi). Perigee: 35,780 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.20 min.
Commercial business communications; stationed at 101 deg W. C, Ku band communications satellite. Positioned in geosynchronous orbit at 101 deg W in 1991-1999; 81 deg W in 2000. As of 6 September 2001 located at 172.04 deg E drifting at 0.007 deg W per day. As of 2007 Mar 9 located at 34.51E drifting at 2.539W degrees per day.

1991 May 29 - . 22:55 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

Aurora 2 - . Payload: Satcom-C 5. Mass: 1,336 kg (2,945 lb). Nation: USA. Agency: GE. Manufacturer: Lockheed. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. USAF Sat Cat: 21392 . COSPAR: 1991-037A. Apogee: 36,161 km (22,469 mi). Perigee: 36,125 km (22,446 mi). Inclination: 1.20 deg. Period: 1,454.40 min.
Stationed at 139 deg W. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). Positioned in geosynchronous orbit at 139 deg W in 1991-1999 As of 30 August 2001 located at 148.31 deg E drifting at 4.531 deg W per day. As of 2007 Mar 9 located at 2.15E drifting at 4.534W degrees per day.

1991 July 4 - . 02:32 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 71 - . Payload: GPS 2A-11 / GPS SVN 24. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 21552 . COSPAR: 1991-047A. Apogee: 20,319 km (12,625 mi). Perigee: 20,043 km (12,454 mi). Inclination: 55.60 deg. Period: 717.90 min. Global Positioning System. Placed in Plane D Slot 1..

Losat X - . Mass: 75 kg (165 lb). Nation: USA. Agency: SDIO. Class: Military. Type: Strategic defense satellite. Spacecraft: Losat. Decay Date: 1991-11-15 . USAF Sat Cat: 21553 . COSPAR: 1991-047B. Apogee: 417 km (259 mi). Perigee: 405 km (251 mi). Inclination: 40.00 deg. Period: 92.80 min. Test flight of DOD sensors; Low Altitude Satellite Experiment. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

1991 August 25 - . 08:40 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: H-1.

Yuri 3B - . Payload: BS-3b. Mass: 1,115 kg (2,458 lb). Nation: Japan. Manufacturer: Lockheed. Program: BS. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1999-04-05 . USAF Sat Cat: 21668 . COSPAR: 1991-060A. Apogee: 36,244 km (22,520 mi). Perigee: 36,171 km (22,475 mi). Inclination: 3.20 deg. Period: 1,457.70 min. TV; 110 deg E. Positioned in geosynchronous orbit at 110 deg E in 1991-1999 As of 3 September 2001 located at 91.59 deg E drifting at 5.350 deg W per day. As of 2007 Mar 9 located at 152.69E drifting at 5.334W degrees per day..

1992 February 11 - . 01:50 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: H-1.

JERS-1 - . Payload: ERS-1. Mass: 1,340 kg (2,950 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Earth resources satellite. Spacecraft: JERS. Completed Operations Date: 1998-10-12 . Decay Date: 2001-12-03 . USAF Sat Cat: 21867 . COSPAR: 1992-007A. Apogee: 568 km (352 mi). Perigee: 567 km (352 mi). Inclination: 97.70 deg. Period: 96.00 min.
Japanese Research Satellite-1. JERS-1 (FUYO-1). To verify functions and performance of optical sensors and a Synthetic Aperture Radar and to establish an integrated system for observing the Earth's resources; to perform observations and measurements for land survey, agriculture, forest ry, fishery, environmental preservation, disaster prevention and coastal surveillance. Launch time 0150 GMT. Launching organization NASDA. The Japanese Fuyo-1 (ERS-1) satellite failed on Oct 12, 1998 after six years of operation.

1992 February 23 - . 22:29 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 79 - . Payload: GPS 2A-12 / GPS SVN 25. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 21890 . COSPAR: 1992-009A. Apogee: 20,332 km (12,633 mi). Perigee: 20,032 km (12,447 mi). Inclination: 54.20 deg. Period: 718.00 min. Global Positioning System. Placed in Plane A Slot 2..

1992 April 10 - . 03:20 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 80 - . Payload: GPS 2A-13 / GPS SVN 28. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 21930 . COSPAR: 1992-019A. Apogee: 20,277 km (12,599 mi). Perigee: 20,082 km (12,478 mi). Inclination: 54.50 deg. Period: 717.90 min. Global Positioning System. Retired 15 August 1997..

1992 May 14 - . 00:40 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

Palapa B4 - . Mass: 1,254 kg (2,764 lb). Nation: Indonesia. Agency: PT Telkom. Program: Palapa. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 21964 . COSPAR: 1992-027A. Apogee: 35,790 km (22,230 mi). Perigee: 35,787 km (22,236 mi). Inclination: 0.00 deg. Period: 1,436.20 min. Stationed at 118 deg E. Positioned in geosynchronous orbit at 118 deg E in 1992-1999 As of 2 September 2001 located at 118.02 deg E drifting at 0.020 deg W per day. As of 2007 Mar 9 located at 164.88E drifting at 1.157W degrees per day..

1992 June 7 - . 16:40 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 6920-10.

EUVE - . Mass: 3,275 kg (7,220 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft Bus: MMS. Spacecraft: EUVE. Decay Date: 2002-01-31 . USAF Sat Cat: 21987 . COSPAR: 1992-031A. Apogee: 524 km (325 mi). Perigee: 510 km (310 mi). Inclination: 28.40 deg. Period: 95.00 min.
Extreme Ultra-Violet Explorer; mapped galactic EUV sources. The Extreme Ultraviolet Explorer was switched off on February 2, 2001. NASA decided to terminate funding for the mission, even though the spacecraft was still operating well. The sky survey was completed in January 1993 and after that the EUVE was used by guest astronomers for observations of specific targets. The final observations were made on January 26, 2001. After end-of-life tests of the never-used backup high voltage supplies and checking the remaining battery capacity, EUVE was stabilized pointing away from the Sun and sent into safehold at 2359 GMT on January 31. The transmitters were commanded off on February 2.

1992 July 7 - . 09:20 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 83 - . Payload: GPS 2A-14 / GPS SVN 26. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 22014 . COSPAR: 1992-039A. Apogee: 20,400 km (12,600 mi). Perigee: 19,962 km (12,403 mi). Inclination: 54.90 deg. Period: 718.00 min. Global Positioning System. Placed in Plane F Slot 2..

1992 July 24 - . 14:26 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 6925.

Geotail - . Payload: Geotail. Mass: 1,008 kg (2,222 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Geotail. USAF Sat Cat: 22049 . COSPAR: 1992-044A. Apogee: 399,941 km (248,511 mi). Perigee: 57,448 km (35,696 mi). Inclination: 18.00 deg. Period: 18,904.40 min.
Measured magnetosphere and Earth's geomagnetic tail. To investigate the structure and dynamics of the geomagnetic tail that extends on the nightside of the Earth. Launch time 1426 GMT. Launching states Japan and the United States of America. Launching organization NASA.

DUVE - . Payload: DUVE. Nation: Japan. Agency: MDAC. Class: Earth. Type: Seismology satellite. Spacecraft: DUVE. Decay Date: 1993-03-16 . USAF Sat Cat: 22050 . COSPAR: 1992-044B. Apogee: 1,413 km (877 mi). Perigee: 215 km (133 mi). Inclination: 27.40 deg. Period: 101.17 min. Diffuse Ultraviolet Explorer package bolted to Delta 2 2nd stage..

1992 August 31 - . 10:41 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

Satcom C4 - . Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: GE Americom. Manufacturer: Lockheed. Program: Satcom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. USAF Sat Cat: 22096 . COSPAR: 1992-057A. Apogee: 35,789 km (22,238 mi). Perigee: 35,786 km (22,236 mi). Inclination: 0.10 deg. Period: 1,436.20 min. Stationed at 135 deg W. Positioned in geosynchronous orbit at 135 deg W in 1992-1999 As of 3 September 2001 located at 135.00 deg W drifting at 0.002 deg E per day. As of 2007 Mar 10 located at 164.40W drifting at 4.518W degrees per day..

1992 September 9 - . 08:57 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 84 - . Payload: GPS 2A-15 / GPS SVN 27. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 22108 . COSPAR: 1992-058A. Apogee: 20,453 km (12,708 mi). Perigee: 19,909 km (12,370 mi). Inclination: 54.50 deg. Period: 718.00 min. Global Positioning System. Placed in Plane A Slot 4..

1992 October 12 - . 09:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

DFS 3 - . Payload: Kopernikus 3. Mass: 1,400 kg (3,000 lb). Nation: Germany. Agency: Bundespost. Program: DFS. Class: Communications. Type: Civilian communications satellite. Spacecraft: Spacebus 100. USAF Sat Cat: 22175 . COSPAR: 1992-066A. Apogee: 35,799 km (22,244 mi). Perigee: 35,773 km (22,228 mi). Inclination: 0.50 deg. Period: 1,436.10 min.
Stationed at 33.5 deg E. Communication satellite. Longitude 33.5 deg E. Delta II flight no 212. Positioned in geosynchronous orbit at 31 deg E in 1992; 23 deg E in 1993-1999 As of 1 September 2001 located at 23.45 deg E drifting at 0.001 deg E per day. As of 2007 Mar 9 located at 29.79E drifting at 1.955W degrees per day.

1992 November 22 - . 23:54 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 85 - . Payload: GPS 2A-16 / GPS SVN 32. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 22231 . COSPAR: 1992-079A. Apogee: 20,325 km (12,629 mi). Perigee: 20,038 km (12,451 mi). Inclination: 55.50 deg. Period: 718.00 min. Global Positioning System. Placed in Plane F Slot 4..

1992 December 18 - . 22:16 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 87 - . Payload: GPS 2A-17 / GPS SVN 29. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 22275 . COSPAR: 1992-089A. Apogee: 20,324 km (12,628 mi). Perigee: 20,038 km (12,451 mi). Inclination: 54.70 deg. Period: 718.00 min. Global Positioning System. Placed in Plane F Slot 5..

1993 February 3 - . 02:55 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 88 - . Payload: GPS 2A-18 / GPS SVN 22. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 22446 . COSPAR: 1993-007A. Apogee: 20,359 km (12,650 mi). Perigee: 20,006 km (12,431 mi). Inclination: 54.80 deg. Period: 718.00 min. Global Positioning System. Placed in Plane Plane B Slot 1..

1993 March 30 - . 03:09 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 90 - . Payload: GPS 2A-19 / GPS SVN 31. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 22581 . COSPAR: 1993-017A. Apogee: 20,293 km (12,609 mi). Perigee: 20,072 km (12,472 mi). Inclination: 55.00 deg. Period: 718.00 min. Global Positioning System. Placed in Plane C Slot 3..

SEDS 1 Deployer - . Payload: SEDS 1 Deployer. Mass: 25 kg (55 lb). Nation: USA. Agency: MDAC. Program: Navstar. Spacecraft: SEDS. Decay Date: 1999-05-05 . USAF Sat Cat: 22583 . COSPAR: 1993-017C. Apogee: 1,292 km (802 mi). Perigee: 305 km (189 mi). Inclination: 36.10 deg. Period: 100.84 min.

SEDS 1 - . Payload: SEDS 1 End Mass/Tether. Mass: 25 kg (55 lb). Nation: USA. Agency: NASA Huntsville. Class: Technology. Type: Tether technology satellite. Spacecraft: SEDS. Decay Date: 1993-03-30 . USAF Sat Cat: 22582 . COSPAR: 1993-017B. Apogee: 719 km (446 mi). Perigee: 183 km (113 mi). Inclination: 36.00 deg. Period: 93.62 min. Small Expendable-tether Deployer System. .

1993 May 13 - . 00:07 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 91 - . Payload: GPS 2A-20 / GPS SVN 37. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 22657 . COSPAR: 1993-032A. Apogee: 20,345 km (12,641 mi). Perigee: 20,017 km (12,437 mi). Inclination: 55.10 deg. Period: 718.00 min. Global Positioning System. Placed in Plane C Slot 4..

1993 June 26 - . 13:27 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 92 - . Payload: GPS 2A-21 / GPS SVN 39. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 22700 . COSPAR: 1993-042A. Apogee: 20,250 km (12,580 mi). Perigee: 20,112 km (12,496 mi). Inclination: 54.60 deg. Period: 717.90 min. Global Positioning System. Placed in Plane A Slot 1..

PMG Far End Package - . Nation: USA. Agency: MDSSC. Program: Navstar. Spacecraft: PMG. COSPAR: 1993-042xx.

PMG - . Payload: Plasma Motor Generator. Nation: USA. Agency: MDAC. Program: Navstar. Spacecraft: PMG. Decay Date: 1993-08-30 . USAF Sat Cat: 22701 . COSPAR: 1993-042B. Apogee: 677 km (420 mi). Perigee: 185 km (114 mi). Inclination: 25.70 deg. Period: 93.20 min.

1993 August 30 - . 12:38 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 94 - . Payload: GPS 2A-22 / GPS SVN 35. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 22779 . COSPAR: 1993-054A. Apogee: 20,255 km (12,585 mi). Perigee: 20,110 km (12,490 mi). Inclination: 54.90 deg. Period: 718.00 min. Global Positioning System. Placed in Plane B Slot 4..

1993 October 26 - . 17:04 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 96 - . Payload: GPS 2A-23 / GPS SVN 34. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 22877 . COSPAR: 1993-068A. Apogee: 20,260 km (12,580 mi). Perigee: 20,104 km (12,492 mi). Inclination: 55.10 deg. Period: 718.00 min. Global Positioning System. Placed in Plane D Slot 4..

1993 December 8 - . 00:48 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 98 - . Payload: NATO 4B. Mass: 1,430 kg (3,150 lb). Nation: NATO. Agency: NATO. Program: NATO. Class: Communications. Type: Military communications satellite. Spacecraft: ECS/OTS. USAF Sat Cat: 22921 . COSPAR: 1993-076A. Apogee: 35,805 km (22,248 mi). Perigee: 35,767 km (22,224 mi). Inclination: 2.20 deg. Period: 1,436.10 min.
NATO encrypted communications relay. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 6 deg E in 1994-1998; 20 deg W in 1998-1999 As of 2 September 2001 located at 20.16 deg W drifting at 0.009 deg W per day. As of 2007 Mar 10 located at 35.47E drifting at 0.007E degrees per day.

1994 February 19 - . 23:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925-8.

Galaxy 1R - . Payload: Galaxy 1RR. Mass: 1,391 kg (3,066 lb). Nation: USA. Agency: HCI. Program: Galaxy. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 23016 . COSPAR: 1994-013A. Apogee: 35,797 km (22,243 mi). Perigee: 35,774 km (22,228 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
Stationed at 133 deg W; replaced Galaxy 1. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). Positioned in geosynchronous orbit at 133 deg W in 1994-1999 As of 5 September 2001 located at 132.97 deg W drifting at 0.005 deg E per day. As of 2007 Mar 9 located at 88.88W drifting at 3.795W degrees per day.

1994 March 10 - . 03:40 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 100 - . Payload: GPS 2A-24 / GPS SVN 36. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 23027 . COSPAR: 1994-016A. Apogee: 20,366 km (12,654 mi). Perigee: 20,000 km (12,000 mi). Inclination: 53.90 deg. Period: 718.00 min. Final element of initial GPS constellation. Placed in Plane C Slot 1..

SEDS 2 - . Payload: SEDS 2 End Mass. Mass: 25 kg (55 lb). Nation: USA. Agency: MDSSC. Program: Navstar. Spacecraft: SEDS. COSPAR: 1994-016xx.

SEDS 2 Deployer - . Payload: SEDS 2 Deployer. Mass: 25 kg (55 lb). Nation: USA. Agency: MDAC. Program: Navstar. Spacecraft: SEDS. Decay Date: 1994-05-08 . USAF Sat Cat: 23028 . COSPAR: 1994-016B. Apogee: 341 km (211 mi). Perigee: 340 km (210 mi). Inclination: 32.30 deg. Period: 91.34 min.

1994 November 1 - . 09:31 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925-10.

Wind - . Mass: 1,195 kg (2,634 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Wind. USAF Sat Cat: 23333 . COSPAR: 1994-071A. Apogee: 1,578,658 km (980,930 mi). Perigee: 48,840 km (30,340 mi). Inclination: 19.65 deg. Period: 318,240.00 min.
Solar wind research in L-1 halo orbit; part of International Solar Terrestrial Physics program. 221 day orbit. NASA's Wind probe made its 32nd lunar flyby on August 19, 2000, with a closest approach of 7600 km to the surface. This placed it on a 2 million km apogee orbit, adjusted on August 26 to an approximately 567000 x 1620000 km x 21.8 deg `Distant Prograde Orbit', reaching apogee on September 29 2000.

1995 August 5 - . 11:10 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925. FAILURE: Partial Failure.. Failed Stage: U.

Mugunghwa 1 - . Payload: Koreasat 1. Mass: 1,459 kg (3,216 lb). Nation: Korea South. Agency: KT. Manufacturer: Lockheed. Program: Koreasat. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. USAF Sat Cat: 23639 . COSPAR: 1995-041A. Apogee: 35,796 km (22,242 mi). Perigee: 35,776 km (22,230 mi). Inclination: 2.70 deg. Period: 1,436.10 min.
15 Ku-band transponders; boosted into geosynch orbit by satellite thrusters following Delta failure that left satellite in LEO; unplanned use of satellite propellant cut usable satellite lifetime by approx. 50 percent. Stationed at 116.0 deg E. Stage 1 SRM failure Positioned in geosynchronous orbit at 116 deg E in 1995-1999 As of 5 September 2001 located at 47.22 deg E drifting at 0.022 deg E per day. As of 2007 Mar 9 located at 152.88E drifting at 2.155W degrees per day.

1995 November 4 - . 14:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10.

Radarsat - . Mass: 2,713 kg (5,981 lb). Nation: Canada. Agency: CSA. Class: Earth. Type: Civilian Radarsat. Spacecraft Bus: BCP-4000. Spacecraft: Radarsat. USAF Sat Cat: 23710 . COSPAR: 1995-059A. Apogee: 793 km (492 mi). Perigee: 791 km (491 mi). Inclination: 98.60 deg. Period: 100.70 min. Earth imaging with synthetic aperture radar..

SURFSAT - . Payload: SURFSAT/Delta 229. Mass: 55 kg (121 lb). Nation: USA. Agency: MDAC. Class: Technology. Type: Navigation technology satellite. Spacecraft: SURFSAT-1. USAF Sat Cat: 23711 . COSPAR: 1995-059B. Apogee: 1,494 km (928 mi). Perigee: 934 km (580 mi). Inclination: 100.60 deg. Period: 109.70 min. Test satellite for NASA's Deep Space Network..

1995 December 30 - . 13:48 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7920-10.

XTE - . Payload: Rossi X-ray Timing Explorer. Mass: 3,000 kg (6,600 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: XTE. Decay Date: 2018-04-30 . USAF Sat Cat: 23757 . COSPAR: 1995-074A. Apogee: 583 km (362 mi). Perigee: 565 km (351 mi). Inclination: 23.00 deg. Period: 96.10 min. X-ray Timing Explorer; X-ray astronomy..

1996 January 14 - . 11:10 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

Koreasat 2 - . Mass: 600 kg (1,320 lb). Nation: Korea South. Agency: KT. Manufacturer: Lockheed. Program: Koreasat. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 2000-04-08 . USAF Sat Cat: 23768 . COSPAR: 1996-003A. Apogee: 35,792 km (22,240 mi). Perigee: 35,782 km (22,233 mi). Inclination: 0.00 deg. Period: 1,436.20 min. Geostationary at 116.0E. Positioned in geosynchronous orbit at 116 deg E in 1996-2000 As of 5 September 2001 located at 113.02 deg E drifting at 0.017 deg W per day. As of 2007 Mar 11 located at 116.35E drifting at 0.013W degrees per day..

1996 February 17 - . 20:43 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925-8.

NEAR - . Payload: Discovery 1. Mass: 818 kg (1,803 lb). Nation: USA. Agency: NASA Greenbelt. Program: Discovery series. Class: Asteroids. Type: Asteroid probe. Spacecraft: NEAR. Decay Date: 2001-02-12 . USAF Sat Cat: 23784 . COSPAR: 1996-008A.
Near Earth Asteroid Rendezvous (NEAR) mission was the first of NASA's Discovery missions, a series of small-scale spacecraft designed to proceed from development to flight in under three years for a cost of less than $150 million. The spacecraft's mission was to rendezvous with and achieve orbit around the asteroid Eros in January 1999, and study the asteroid for one year. However as it flew by the Earth on 23 January 1998, a problem caused an abort of the first encounter burn. The mission had to be rescoped for a later encounter but successfully entered orbit around Eros on Valentine's Day 2000 and ended the mission by gently landing on its surface on 12 February 2001.

1996 February 24 - . 11:24 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7925-10.

Polar - . Mass: 1,300 kg (2,800 lb). Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Polar. USAF Sat Cat: 23802 . COSPAR: 1996-013A. Apogee: 50,423 km (31,331 mi). Perigee: 5,554 km (3,451 mi). Inclination: 86.30 deg. Period: 1,070.20 min. HEO. Fields and particles, auroral studies; part of International Solar Terrestrial Physics program..

1996 March 28 - . 00:21 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 117 - . Payload: GPS 2A-25 / GPS SVN 33. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 23833 . COSPAR: 1996-019A. Apogee: 20,257 km (12,587 mi). Perigee: 20,106 km (12,493 mi). Inclination: 54.60 deg. Period: 718.00 min. Placed in Plane C Slot 2 of the constellation..

1996 April 24 - . 12:27 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10.

MSX - . Mass: 2,700 kg (5,900 lb). Nation: USA. Agency: BMDO. Class: Military. Type: Strategic defense satellite. Spacecraft: MSX. USAF Sat Cat: 23851 . COSPAR: 1996-024A. Apogee: 907 km (563 mi). Perigee: 897 km (557 mi). Inclination: 99.40 deg. Period: 103.10 min. LEO. Midcourse Space eXperiment; missile detection technology tests; also used for auroral and atmospheric studies .

1996 May 24 - . 01:09 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

Galaxy 9 - . Nation: USA. Agency: HCI. Program: Galaxy. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 23877 . COSPAR: 1996-033A. Apogee: 35,789 km (22,238 mi). Perigee: 35,783 km (22,234 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
Geostationary at 123.0W. Positioned in geosynchronous orbit at 123 deg W in 1996-2000; 127 deg W in 2000.- As of 5 September 2001 located at 126.96 deg W drifting at 0.001 deg W per day. As of 2007 Mar 11 located at 74.14W drifting at 0.004W degrees per day.

1996 July 16 - . 00:50 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 126 - . Payload: GPS 2A-26 / GPS SVN 40. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 23953 . COSPAR: 1996-041A. Apogee: 20,237 km (12,574 mi). Perigee: 20,127 km (12,506 mi). Inclination: 55.10 deg. Period: 717.90 min. Placed in Plane E Slot 3 of the constellation..

1996 September 12 - . 08:49 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 128 - . Payload: GPS 2A-27 / GPS SVN 30. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 24320 . COSPAR: 1996-056A. Apogee: 20,320 km (12,620 mi). Perigee: 20,042 km (12,453 mi). Inclination: 54.70 deg. Period: 718.00 min. Placed in Plane B Slot 2 of the constellation..

1996 November 7 - . 17:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

Mars Global Surveyor - . Payload: MGS / Leros 1B LAE. Nation: USA. Agency: JPL, NASA. Program: Mars Surveyor. Class: Mars. Type: Mars probe. Spacecraft: Mars Global Surveyor. USAF Sat Cat: 24648 . COSPAR: 1996-062A.
Mars Global Surveyor entered a 258 x 54021 km x 93.3 deg polar orbit around Mars on 12 September 1997 after a 22 minute burn of its main engine. After a long aerobraking phase to a lower circular orbit, the spacecraft began its primary mission of photographing and observing changes on the Martian surface in March 1999. After nearly ten years of service, the last signals from MGS were received on 3 November 2006. The spacecraft went silent after an incorrect software upload caused its solar arrays to lose power.

1996 December 4 - . 06:58 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925.

Mars Pathfinder - . Payload: Discovery 2. Nation: USA. Agency: JPL, NASA. Program: Discovery series. Class: Mars. Type: Mars probe. Spacecraft Bus: Mars Rovers. Spacecraft: Mars Pathfinder. Decay Date: 1997-07-04 . USAF Sat Cat: 24667 . COSPAR: 1996-068A. En route Mars.

Sojourner - . Payload: MFEX Rover. Nation: USA. Agency: MDSSC. Spacecraft Bus: Mars Rovers. Spacecraft: Mars Pathfinder. COSPAR: 1996-068xx.

MPF Cruise Stage - . Nation: USA. Agency: MDSSC. Spacecraft Bus: Mars Rovers. Spacecraft: Mars Pathfinder. COSPAR: 1996-068xx.

1997 January 17 - . 16:28 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925. FAILURE: T+12 sec GEM strap-on number 2 structural failure.. Failed Stage: 0.

GPS 42 - . Payload: GPS 2R-1 / GPS SVN 42. Mass: 2,030 kg (4,470 lb). Nation: USA. Agency: MDSSC. Manufacturer: Valley Forge. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. Destroyed in launch vehicle failure..

1997 May 5 - . 14:55 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

Iridium 8 - . Payload: Iridium s/n SV008. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2017-11-24 . USAF Sat Cat: 24792 . COSPAR: 1997-020A. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 4. Ascending node 262.5 degrees..

Iridium 4 - . Payload: Iridium s/n SV004. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24796 . COSPAR: 1997-020E. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 4. Ascending node 262.5 degrees..

Iridium 6 - . Payload: Iridium s/n SV006. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2017-12-23 . USAF Sat Cat: 24794 . COSPAR: 1997-020C. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 4. Ascending node 262.5 degrees..

Iridium 5 - . Payload: Iridium s/n SV005. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24795 . COSPAR: 1997-020D. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 4. Ascending node 262.5 degrees..

Iridium 7 - . Payload: Iridium s/n SV007. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24793 . COSPAR: 1997-020B. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 4. Ascending node 262.4 degrees..

1997 May 20 - . 22:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

Thor 2 - . Payload: Thor 2A. Mass: 2,800 kg (6,100 lb). Nation: Norway. Agency: Telenor. Manufacturer: El Segundo. Program: Thor Comsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 24808 . COSPAR: 1997-025A. Apogee: 35,793 km (22,240 mi). Perigee: 35,780 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 0.8W Positioned in geosynchronous orbit at 1 deg W in 1997-1999 As of 5 September 2001 located at 0.73 deg W drifting at 0.000 deg E per day. As of 2007 Mar 9 located at 0.76W drifting at 0.002W degrees per day..

1997 July 9 - . 13:04 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

Iridium 15 - . Payload: Iridium s/n SV015. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-10-14 . USAF Sat Cat: 24869 . COSPAR: 1997-034A. Apogee: 778 km (483 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 6. Ascending node 325.8 degrees..

Iridium 21 - . Payload: Iridium s/n SV021. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24873 . COSPAR: 1997-034E. Apogee: 640 km (390 mi). Perigee: 626 km (388 mi). Inclination: 86.39 deg. Period: 97.38 min. Plane 6. Ascending node 310.4 degrees. Failed in low orbit..

Iridium 18 - . Payload: Iridium s/n SV018. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-08-19 . USAF Sat Cat: 24872 . COSPAR: 1997-034D. Apogee: 778 km (483 mi). Perigee: 776 km (482 mi). Inclination: 86.39 deg. Period: 100.40 min. Plane 6. Ascending node 325.8 degrees..

Iridium 20 - . Payload: Iridium s/n SV020. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24871 . COSPAR: 1997-034C. Apogee: 784 km (487 mi). Perigee: 768 km (477 mi). Inclination: 86.40 deg. Period: 100.37 min. Plane 6. Ascending node 325.7 degrees. Failed..

Iridium 17 - . Payload: Iridium s/n SV017. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24870 . COSPAR: 1997-034B. Apogee: 778 km (483 mi). Perigee: 776 km (482 mi). Inclination: 86.39 deg. Period: 100.40 min. Plane 6. Ascending node 325.8 degrees..

1997 July 23 - . 03:43 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 132 - . Payload: GPS 2R-2 / GPS SVN 43. Mass: 2,030 kg (4,470 lb). Nation: USA. Agency: USAF. Manufacturer: Valley Forge. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 24876 . COSPAR: 1997-035A. Apogee: 20,235 km (12,573 mi). Perigee: 20,132 km (12,509 mi). Inclination: 55.80 deg. Period: 718.00 min. Placed in Plane F Slot 3 of the constellation..

1997 August 21 - . 00:38 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

Iridium 26 - . Payload: Iridium s/n SV026. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24903 . COSPAR: 1997-043A. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 199.4 degrees..

Iridium 22 - . Payload: Iridium s/n SV022. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24907 . COSPAR: 1997-043E. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 199.3 degrees..

Iridium 23 - . Payload: Iridium s/n SV023. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-03-28 . USAF Sat Cat: 24906 . COSPAR: 1997-043D. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 199.4 degrees..

Iridium 24 - . Payload: Iridium s/n SV024. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24905 . COSPAR: 1997-043C. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 199.3 degrees. Should be 24905, failed..

Iridium 25 - . Payload: Iridium s/n SV025. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-05-14 . USAF Sat Cat: 24904 . COSPAR: 1997-043B. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 199.4 degrees..

1997 August 25 - . 14:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7920-8.

ACE - . Payload: ACE. Mass: 785 kg (1,730 lb). Nation: USA. Agency: NASA Greenbelt. Manufacturer: APL. Class: Earth. Type: Magnetosphere satellite. Spacecraft: ACE. USAF Sat Cat: 24912 . COSPAR: 1997-045A. Apogee: 128,196 km (79,657 mi). Perigee: 176 km (109 mi). Period: 86,411.37 min. Earth-Sun L1 point.

1997 September 27 - . 01:23 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

Iridium 19 - . Payload: Iridium s/n SV019. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-04-07 . USAF Sat Cat: 24965 . COSPAR: 1997-056A. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 4. Ascending node 262.4 degrees..

Iridium 37 - . Payload: Iridium s/n SV037. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-12-26 . USAF Sat Cat: 24966 . COSPAR: 1997-056B. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 4. Ascending node 262.6 degrees..

Iridium 34 - . Payload: Iridium s/n SV034. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-01-08 . USAF Sat Cat: 24969 . COSPAR: 1997-056E. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 4. Ascending node 262.5 degrees..

Iridium 36 - . Payload: Iridium s/n SV036. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 24967 . COSPAR: 1997-056C. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 4. Ascending node 262.4 degrees..

Iridium 35 - . Payload: Iridium s/n SV035. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-05-26 . USAF Sat Cat: 24968 . COSPAR: 1997-056D. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 4. Ascending node 262.5 degrees..

1997 November 6 - . 00:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925.

USA 134 - . Payload: GPS 2A-28 / GPS SVN 38. Mass: 1,816 kg (4,003 lb). Nation: USA. Agency: USAF. Manufacturer: Seal Beach. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: Navstar. Spacecraft: GPS Block 2 and 2A. USAF Sat Cat: 25030 . COSPAR: 1997-067A. Apogee: 20,394 km (12,672 mi). Perigee: 19,970 km (12,400 mi). Inclination: 55.00 deg. Period: 718.00 min. Final GPS Block 2A satellite. Placed in Plane A Slot 3..

1997 November 9 - . 01:34 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

Iridium 43 - . Payload: Iridium s/n SV043. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-02-11 . USAF Sat Cat: 25039 . COSPAR: 1997-069A. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.39 deg. Period: 100.40 min. Plane 6. Ascending node 325.8 degrees..

Iridium 38 - . Payload: Iridium s/n SV038. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25043 . COSPAR: 1997-069E. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 6. Ascending node 325.6 degrees..

Iridium 40 - . Payload: Iridium s/n SV040. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-09-23 . USAF Sat Cat: 25041 . COSPAR: 1997-069C. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.39 deg. Period: 100.40 min. Plane 6. Ascending node 325.8 degrees..

Iridium 39 - . Payload: Iridium s/n SV039. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25042 . COSPAR: 1997-069D. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 6. Ascending node 325.8 degrees..

Iridium 41 - . Payload: Iridium s/n SV041. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-07-28 . USAF Sat Cat: 25040 . COSPAR: 1997-069B. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 6. Ascending node 325.8 degrees..

1997 December 20 - . 13:16 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

Iridium 45 - . Payload: Iridium s/n SV045. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25104 . COSPAR: 1997-082A. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 199.4 degrees..

Iridium 48 - . Payload: Iridium s/n SV048. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2001-05-05 . USAF Sat Cat: 25107 . COSPAR: 1997-082D. Apogee: 780 km (480 mi). Perigee: 775 km (481 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 199.4 degrees..

Iridium 49 - . Payload: Iridium s/n SV049. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-02-13 . USAF Sat Cat: 25108 . COSPAR: 1997-082E. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 199.4 degrees..

Iridium 47 - . Payload: Iridium s/n SV047. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-09-01 . USAF Sat Cat: 25106 . COSPAR: 1997-082C. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 2. Ascending node 199.4 degrees..

Iridium 46 - . Payload: Iridium s/n SV046. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25105 . COSPAR: 1997-082B. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.41 deg. Period: 100.40 min. Plane 2. Ascending node 199.4 degrees. Should be 25105..

1998 January 10 - . 00:32 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

Skynet 4D - . Mass: 1,490 kg (3,280 lb). Nation: UK. Agency: MoD. Manufacturer: Martin. Program: Skynet. Class: Communications. Type: Military communications satellite. Spacecraft: ECS/OTS. USAF Sat Cat: 25134 . COSPAR: 1998-002A. Apogee: 35,795 km (22,241 mi). Perigee: 35,776 km (22,230 mi). Inclination: 3.90 deg. Period: 1,436.00 min. Geostationary at 52.8 degrees E. Positioned in geosynchronous orbit at 53 deg E in 1998-1999; moving As of 4 September 2001 located at 34.00 deg W drifting at 0.004 deg W per day. As of 2007 Mar 10 located at 34.33W drifting at 0.016W degrees per day..

1998 February 14 - . 14:34 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

Globalstar FM1 - . Payload: Globalstar s/n FM1. Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Manufacturer: Alenia, Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25162 . COSPAR: 1998-008A. Apogee: 1,414 km (878 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min. Plane 1. Ascending node 43.9 degrees..

Globalstar FM3 - . Payload: Globalstar s/n FM3. Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Manufacturer: Alenia, Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25164 . COSPAR: 1998-008C. Apogee: 1,520 km (940 mi). Perigee: 1,509 km (937 mi). Inclination: 52.00 deg. Period: 116.30 min. Plane 1. Ascending node 42.4 degrees..

Globalstar FM4 - . Payload: Globalstar s/n FM4. Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Manufacturer: Alenia, Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25165 . COSPAR: 1998-008D. Apogee: 1,416 km (879 mi). Perigee: 1,412 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min. Plane 1. Ascending node 43.6 degrees..

Globalstar FM2 - . Payload: Globalstar s/n FM2. Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Manufacturer: Alenia, Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25163 . COSPAR: 1998-008B. Apogee: 1,414 km (878 mi). Perigee: 1,412 km (877 mi). Inclination: 52.01 deg. Period: 114.08 min. Plane 1. Ascending node 43.8 degrees..

1998 February 18 - . 13:58 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

Iridium 52 - . Payload: Iridium s/n SV052. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-11-05 . USAF Sat Cat: 25169 . COSPAR: 1998-010A. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 5. Ascending node 294.1 degrees..

Iridium 50 - . Payload: Iridium s/n SV050. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-09-23 . USAF Sat Cat: 25172 . COSPAR: 1998-010D. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 5. Ascending node 294.2 degrees..

Iridium 56 - . Payload: Iridium s/n SV056. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-10-11 . USAF Sat Cat: 25170 . COSPAR: 1998-010B. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 5. Ascending node 294 degrees..

Iridium 53 - . Payload: Iridium s/n SV053. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-09-30 . USAF Sat Cat: 25173 . COSPAR: 1998-010E. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 5. Ascending node 294.2 degrees..

Iridium 54 - . Payload: Iridium s/n SV054. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25171 . COSPAR: 1998-010C. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 5. Ascending node 294.2 degrees..

1998 March 30 - . 06:02 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

Iridium 55 - . Payload: Iridium s/n SV055. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25272 . COSPAR: 1998-019A. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 3. Ascending node 230.9 degrees..

Iridium 60 - . Payload: Iridium s/n SV060. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25276 . COSPAR: 1998-019E. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 3. Ascending node 230.9 degrees..

Iridium 59 - . Payload: Iridium s/n SV059. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25275 . COSPAR: 1998-019D. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 3. Ascending node 230.9 degrees..

Iridium 57 - . Payload: Iridium s/n SV057. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25273 . COSPAR: 1998-019B. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 3. Ascending node 230.9 degrees..

Iridium 58 - . Payload: Iridium s/n SV058. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25274 . COSPAR: 1998-019C. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 3. Ascending node 230.9 degrees..

1998 April 24 - . 22:38 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

Globalstar FM6 - . Payload: Globalstar s/n FM6. Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Manufacturer: Alenia, Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25306 . COSPAR: 1998-023A. Apogee: 1,523 km (946 mi). Perigee: 1,503 km (933 mi). Inclination: 52.00 deg. Period: 116.30 min. Plane 2. Ascending node 90.4 degrees..

Globalstar FM15 - . Payload: Globalstar s/n FM15. Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Manufacturer: Alenia, Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25309 . COSPAR: 1998-023D. Apogee: 1,414 km (878 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min. Plane 2. Ascending node 88.0 degrees..

Globalstar FM14 - . Payload: Globalstar s/n FM14. Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Manufacturer: Alenia, Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25308 . COSPAR: 1998-023C. Apogee: 1,414 km (878 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min. Plane 2. Ascending node 90.2 degrees..

Globalstar FM8 - . Payload: Globalstar s/n FM8. Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Manufacturer: Alenia, Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25307 . COSPAR: 1998-023B. Apogee: 1,414 km (878 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min. Plane 2. Ascending node 88.9 degrees..

1998 May 17 - . 21:16 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

Iridium 70 - . Payload: Iridium s/n SV070. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-10-11 . USAF Sat Cat: 25342 . COSPAR: 1998-032A. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 1. Ascending node 167.8 degrees..

Iridium 72 - . Payload: Iridium s/n SV072. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-05-14 . USAF Sat Cat: 25343 . COSPAR: 1998-032B. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 1. Ascending node 167.8 degrees..

Iridium 73 - . Payload: Iridium s/n SV073. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25344 . COSPAR: 1998-032C. Apogee: 778 km (483 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 1. Ascending node 167.8 degrees..

Iridium 74 - . Payload: Iridium s/n SV074. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2017-06-11 . USAF Sat Cat: 25345 . COSPAR: 1998-032D. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 1. Ascending node 167.8 degrees..

Iridium 75 - . Payload: Iridium s/n SV075. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-07-10 . USAF Sat Cat: 25346 . COSPAR: 1998-032E. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 1. Ascending node 167.7 degrees. Not in service..

1998 June 10 - . 00:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

Thor 3 - . Mass: 2,800 kg (6,100 lb). Nation: Norway. Agency: Telenor. Manufacturer: El Segundo. Program: Thor Comsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 25358 . COSPAR: 1998-035A. Apogee: 35,798 km (22,243 mi). Perigee: 35,777 km (22,230 mi). Inclination: 0.10 deg. Period: 1,436.10 min.
The spacecraft was delivered to its final orbit in a complex series of five engine burns by three rocket stages. The Delta's second stage demonstrated its restart capability in 4 burns: Burn 1 placed the rocket and payload into a low circular orbit; Burn 2 raised the apogee to 1400 km; Burn 3 circularised the orbit at 1400 km. The second stage then separated, and Burn 4 lowered the spent stage's perigee to a low altitude to ensure the stage would decay quickly and not add to the space junk already on orbit. Stage 3 burned once to place the payload and its kick motor into a high 1400 km perigee geosynchronous transfer orbit. The Stage 4 Star 30 apogee kick motor circularised the spacecraft's orbit at geostationary altitude. Geostationary at 0.8 degrees W. Positioned in geosynchronous orbit at 1 deg W in 1998-1999 As of 4 September 2001 located at 0.83 deg W drifting at 0.000 deg E per day. As of 2007 Mar 9 located at 0.85W drifting at 0.002W degrees per day.

1998 August 27 - . 01:17 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Thor. Launch Vehicle: Delta 8930. FAILURE: Due to guidance system induced oscillation all solid motor gimbal hydraulic fluid exhausted after only 71 seconds of flight. Range safety destroyed booster 75 seconds into flight at 16 km altitude.. Failed Stage: G.

Galaxy 10 - . Payload: HS 601HP. Mass: 3,876 kg (8,545 lb). Nation: USA. Agency: PanAmSat. Manufacturer: El Segundo. Program: Galaxy. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601.
Built by Hughes/El Segundo for Panamsat. The satellite carried 24 C-band and 24 Ku-band transponders to provide US/Caribbean coverage, and was to have replaced the ageing SBS-5 satellite at 123 deg West. Replenishing the Galaxy/PAS constellation was a high priority for Panamsat following the loss of Galaxy 4 and problems with Galaxy 7. Galaxy 11 was not scheduled to go up until the first launch of the Sea Launch Zenit-3SL in early 1999, and this booster was in limbo due to legal problems with unauthorised transfer of technical data from Boeing to Russia. In addition there were several PAS satellites awaiting launch over the next year on Proton and Ariane vehicles.

1998 September 8 - . 21:13 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

Iridium 82 - . Payload: Iridium s/n SV082. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25467 . COSPAR: 1998-051A. Apogee: 712 km (442 mi). Perigee: 708 km (439 mi). Inclination: 86.50 deg. Period: 99.00 min. Plane 6. Ascending node 325.6 degrees. Not in service..

Iridium 81 - . Payload: Iridium s/n SV081. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-07-17 . USAF Sat Cat: 25468 . COSPAR: 1998-051B. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 6. Ascending node 325.7 degrees..

Iridium 80 - . Payload: Iridium s/n SV080. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-08-12 . USAF Sat Cat: 25469 . COSPAR: 1998-051C. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 6. Ascending node 325.7 degrees..

Iridium 79 - . Payload: Iridium s/n SV079. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2000-11-29 . USAF Sat Cat: 25470 . COSPAR: 1998-051D. Apogee: 544 km (338 mi). Perigee: 494 km (306 mi). Inclination: 86.01 deg. Period: 95.01 min. Plane 6. Ascending node 316.3 degrees. Failed in low orbit..

Iridium 77 - . Payload: Iridium s/n SV077. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2017-09-22 . USAF Sat Cat: 25471 . COSPAR: 1998-051E. Apogee: 709 km (440 mi). Perigee: 707 km (439 mi). Inclination: 86.52 deg. Period: 98.96 min. Plane 6. Ascending node 325.4 degrees. Not in service..

1998 October 24 - . 12:08 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7326-9.5.

Deep Space 1 - . Mass: 486 kg (1,071 lb). Nation: USA. Agency: NASA. Manufacturer: JPL. Class: Asteroids. Type: Asteroid probe. Spacecraft: Deep Space 1. USAF Sat Cat: 25508 . COSPAR: 1998-061A.
The primary mission of Deep Space 1 probe was to test new technology for future interplanetary spacecraft, the main experiment being an ion propulsion engine using xenon propellant. It had an initial mass of 486.3 kg, including 81.5 kg of Xenon and 31.1 kg of hydrazine propellants. The Delta 7326 used three Alliant GEM-40 solid strap-on motors, the standard Delta II core vehicle, and a Thiokol Star 37FM solid motor as the third stage. The Delta second stage entered a 185 km parking orbit, then fired again to enter a 174 km x 2744 km x 28.5 degree orbit. The Star 37FM then separated and accelerated to place Deep Space 1 to escape velocity. Deep Space 1 successfully started its ion engine on November 24 after an initial attempt failed after four minutes on November 10. From its initial solar orbit of 0.99 AU x 1.32 AU x 0.4 degree, Deep Space 1 was to fly past the 3 km diameter asteroid 1992 KD at its perihelion of 1.33 AU. The spacecraft then flew past the nucleus of comet 19P/Borrelly at a distance of 2200 km at 2230 GMT on Sep 22 2001. It survived the encounter in good shape, sending back photos of the comet. At the encounter DS1 was in a 1.3 x 1.5 AU x 0 deg (ecliptic) solar orbit; Borrelly's orbit was 1.3 x 5.9 AU.

SEDSAT 1 - . Nation: USA. Agency: Boeing. Manufacturer: SEDS. Program: STS. Class: Technology. Type: Navigation technology satellite. Spacecraft: SEDSAT. USAF Sat Cat: 25509 . COSPAR: 1998-061B. Apogee: 1,050 km (650 mi). Perigee: 544 km (338 mi). Inclination: 31.40 deg. Period: 100.80 min.
Following separation of the third stage and the primary Deep Space 1 payload, the Delta second stage manoeuvred from its 185 km parking orbit to a 174 km x 2744 km x 28.5 degree orbit. It then released the SEDSAT micro-satellite, built by the Huntsville, Alabama chapter of SEDS (the Students for the Exploration and Development of Space). SEDSAT has two amateur radio transponders and an earth imaging camera.

1998 November 6 - . 13:37 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

Iridium 2 - . Payload: Iridium s/n SV087. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 25527 . COSPAR: 1998-066A. Apogee: 603 km (374 mi). Perigee: 590 km (360 mi). Inclination: 85.60 deg. Period: 96.60 min. Plane 5. Ascending node 289.1 degrees. Parking orbit..

Iridium 83 - . Payload: Iridium s/n SV083. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-11-05 . USAF Sat Cat: 25531 . COSPAR: 1998-066E. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 5. Ascending node 294.2 degrees..

Iridium 86 - . Payload: Iridium s/n SV086. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-10-05 . USAF Sat Cat: 25528 . COSPAR: 1998-066B. Apogee: 712 km (442 mi). Perigee: 708 km (439 mi). Inclination: 86.50 deg. Period: 99.00 min. Plane 5. Ascending node 293.9 degrees. Raising orbit..

Iridium 84 - . Payload: Iridium s/n SV084. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-11-04 . USAF Sat Cat: 25530 . COSPAR: 1998-066D. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.40 deg. Period: 100.40 min. Plane 5. Ascending node 294.1 degrees. Raising orbit..

Iridium 85 - . Payload: Iridium s/n SV085. Mass: 689 kg (1,518 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2000-12-30 . USAF Sat Cat: 25529 . COSPAR: 1998-066C. Apogee: 536 km (333 mi). Perigee: 512 km (318 mi). Inclination: 86.02 deg. Period: 95.12 min. Plane 5. Ascending node 291.1 degrees. Parking orbit..

1998 November 22 - . 23:54 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

BONUM-1 - . Mass: 2,800 kg (6,100 lb). Nation: Russia. Agency: Telenor. Manufacturer: El Segundo. Program: BONUM. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 25546 . COSPAR: 1998-068A. Apogee: 35,794 km (22,241 mi). Perigee: 35,778 km (22,231 mi). Inclination: 0.20 deg. Period: 1,436.10 min.
BONUM-1 provided domestic Russian television service for Media Most, a Moscow media enterprise, broadcasting 50 channels to western Russia from a geostationary orbit at 36 degrees E. Mass was 1426 kg at launch, 800 kg of that propellant. BONUM-1 carried 8 Ku-band transponders. The Delta upper stage raised the initial 157 km x 189 km at 29.2 degree parking orbit to 159 km x 1304 km and then 1228 km x 1683 km at 26.7 degrees. A Thiokol Star 48B solid third stage boosted BONUM-1 to a 1285 x 36703 km x 19.5 degree geostationary transfer orbit, with the Thiokol Star 30 apogee kick motor placing the satellite in its final geostationary orbit. After separation of the spacecraft, the Delta made a final depletion burn to lower its orbit to 274 km x 1552 km x 25.6 degree to ensure it would quickly decay and burn up in the atmosphere. Geostationary at 35.9 degrees E. From 8 August 2000 position was 56.0 degrees E. Positioned in geosynchronous orbit at 36 deg E in 1998-1999 55 deg E in 2000. As of 5 September 2001 located at 56.03 deg E drifting at 0.016 deg W per day. As of 2007 Mar 10 located at 55.94E drifting at 0.008W degrees per day.

1998 December 11 - . 18:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7425-9.5.

Mars Climate Orbiter - . Mass: 629 kg (1,386 lb). Nation: USA. Agency: JPL. Manufacturer: Martin. Program: Mars Surveyor. Class: Mars. Type: Mars probe. Spacecraft: MCO. Decay Date: 1999-09-23 . USAF Sat Cat: 25571 . COSPAR: 1998-073A.
The Mars Climate Orbiter was the second flight of the Mars Surveyor Program. The probe was to enter a 160 km x 38600 km polar orbit around Mars on September 23,1999, and use aerobraking to reach a 373 km x 437 km x 92.9 degree sun-synchronous mapping orbit by November 23 1999. While the Mars Orbit Insertion burn began as planned on September 23, 1999 at 08:50 GMT, no signal was received after the spacecraft went behind the planet. Subsequent investigation showed that the spacecraft had plunged deep into the Martian atmosphere, with its closest approach to Mars being 57 km. It was concluded that the spacecraft burnt up in the atmosphere. It was later found that cutbacks in tracking, combined with incorrect values in a look-up table imbedded deep in the spacecraft software (use of pounds force instead of newtons) were to blame. This failure led to a shake-up of NASA's 'faster, better, cheaper' approach to unmanned spaceflight. Additional Details: here....

1999 January 3 - . 20:21 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7425-9.5.

Mars Polar Lander - . Mass: 576 kg (1,269 lb). Nation: USA. Agency: JPL. Manufacturer: Martin. Class: Mars. Type: Mars probe. Spacecraft: Mars Polar Lander. Decay Date: 1999-12-03 . USAF Sat Cat: 25605 . COSPAR: 1999-001A.
The Mars Polar Lander was placed by the first burn of the second stage into a 157 x 245 km x 28.35 deg parking orbit. The second stage restarted at 20:55 GMT and shut down in a 226 x 740 km x 25.8 deg Earth orbit. The solid rocket third stage (a Star 48B with a Nutation Control System and a yo-yo despin device) then ignited and put the spacecraft into solar orbit, separating at 21:02 GMT. Mars Polar Lander was to land near the south pole of Mars on December 3, 1999, and conduct conduct a three month mission, trenching near its landing site and testing for the presense of frozen water and carbon dioxide. Attached were two Deep Space 2 Microprobes, penetrators which would impact the Martian surface separately from the lander and return data on subsurface conditions from widely spaced points.
When the spacecraft reached Mars on December 3, the lander separated from the cruise stage at 19:51 UTC and the two penetrators, Scott and Amundsen, were to separate about 20 seconds later. No further communications were ever received from the spacecraft. Landing had been expected at 20:01 UTC at 76.1S 195.3W, with the penetrators landing a few kilometres from each other at 75.0S 196.5W.
This failure resulted in a review and reassessment of NASA's 'faster, better, cheaper' approach to planetary missions.

DS2 Microprobe 1 - . Nation: USA. Agency: Douglas. Class: Mars. Type: Mars probe. Spacecraft Bus: Mars Polar Lander. Spacecraft: DS2 Microprobe. USAF Sat Cat: 25606 . COSPAR: 1999-001B.

DS2 Microprobe 2 - . Nation: USA. Agency: Douglas. Class: Mars. Type: Mars probe. Spacecraft Bus: Mars Polar Lander. Spacecraft: DS2 Microprobe. Decay Date: 1999-03-23 . USAF Sat Cat: 25607 . COSPAR: 1999-001C. Apogee: 645 km (400 mi). Perigee: 220 km (130 mi). Inclination: 25.80 deg. Period: 93.23 min.

1999 February 7 - . 21:04 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7426-9.5.

Stardust - . Payload: Discovery 4. Mass: 370 kg (810 lb). Nation: USA. Agency: JPL. Manufacturer: Martin. Program: Discovery series. Class: Comet. Type: Comet probe. Spacecraft: Stardust. USAF Sat Cat: 25618 . COSPAR: 1999-003A.
Stardust was to fly within 100 km of comet 81P/Wild-2 in January 2004 and recover cometary material using an aerogel substance. A return capsule would land on a lake bed in Utah in January 2006, returning the material to earth. The launch went as planned. The second stage ignited at 21:08 GMT and its first burn put the vehicle into a 185 km x 185 km x 28 degree parking orbit at 21:14 GMT. The second stage second burn at 21:25 changed the orbit to planned values of 178 km x 7184 km x 28.5 degrees. The Star 37FM solid third stage ignited at 21:29 GMT and placed the spacecraft into a 2 year period solar orbit. The spacecraft separated at 21:31 GMT. Meanwhile, the Delta 266 second stage burned a third time on its own, until its propellants were depleted, entering a final orbit of 294 km x 6818 km x 22.5 degrees. The Stardust probe flew past Earth at a distance of 3706 km at 1115 GMT on January 15, 2001, and flew near the Moon at a distance of 98000 km at around 0200 GMT on January 16. The gravity assist flyby changed Stardust's heliocentric orbit from 0.956 x 2.216 AU x 0.0 deg to 0.983 x 2.285 AU x 3.7 deg.

1999 February 23 - . 10:29 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10.

ARGOS - . Payload: P91-1. Nation: USA. Agency: USAF SM. Manufacturer: Seal Beach. Class: Technology. Type: Ion engine technology satellite. Spacecraft: ARGOS. USAF Sat Cat: 25634 . COSPAR: 1999-008A. Apogee: 836 km (519 mi). Perigee: 821 km (510 mi). Inclination: 98.90 deg. Period: 101.50 min. ARGOS was a USAF Space Test Program P91-1 technology satellite, equipped with an ion engine, ionosphere, x-ray, and dust detectors. Much delayed, it finally was placed into orbit on the eleventh (!) launch attempt..

Sunsat - . Nation: South Africa. Agency: Boeing. Manufacturer: Stellenbosch. Class: Technology. Type: Navigation technology satellite. Spacecraft: Sunsat. USAF Sat Cat: 25636 . COSPAR: 1999-008C. Apogee: 852 km (529 mi). Perigee: 641 km (398 mi). Inclination: 96.50 deg. Period: 99.80 min. Sunsat was built by students at Stellenbosch University, South Africa and carried a small imager and a message relay payload..

Orsted - . Mass: 62 kg (136 lb). Nation: Denmark. Agency: DMI. Manufacturer: CRI. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Orsted. USAF Sat Cat: 25635 . COSPAR: 1999-008B. Apogee: 839 km (521 mi). Perigee: 638 km (396 mi). Inclination: 96.50 deg. Period: 99.60 min. Denmark's Orsted gravity gradient stabilised satellite was to map the Earth's magnetic field. It was managed and operated by the Danish Meteorological Institute in Copenhagen. The satellite's prime contractor was CRI , Copenhagen..

1999 April 15 - . 18:32 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10.

Landsat 7 - . Mass: 1,969 kg (4,340 lb). Nation: USA. Agency: NASA Greenbelt. Manufacturer: Valley Forge. Program: Landsat. Class: Earth. Type: Earth resources satellite. Spacecraft Bus: TIROS N. Spacecraft: Landsat 7. USAF Sat Cat: 25682 . COSPAR: 1999-020A. Apogee: 703 km (436 mi). Perigee: 702 km (436 mi). Inclination: 98.20 deg. Period: 98.80 min.
The vehicle entered a 175 km x 706 km x 98.2 deg initial orbit. 57 minutes after launch the Delta stage burned again to circularize the orbit at 668 km x 698 km and Landsat 7 separated from the stage. The Delta stage then burned to depletion of its propellant, into a 184 km x 710 km x 107.5 deg orbit that would decay quickly. The Landsat 7 remote sensing satellite was to be operated by NASA/Goddard until October 2000, when operations would be transferred to the US Geological Survey.

1999 May 5 - . 01:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 8930. FAILURE: Engine failure at ignition for second burn of Centaur stage.. Failed Stage: U.

Orion 3 - . Payload: HS 601HP. Mass: 4,300 kg (9,400 lb). Nation: USA. Agency: Palo Alto. Manufacturer: El Segundo. Program: Orion. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 25727 . COSPAR: 1999-024A. Apogee: 2,529 km (1,571 mi). Perigee: 2,456 km (1,526 mi). Inclination: 19.80 deg. Period: 138.60 min.
The Centaur RL-10B-2 second stage engine's combustion chamber ruptured at the beginning of the second burn. The hot gases already in the chamber vented, putting the stage/spacecraft assembly into an uncontrollable tumble. The Orion 3 communications satellite ended up in a useless parking orbit of 162 km x 1378 km x 29.5 deg. It was to have served the Asia-Pacific region for Loral Orion with 33 Ku-band and 10 C-band transponders.

1999 June 10 - . 13:48 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

Globalstar 52 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25770 . COSPAR: 1999-031A. Apogee: 1,414 km (878 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min.

Globalstar 25 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25772 . COSPAR: 1999-031C. Apogee: 1,414 km (878 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min.

Globalstar 47 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25773 . COSPAR: 1999-031D. Apogee: 1,415 km (879 mi). Perigee: 1,412 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min.

Globalstar 49 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25771 . COSPAR: 1999-031B. Apogee: 2,101 km (1,305 mi). Perigee: 2,099 km (1,304 mi). Inclination: 52.00 deg. Period: 129.50 min.

1999 June 24 - . 15:44 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7320-10.

FUSE - . Nation: USA. Agency: NASA Greenbelt. Manufacturer: Germantown. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft Bus: MidStar. Spacecraft: FUSE. USAF Sat Cat: 25791 . COSPAR: 1999-035A. Apogee: 760 km (470 mi). Perigee: 745 km (462 mi). Inclination: 25.00 deg. Period: 99.90 min.
The Delta 3-m payload fairing was successfully jettisoned and the Far Ultraviolet Spectroscopic Explorer was placed in a 754 km x 769 km x 25.0 degree initial orbit. After separation the Delta second stage then a depletion burn and was left in a 182 x 915 km x 19.1 degree orbit from which it would quickly decay out of orbit. Checkout of FUSE in orbit was proceeding well as of July 1.

1999 July 10 - . 08:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

Globalstar 32 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25851 . COSPAR: 1999-037A. Apogee: 1,414 km (878 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min.

Globalstar 51 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25854 . COSPAR: 1999-037D. Apogee: 1,414 km (878 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min.

Globalstar 30 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25852 . COSPAR: 1999-037B. Apogee: 1,415 km (879 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min.

Globalstar 35 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25853 . COSPAR: 1999-037C. Apogee: 1,415 km (879 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min.

1999 July 25 - . 07:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

Globalstar 26 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25872 . COSPAR: 1999-041A. Apogee: 1,414 km (878 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min.

Globalstar 43 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25874 . COSPAR: 1999-041C. Apogee: 2,044 km (1,270 mi). Perigee: 2,020 km (1,250 mi). Inclination: 51.90 deg. Period: 127.90 min.

Globalstar 48 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25875 . COSPAR: 1999-041D. Apogee: 1,415 km (879 mi). Perigee: 1,412 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min.

Globalstar 28 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25873 . COSPAR: 1999-041B. Apogee: 1,414 km (878 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min.

1999 August 17 - . 04:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

Globalstar 24 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25883 . COSPAR: 1999-043A. Apogee: 2,113 km (1,312 mi). Perigee: 2,108 km (1,309 mi). Inclination: 52.00 deg. Period: 129.70 min.

Globalstar 53 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25885 . COSPAR: 1999-043C. Apogee: 1,970 km (1,220 mi). Perigee: 1,961 km (1,218 mi). Inclination: 52.00 deg. Period: 126.40 min.

Globalstar 54 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25886 . COSPAR: 1999-043D. Apogee: 2,024 km (1,257 mi). Perigee: 2,021 km (1,255 mi). Inclination: 52.00 deg. Period: 127.70 min.

Globalstar 27 - . Mass: 222 kg (489 lb). Nation: USA. Agency: Globalstar. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 25884 . COSPAR: 1999-043B. Apogee: 1,414 km (878 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min.

1999 October 7 - . 12:51 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 145 - . Payload: GPS 2R-3 / GPS SVN 46. Mass: 2,030 kg (4,470 lb). Nation: USA. Agency: USAF. Manufacturer: Valley Forge. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 25933 . COSPAR: 1999-055A. Apogee: 20,202 km (12,552 mi). Perigee: 20,163 km (12,528 mi). Inclination: 52.60 deg. Period: 718.00 min. Third GPS Block 2R satellite. SVN 46 replaced SVN 50 which had been damaged by rain on Pad 17 earlier while being prepared for launch earlier in the year. Placed in Plane D Slot 2..

2000 February 8 - . 21:24 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

Globalstar M060 - . Payload: Globalstar 60. Mass: 450 kg (990 lb). Nation: USA. Agency: Globalsat. Manufacturer: Alenia, Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 26081 . COSPAR: 2000-008A. Apogee: 1,414 km (878 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min. Mobile Telephony. These four Globalstar satellites completed the Globalstar initial constellation..

Globalstar M062 - . Payload: Globalstar 62. Mass: 450 kg (990 lb). Nation: USA. Agency: Globalsat. Manufacturer: Alenia, Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 26082 . COSPAR: 2000-008B. Apogee: 1,418 km (881 mi). Perigee: 1,417 km (880 mi). Inclination: 52.01 deg. Period: 114.09 min. Mobile Telephony. .

Globalstar M063 - . Payload: Globalstar 63. Mass: 450 kg (990 lb). Nation: USA. Agency: Globalsat. Manufacturer: Alenia, Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 26083 . COSPAR: 2000-008C. Apogee: 1,415 km (879 mi). Perigee: 1,413 km (877 mi). Inclination: 52.00 deg. Period: 114.10 min. Mobile Telephony. .

Globalstar M064 - . Payload: Globalstar 64. Mass: 450 kg (990 lb). Nation: USA. Agency: Globalsat. Manufacturer: Alenia, Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: Globalstar. USAF Sat Cat: 26084 . COSPAR: 2000-008D. Apogee: 934 km (580 mi). Perigee: 915 km (568 mi). Inclination: 52.01 deg. Period: 103.43 min. Mobile Telephony. .

2000 March 25 - . 20:34 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7326-9.5.

IMAGE - . Mass: 536 kg (1,181 lb). Nation: USA. Agency: NASA Greenbelt. Manufacturer: Lockheed. Class: Earth. Type: Ionosphere satellite. Spacecraft: IMAGE. USAF Sat Cat: 26113 . COSPAR: 2000-017A. Apogee: 45,461 km (28,248 mi). Perigee: 1,408 km (875 mi). Inclination: 89.43 deg. Period: 854.09 min.
Imager for Magnetopause to Aurora Global Exploration was a MIDEX (mid-sized Explorer mission) developed by NASA-Goddard and the SWRI (Southwest Research Institute) of San Antonio, Texas. The spin-stabilised spacecraft carried a set of neutral atom and ultraviolet imagers, and antennae to study radio wavelength emissions from the magnetosphere plasma. The RPI radio plasma imager has four long wire antennae which will be deployed to a span of half a kilometre.

2000 May 11 - . 01:48 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 150 - . Payload: GPS 2R-4 / GPS SVN 51. Mass: 2,030 kg (4,470 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 26360 . COSPAR: 2000-025A. Apogee: 20,235 km (12,573 mi). Perigee: 20,127 km (12,506 mi). Inclination: 55.20 deg. Period: 717.90 min. Placed into an elliptical transfer orbit. The satellite's Thiokol Star 37 apogee motor was used to circularise the orbit at 20,000 km in Plane E Slot 1 of the constellation, replacing GPS GPS 2-1..

2000 July 16 - . 09:17 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 151 - . Payload: GPS 2R-5 / GPS SVN 44. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 26407 . COSPAR: 2000-040A. Apogee: 20,650 km (12,830 mi). Perigee: 19,715 km (12,250 mi). Inclination: 56.00 deg. Period: 718.00 min. Global Positioning satellite, placed in Plane B Slot 5. Launch delayed from June 15 and the June 21..

2000 August 23 - . 11:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 8930.

DM-F3 - . Payload: Dummy Payload. Mass: 4,348 kg (9,585 lb). Nation: USA. Agency: Seal Beach. Manufacturer: Douglas. Class: Technology. Type: Navigation technology satellite. Spacecraft: HS 601. Decay Date: 2009-02-04 . USAF Sat Cat: 26476 . COSPAR: 2000-048A. Apogee: 19,547 km (12,145 mi). Perigee: 212 km (131 mi). Inclination: 27.60 deg.
Vehicle Demonstration. Return to flight following earlier failure. The third Boeing Delta III launch was financed by the company and carried a dummy payload in order to bolster customer confidence in the new launch vehicle. The second stage ignited at an altitude of 158 km and the RL-10 shut off as planned in a 157 x 1363 km x 29.5 deg parking orbit. The engine fired again until fuel depletion, to place the vehicle in a geostationary transfer orbit of 190 x 20,655 km x 27.6 deg. This was much lower than that planned (23,400 km plus or minus 3,000 km) due to the fuel temperature and atmospheric conditions on the day of launch. The DM-F3 dummy payload was a mass model of the Orion 3 HS-601 satellite launched on the second Delta 3. The 4348 kg model was a 2.0m diameter, 1.7m high cylinder with two circular end plates, painted with black and white patterns. It was to be used by US Air Force researchers as a calibration target.

2000 November 10 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 154 - . Payload: GPS 2R-6 / GPS SVN 41. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 26605 . COSPAR: 2000-071A. Apogee: 20,244 km (12,579 mi). Perigee: 20,118 km (12,500 mi). Inclination: 55.50 deg. Period: 717.90 min.
The Delta stage 2 entered a 153 x 418 km x 37 deg parking orbit followed by a 172 x 1144 km second orbit; the PAM-D solid upper stage then fired to give SVN 41 a 20457 km apogee. The Thiokol Star 37FM solid kick motor was fired prior to November 13 to place the spacecraft in its final circular 20,000 km orbit. Placed in Plane F Slot 1 of the GPS constellation.

2000 November 21 - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7320-10.

EO-1 - . Mass: 529 kg (1,166 lb). Nation: USA. Agency: NASA Greenbelt. Manufacturer: Swales. Class: Earth. Type: Earth resources satellite. Spacecraft: EO-1. USAF Sat Cat: 26619 . COSPAR: 2000-075A. Apogee: 703 km (436 mi). Perigee: 702 km (436 mi). Inclination: 98.20 deg. Period: 98.80 min.
First use of a Delta dual payload attach fitting. The Earth Orbiter 1 satellite was part of NASA's New Millenium Program. Complementing the New Millenium's Deep Space series, EO-1 was a NASA-Goddard satellite which demonstrated technology for the next generation Landsat. It flew in formation with Landsat-7 for comparison purposes, using a hydrazine thruster to adjust its orbit. The satellite used a MIDEX-derived bus built by Swales Aerospace; dry mass was 566 kg. The main instruments were ALI (Advanced Land Imager) and the Hyperion 220-band imaging spectrometer. At 1835 GMT the Delta second stage completed its first burn and entered a 185 x 713 km x 98.2 deg transfer orbit. At 1920 GMT the orbit was circularised and EO-1 separated at 1925 GMT into a 682 x 729 km x 98.2 deg orbit.

Munin - . Mass: 529 kg (1,166 lb). Nation: Sweden. Agency: Seal Beach. Manufacturer: SISP. Class: Technology. Type: Navigation technology satellite. Spacecraft: Munin. USAF Sat Cat: 26621 . COSPAR: 2000-075C. Apogee: 1,797 km (1,116 mi). Perigee: 701 km (435 mi). Inclination: 95.40 deg. Period: 110.50 min.
The small 6 kg Munin nanosatellite was built by Swedish students in collaboration with the Swedish Insitute for Space Physics (IRF) and carried a particle detector, a spectrometer, and an auroral camera. After deployment of EO-1 and SAC-C a fourth burn put the Delta second stage in a 697 x 1800 km x 95.4 deg orbit, after which Munin was ejected from the stage.

SAC-C - . Mass: 529 kg (1,166 lb). Nation: Argentina. Agency: CONAE. Manufacturer: INVAP. Program: SAC. Class: Earth. Type: Earth resources satellite. Spacecraft: SAC-C. USAF Sat Cat: 26620 . COSPAR: 2000-075B. Apogee: 704 km (437 mi). Perigee: 701 km (435 mi). Inclination: 98.20 deg. Period: 98.80 min.
The SAC-C Satelite de Aplicaciones Cientificas C was developed by the Argentine space agency CONAE and built by the Argentine company INVAP. The 467 kg satellite carried a battery of earth observing instruments for Argentine forestry and agriculture studies. SAC-C also carried a NASA experiment which used the distortion of GPS signals observed near the horizon to derive atmospheric conditions. The DPAF dual payload support structure, derived from Ariane's SPELDA, was ejected after deployment of the EO-1 satellite from the Delta stage to reveal SAC-C. After a further Delta burn SAC-C was ejected at 1955 GMT into a 687 x 707 km x 98.3 deg orbit.

2001 January 30 - . 07:55 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 156 - . Payload: GPS 2R-7 / GPS SVN 54. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 26690 . COSPAR: 2001-004A. Apogee: 20,208 km (12,556 mi). Perigee: 20,157 km (12,524 mi). Inclination: 55.20 deg. Period: 718.00 min. GPS Block IIR production no. SV 14. Placed in Plane E Slot 4 of the constellation..

2001 April 7 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

2001 Mars Odyssey - . Mass: 725 kg (1,598 lb). Nation: USA. Agency: JPL. Class: Mars. Type: Mars probe. Spacecraft: Mars Odyssey. USAF Sat Cat: 26734 . COSPAR: 2001-013A.
The 2001 Mars Odyssey probe (formerly the Mars Surveyor 2001 Orbiter) was the first spacecraft in the revamped NASA Mars Exploration Program. Built by Lockheed Martin Astronautics (Denver) and JPL, the satellite was similar to Mars Climate Orbiter. It carried a 6-meter boom with a gamma ray spectrometer for remote sensing of Martian surface mineralogy, as well as an infrared imager and a radiation environment monitor. The probe had a dry mass of 376 kg and carried 349 kg of propellant. 2001 Mars Odyssey entered a 195 x 215 km x 52 deg parking orbit 10 minutes after launch. After a 12 minute coast the Delta second stage fired again and separated from the third stage, which placed the probe on an Earth escape trajectory into a 0.982 x 1.384 AU x 3.05 deg solar orbit. It escaped Earth's nominal gravitational sphere of influence at around 19:00 GMT on April 10.
The 2001 Mars Odyssey probe entered Mars orbit on October 24, 2001. The orbit insertion burn with the main 640 N bipropellant N2O4/hydrazine engine began at 0218 GMT lasted 20 min 19 sec. Mass of the spacecraft was then 456 kg, including 79 kg of fuel left. Initial orbit was was 272 x 26818 km x 93.42 deg with periapsis near the Martian north pole. 76 days of aerobraking began on October 26 to slowly circularise the orbit to its 400 km altitude, 2 hour period sun synchronous operational orbit. The solar panels reached 180 deg C as Odyssey skimmed through upper atmosphere of Mars on each orbit.
After reaching the operational orbit, the probe was to conduct a 917 day mapping program. It was to also serve as a communications relay for American and international landers expected to arrive in 2003/2004. In the Martian orbit, it was to map the distribution of elements and minerals on the surface, the distribution of hydrogen (embedded in water ice) and the radiation environment. The second was to assess the likelyhood of past or present life, and the third was to assess the radiation hazard to manned missions. The three major instruments on board were THEMIS (Thermal Emission Imaging System at the visible and infrared light) for the distribution, at 100 meter resolution, of minerals that form only in the presence of water, GRS (Gamma Ray Spectrometer) for determining hydrogen and other elements, and MARIE (presumably, MArs RadIation Environment) for determining the radiation hazard. THEMIS was to also enable site selection for a future manned landing. THEMIS was expected to provide 15,000 images, each covering 20 x 20 km. GRS carried two neutron monitors also. The gamma rays and neutrons come out of the surface in distinct, element-specific energies, released by cosmic ray bombardment.

2001 May 18 - . 17:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 158 - . Payload: GeoLITE. Mass: 93 kg (205 lb). Nation: USA. Agency: NRO. Manufacturer: TRW. Class: Communications. Type: Military communications satellite. Spacecraft Bus: T310. Spacecraft: GeoLITE. USAF Sat Cat: 26770 . COSPAR: 2001-020A. Apogee: 35,700 km (22,100 mi). Perigee: 179 km (111 mi). Inclination: 19.50 deg. Period: 629.01 min.
Military Communications Technology flight. Launch delayed from March 1, April 25, May 2 and 17. GeoLITE, US National Reconnaissance Office spacecraft was into placed by the Delta launch vehicle into a geostationary transfer orbit. GeoLITE was a TRW T-310 class satellite with a mass of about 1800 kg, including a solid apogee motor. The satellite carried an experimental laser communications payload and an operational UHF data relay payload.

2001 June 30 - . 19:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7425-10.

MAP - . Mass: 840 kg (1,850 lb). Nation: USA. Agency: NASA Greenbelt. Class: Astronomy. Type: Infrared astronomy satellite. Spacecraft: MAP. USAF Sat Cat: 26859 . COSPAR: 2001-027A. Apogee: 379,553 km (235,842 mi). Perigee: 4,704 km (2,922 mi). Inclination: 27.80 deg. Period: 14,669.70 min.
NASA's Microwave Anisotropy Probe (MAP) was placed in a 167 x 204 km x 28.8 deg parking orbit at 1958 GMT. At 2104 GMT the second stage ignited again for a 4 second burn, raising the orbit to around 181 x 308 km; the third stage spun up and ignited at 2108 GMT, accelerating MAP to a highly elliptical orbit of 182 x 292,492 km x 28.7 deg. MAP used on-board fuel to tweak the orbit and make a lunar flyby at fourth apogee on July 30, arriving at the L2 Earth-Moon Lagrangian point 1.5 million km from Earth three months later. From L2, MAP was to measure fluctuations in the cosmic 3 Kelvin microwave background with the degree of precision required to answer questions about the big bang and the total mass and fate of the universe. By July 22 the MAP probe was in a 4055 x 355,935 km x 28.0 deg orbit. It flew past the Moon on July 30 at 1639 GMT at an altitude of 5200 km above the lunar surface.

2001 August 8 - . 16:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7326-9.5.

Genesis - . Payload: Discovery 5. Mass: 636 kg (1,402 lb). Nation: USA. Agency: JPL, NASA. Manufacturer: Martin. Program: Discovery series. Class: Astronomy. Type: Solar satellite. Spacecraft: Genesis. USAF Sat Cat: 26884 . COSPAR: 2001-034A. Apogee: 1,175,513 km (730,428 mi). Perigee: 213,681 km (132,774 mi). Inclination: 28.00 deg. Period: 97,345.15 min.
Launch delayed from February 10 and July 30. The Genesis probe flew to the Earth-Sun L1 Lagrangian point and spend two years collecting samples of the solar wind. The collected samples were to be physically returned to Earth in a sample return capsule (air-snatch recovery was planned over Utah) and analysed in ground-based laboratories. The first burn of the Delta second stage put Genesis in a 185 x 197 km x 28.5 deg parking orbit at 1624 GMT. At 1712 GMT a second burn raised the orbit to 182 x 3811 km, and at 1713 GMT the third stage fired to put Genesis on its trajectory to L1 with a nominal apogee of around 1.2 million km. By the first week of November 2001 Genesis arrived at the Earth-Sun L1 point. A malfunctioning thermal radiator caused some concern for the health of the sample return capsule's critical battery, which was overheating, but Genesis began collecting solar wind samples on schedule.
On September 8, 2004, the Genesis space probe became the first spacecraft to return from beyond lunar orbit to the Earth's surface. The Genesis Sample Return Capsule separated from the spacecraft on September 8, 66,000 km above the Earth. The capsule successfully re-entered the atmosphere over Oregon at 11 km/s, but a wiring error resulted in the drogue parachute release mortar failing to fire at 33 km altitude. The capsule crashed to earth at 90 m/s in the Dugway Proving Ground at 40 07 40 N 113 30 29 W. Although the vehicle was smashed, some of the samples could be retrieved.

2001 October 18 - . 18:51 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7320-10.

QuickBird 2 - . Mass: 980 kg (2,160 lb). Nation: USA. Agency: DigitalGlobe. Manufacturer: Ball. Class: Surveillance. Type: Civilian surveillance satellite. Spacecraft: BCP-2000. Decay Date: 2015-01-27 . USAF Sat Cat: 26953 . COSPAR: 2001-047A. Apogee: 471 km (292 mi). Perigee: 471 km (292 mi). Inclination: 97.20 deg. Period: 94.00 min.
The QuickBird commercial imaging satellite was owned by DigitalGlobe (formerly EarthWatch) and used a Ball BCP2000 bus with a launch mass of 1028 kg and a dry mass of about 995 kg. The Delta upper stage entered a 185 x 472 km x 98.1 deg orbit at 1902 GMT. At 1948 GMT it reached apogee and fired again to deploy QuickBird into a 461 x 465 km x 97.2 deg orbit. The Delta then made a series of unusual depletion burns, lowering its perigee to 167 km and changing inclination to 108.9 deg.
Quickbird 2 was to be operational after a few months of calibration and "ground-truth" checkouts to market high resolution images. The 1.0 tonne satellite was reported to be capable of images with a resolution as small as 0.6 meter, though the standard products were to be coarser. Unlike the comparable quality images from IKONOS images, some of which are currently marketed exclusively to the US military, all Quickbird 2 images may be available in the open market.

2001 December 7 - . 15:07 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10.

Jason 1 - . Payload: TPFO. Mass: 485 kg (1,069 lb). Nation: France. Agency: CNES, NASA. Manufacturer: Cannes. Class: Earth. Type: Ionosphere satellite. Spacecraft Bus: Proteus. Spacecraft: Jason. USAF Sat Cat: 26997 . COSPAR: 2001-055A. Apogee: 1,344 km (835 mi). Perigee: 1,332 km (827 mi). Inclination: 66.10 deg. Period: 112.40 min.
Oceanography satellite, launch delayed from August 10 and September 15. Jason 1 was a joint mission between CNES (the French space agency) and NASA/JPL, following on the Topex satellite which carried the Poseidon sea surface altimeter. Jason carried Poseidon 2, as well as orbital tracking experiments and a microwave radiometer which measured the amount of water vapor, allowing path delay errors to be calibrated. The satellite used the Alcatel Proteus bus and had a dry mass of 472 kg plus 28 kg of hydrazine propellant. The JASON/TIMED mission's Boeing Delta 7920-10C second stage reached an initial orbit of 215 x 1343 km x 66.2 deg at 1517 GMT. A second burn at 1559 GMT circularized at apogee to 1320 x 1330 km x 66.0 deg, and the Jason 1 satellite was ejected at 1602 GMT.

TIMED - . Mass: 485 kg (1,069 lb). Nation: USA. Agency: CNES, NASA. Manufacturer: Cannes. Class: Astronomy. Type: Solar satellite. Spacecraft: TIMED. USAF Sat Cat: 26998 . COSPAR: 2001-055B. Apogee: 624 km (387 mi). Perigee: 623 km (387 mi). Inclination: 74.10 deg. Period: 97.20 min.
TIMED was the first NASA Solar Terrestrial Probe, operated by Johns Hopkins Applied Physics Lab to study the thermosphere, mesosphere and lower ionosphere. TIMED was built in-house at APL and had a mass of 587 kg; the project was managed at NASA-Goddard. It measured solar and auroral energy input, atmospheric cooling rates, and atmospheric composition, temperature and wind profiles.
Five minutes after deploying the JASON satellite, the DPAF adapter atop the Delta upper stage separated to reveal the TIMED satellite inside it. Burn 3 at 1614 GMT put Delta/TIMED in a descending 636 x 1330 km x 71.3 deg orbit; at perigee at 1706 GMT a fourth burn circularized the orbit at 627 x 640 km x 74.1 deg and TIMED was ejected six minutes later. A final depletion burn left the Delta stage in a low perigee orbit.

2002 February 11 - . 17:43 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

Iridium 90 - . Payload: Iridium s/n SV 90. Mass: 690 kg (1,520 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 27372 . COSPAR: 2002-005A. Apogee: 684 km (425 mi). Perigee: 660 km (410 mi). Inclination: 86.60 deg. Period: 98.20 min.

Iridium 96 - . Payload: Iridium s/n SV 96. Mass: 690 kg (1,520 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 27376 . COSPAR: 2002-005E. Apogee: 679 km (421 mi). Perigee: 665 km (413 mi). Inclination: 86.60 deg. Period: 98.20 min.

Iridium 95 - . Payload: Iridium s/n SV 95. Mass: 690 kg (1,520 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. USAF Sat Cat: 27375 . COSPAR: 2002-005D. Apogee: 679 km (421 mi). Perigee: 665 km (413 mi). Inclination: 86.60 deg. Period: 98.20 min.
Mobile Telephony satellite. Return to flight after GEM solid booster failure on GBI launch. Launch delayed from February 8, 9 and 10. Five Motorola Iridium satellites were launched for Iridium Satellite LLC, the new company that bought out the bankrupt Iridium LLC. This was the first system replenishment launch since the bankruptcy.

Iridium 91 - . Payload: Iridium s/n SV 91. Mass: 690 kg (1,520 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2019-01-23 . USAF Sat Cat: 27373 . COSPAR: 2002-005B. Apogee: 679 km (421 mi). Perigee: 665 km (413 mi). Inclination: 86.60 deg. Period: 98.20 min.

Iridium 94 - . Payload: Iridium s/n SV 94. Mass: 690 kg (1,520 lb). Nation: USA. Agency: Iridium. Manufacturer: Lockheed, Motorola. Program: Iridium. Class: Communications. Type: Civilian communications satellite. Spacecraft: LM 700. Decay Date: 2018-04-18 . USAF Sat Cat: 27374 . COSPAR: 2002-005C. Apogee: 677 km (420 mi). Perigee: 667 km (414 mi). Inclination: 86.60 deg. Period: 98.20 min.

2002 May 4 - . 09:54 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10L.

Aqua - . Payload: EOS-PM1. Mass: 2,934 kg (6,468 lb). Nation: USA. Agency: NASA. Manufacturer: TRW. Class: Earth. Type: Earth resources satellite. Spacecraft: Aqua. USAF Sat Cat: 27424 . COSPAR: 2002-022A. Apogee: 706 km (438 mi). Perigee: 699 km (434 mi). Inclination: 98.20 deg. Period: 98.80 min.
Climatology and environment satellite. Launch delayed from December 20, 2001, and January 30, April 18 and 26, May 2. NASA's Aqua remote sensing satellite was placed in a 185 x 707 km x 98.1 deg transfer orbit at 1006 UTC. A second burn of the second stage of the Delta at 1048:58 UTC put Aqua in a 676 x 687 km x 98.2 deg orbit.

2002 July 3 - . 06:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7425-9.5.

Contour - . Payload: Discovery 6. Mass: 1,005 kg (2,215 lb). Nation: USA. Agency: Cornell, NASA. Manufacturer: APL. Program: Discovery series. Class: Comet. Type: Comet probe. Spacecraft: Contour. USAF Sat Cat: 27457 . COSPAR: 2002-034A. Apogee: 108,614 km (67,489 mi). Perigee: 212 km (131 mi). Inclination: 30.60 deg. Period: 2,486.10 min.
Launch delayed from July 1st. The latest NASA Discovery mission was successfully launched on Jul 3. The CONTOUR (Comet Nucleus Tour) probe, built and operated by the Johns Hopkins University's Applied Physics Laboratory (APL), began its five year mission to explore three comets, using repeated encounters with the earth to modify its orbit in order to reach each target. The first burn of the second stage completed at 0659 UTC putting the spacecraft in a 185 x 197 km x 29.7 deg parking orbit. At 0746 UTC the second stage restarted for a short 4s burn to 185 x 309 km x 29.7 deg, and then separated once the PAM-D (ATK Star 48B) solid third stage was spun up. The 1.5 minute burn of the third stage motor at 0748 UTC put it and CONTOUR in a 90 x 106689 km x 30.5 deg phasing orbit. By July 8 CONTOUR's orbit was 214 x 106686 km x 29.8 deg. CONTOUR stayed in this phasing orbit until August 15, when it was injected into solar orbit using its internal ATK Star 30 solid motor. Flyby of the first target, comet 2P/Encke, was scheduled for Nov 2003.

2003 January 13 - . 00:45 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7320-10.

ICESat - . Payload: EOS-LAM. Mass: 1,000 kg (2,200 lb). Nation: USA. Agency: NASA. Manufacturer: Ball. Class: Earth. Type: Sea satellite. Spacecraft: BCP-2000. Decay Date: 2010-08-30 . USAF Sat Cat: 27642 . COSPAR: 2003-002A. Apogee: 610 km (379 mi). Perigee: 593 km (368 mi). Inclination: 94.01 deg. Period: 96.56 min. Oceanography, gravimetry, altimetry mission. Delayed from March 30, May 12, August 30, September 10, December 15 and 20, 2002; and Jan. 11 and 12, 2003..

CHIPSat - . Payload: CHIPSat BD 2. Mass: 85 kg (187 lb). Nation: USA. Agency: NASA. Manufacturer: SpaceDev. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: CHIPSat. USAF Sat Cat: 27643 . COSPAR: 2003-002B. Apogee: 601 km (373 mi). Perigee: 585 km (363 mi). Inclination: 94.01 deg. Period: 96.39 min. Astrophysics mission. Delayed from March 30, May 12, August 30, September 10, December 15 and 20, 2002; and Jan. 11 and 12, 2003..

2003 January 29 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 166 - . Payload: GPS 2R-8 / Navstar 51. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 27663 . COSPAR: 2003-005A. Apogee: 20,352 km (12,646 mi). Perigee: 20,163 km (12,528 mi). Inclination: 55.06 deg. Period: 720.74 min. Launch delayed from June 11 and August 16, 2001; March 6, April 29, August 11 and November 7, 2002..

XSS-10 - . Mass: 28 kg (61 lb). Nation: USA. Manufacturer: USAF RL. Class: Technology. Type: Rendezvous technology satellite. Spacecraft: XSS. USAF Sat Cat: 27664 . COSPAR: 2003-005B. Apogee: 811 km (503 mi). Perigee: 524 km (325 mi). Inclination: 39.75 deg. Period: 97.95 min.
On-orbit servicing technology demonstrator. XSS-10, a 28 kilogram microsatellite, was launched as a secondary payload aboard the Delta 2 launch vehicle carrying a Global Positioning Satellite (GPS) satellite. The mission demonstrated the complex interactions of line-of-sight guidance with basic inertial maneuvering. The micro-satellite was attached to the Delta 2 second stage. Once the second stage separated from the GPS satellite, the microsatellite waited for a sunlit Air Force Space Control Network pass before ejecting from the second stage. Once ejected, the microsatellite commenced an autonomous inspection sequence around the second stage, and live video was transmitted to ground stations. The entire mission lasted only 24 hours. Launch delayed from June 11 and August 16, 2001; March 6, April 29, August 11 and November 7, 2002.

2003 March 31 - . 22:09 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 168 - . Payload: GPS 2R-9 / Navstar 52. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 27704 . COSPAR: 2003-010A. Apogee: 20,376 km (12,661 mi). Perigee: 19,985 km (12,418 mi). Inclination: 55.00 deg. Period: 717.90 min. Delayed from May 16, July 25, November 14, 2002, and February 6, 2003. Timely replenishment of GPS constellation..

2003 June 10 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

Spirit (Mars Exploration Rover A, MER-2) - . Payload: MER-A. Mass: 1,063 kg (2,343 lb). Nation: USA. Agency: NASA. Manufacturer: JPL. Class: Mars. Type: Mars probe. Spacecraft: MER. Decay Date: 2004-01-03 . USAF Sat Cat: 27827 . COSPAR: 2003-027A. Mars rover, placed in a 1.014 AU x 1.531 AU x 0.2 deg solar orbit. Anticipated landing on Mars on Launch delayed from May 30, June 6, 8 and 9. Payload included 530 kg Mars lander total mass, 170 kg Mars Rover mass...

2003 July 8 - . 04:18 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925H.

Opportunity (Mars Exploration Rover B, MER-1) - . Mass: 1,063 kg (2,343 lb). Nation: USA. Agency: JPL. Class: Mars. Type: Mars probe. Spacecraft: MER. Decay Date: 2004-01-25 . USAF Sat Cat: 27849 . COSPAR: 2003-032A.
NASA's second Mars Exploration Rover, MER-B (MER-1) 'Opportunity', was launched by a Delta 7925H, which was similar to the standard 7925 model but with larger GEM-46 solid strapon motors previously used only on the Delta III 8930. MER-B separated from the Delta third stage at 0436 UTC and was then on its way to Mars. The launch had been delayed from June 26, 29 and 30, July 3, 6 and 7. Mass included cruise stage, lander and rover. Rover mass was 170 kg, lander 360 kg.

2003 August 25 - . 05:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7920H.

SIRTF - . Mass: 923 kg (2,034 lb). Nation: USA. Agency: NASA. Class: Astronomy. Type: Infrared astronomy satellite. Spacecraft: SIRTF. USAF Sat Cat: 27871 . COSPAR: 2003-038A.
Originally to have launched January 9, 2003. Delayed six times. The Space Infrared Telescope Facility (SIRTF) was the last of NASA's 'Great Observatories'. It had a 0.85-meter infrared telescope, with a liquid-helium cooled focal plane carrying the three main instruments. SIRTF was launched by the second Delta II Heavy. The second stage entered a 166 x 167 km x 31.5 deg Earth parking orbit, and after about 33 minutes of coast, passing south of Madagascar, restarted at 0613 UTC to enter a hyperbolic orbit with a perigee of 170 km, an eccentricity of 1.0061, and a velocity of 11.05 km/s. This placed it in a solar orbit of 0.996 x 1.019 AU x 1.14 deg with a year about 4 days longer than Earth's.

2003 December 21 - . 08:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 175 - . Payload: GPS 2R-10 / Navstar 53 / GPS SVN 47. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 28129 . COSPAR: 2003-058A. Apogee: 20,328 km (12,631 mi). Perigee: 19,963 km (12,404 mi). Inclination: 55.10 deg. Period: 716.50 min. Tenth Navstar Block IIR (R = replenishment) launch..

2004 March 20 - . 17:53 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 177 - . Payload: GPS 2R-11 / Navstar 54. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 28190 . COSPAR: 2004-009A. Apogee: 20,268 km (12,593 mi). Perigee: 20,100 km (12,400 mi). Inclination: 55.00 deg. Period: 718.00 min. Launch delayed from December 19, 2003, March 8, 2004..

2004 April 20 - . 16:57 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

Gravity Probe B - . Mass: 3,145 kg (6,933 lb). Nation: USA. Agency: NASA. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: Gravity Probe-B. USAF Sat Cat: 28230 . COSPAR: 2004-014A. Apogee: 646 km (401 mi). Perigee: 640 km (390 mi). Inclination: 90.00 deg. Period: 97.60 min.
Gravity Probe B's mission was to confirm a prediction of Einstein's theory of relativity. The physics experiment, developed by Stanford University and Lockheed Martin, was to observe the magnitude 5 star IM Pegasi for over a year, attempting to measure the tiny shifts in the spacecraft gyroscopes' orientation caused by the Lense-Thirring gravitomagnetic (or `frame-dragging') effect. To accomplish this the spacecraft carried four gyroscopes kept at 1.8 deg Kelvin by a liquid helium dewar, laser retroreflectors and two GPS receivers for orbit determination, a drag compensation system, and a 14 cm aperture quartz telescope. The satellite was also to make an accurate measurement of the already-established gravitostatic warping of spacetime due to the Earth's mass.

2004 June 23 - . 22:54 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 178 - . Payload: GPS 2R-12 / Navstar 55. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 28361 . COSPAR: 2004-023A. Apogee: 20,273 km (12,597 mi). Perigee: 20,090 km (12,480 mi). Inclination: 55.10 deg. Period: 717.90 min. Delayed from February 17. Delayed from June 5, 11, 13, 14, 16, 18, 19, 20 and 21. Moved up from July 20..

2004 July 15 - . 10:02 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10L.

Aura - . Payload: EOS-CHEM1 / T330 (AB1200). Mass: 2,967 kg (6,541 lb). Nation: USA. Agency: NASA. Manufacturer: TRW. Class: Earth. Type: Atmosphere satellite. Spacecraft: Aura. USAF Sat Cat: 28376 . COSPAR: 2004-026A. Apogee: 694 km (431 mi). Perigee: 688 km (427 mi). Inclination: 98.20 deg. Period: 98.60 min. Atmosphere Dynamics & Chemistry. Delayed from January 29, February 6, March 19, June 17, 19 and 26, July 8, 10, 11, 13 and 14..

2004 August 3 - . 06:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925H.

Messenger - . Payload: Discovery 8. Mass: 1,066 kg (2,350 lb). Nation: USA. Agency: NASA. Manufacturer: APL. Program: Discovery series. Class: Mercury. Type: Mercury probe. Spacecraft: Messenger. USAF Sat Cat: 28391 . COSPAR: 2004-030A. Apogee: 0 km (0 mi). Perigee: 0 km (0 mi). Inclination: 0.00 deg. Period: 0.00 min.
The NASA Messenger probe to Mercury was was first placed into a parking orbit. The Delta booster second stage's second burn raised the orbit, then the PAM-D solid motor burned to put the probe on an escape trajectory into a 0.92 x 1.08 AU x 6.4 deg heliocentric orbit. Messenger (Mercury Surface, Space Environment, Geochemistry and Ranging) was to make an Earth flyby on August 1, 2005; Venus flybys in 2006 and 2007; and Mercury encounters in January and October 2008 , September 2009 and March 2011 . On this last encounter the Aerojet 660N engine was to fire to put Messenger into a 200 x 15,193 km x 80 deg orbit around Mercury. Launch delayed from March 10, May 11, August 2

2004 November 6 - . 05:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 180 - . Payload: GPS 2R-13 / Navstar 61. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 28474 . COSPAR: 2004-045A. Apogee: 20,413 km (12,684 mi). Perigee: 19,810 km (12,300 mi). Inclination: 54.90 deg. Period: 715.10 min. Launch delayed from September 22, October 8, 25 and 30, November 5. Fired its apogee motor at around 02:40 GMT on November 9 to transfer from its initial 159 x 20380 km x 39.1 deg transfer orbit to its operational orbit in the GPS constellation..

2004 November 20 - . 17:16 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7320-10C.

Swift - . Payload: SA-200LL. Mass: 1,331 kg (2,934 lb). Nation: USA. Agency: NASA. Manufacturer: Gilbert. Class: Astronomy. Type: Gamma ray astronomy satellite. Spacecraft Bus: SA-200. Spacecraft: Swift. USAF Sat Cat: 28485 . COSPAR: 2004-047A. Apogee: 604 km (375 mi). Perigee: 584 km (362 mi). Inclination: 20.60 deg. Period: 96.60 min. NASA Medium-class Explorer satellite dedicated to study of gamma ray bursts, the third after the IMAGE and WMAP satellites. Delayed from December 5 and 29, 2003, January 14, April 29, July 15, September 1, October 7 and 26, November 8, 11, 17, 18 and 19..

2005 January 12 - . 18:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

Deep Impact - . Payload: Discovery 7. Mass: 601 kg (1,324 lb). Nation: USA. Agency: Seal Beach. Program: Discovery series. Class: Comet. Type: Comet probe. Spacecraft: Deep Impact. USAF Sat Cat: 28517 . COSPAR: 2005-001A.
Launched into a 0.981 AU x 1.628 AU solar orbit inclined 0.6 deg to the ecliptic. Deep Impact was to fly by Comet 9P/Tempel-1 on 3 July 2005. An impacter it released was to hit the comet on 4 July at 10.2 km/s, producing a crater and ejecta plume that would allow the flyby spacecraft to determine the composition and structure of the comet's nucleus.

2005 May 20 - . 10:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7320-10C.

NOAA 18 - . Payload: NOAA-N. Mass: 1,420 kg (3,130 lb). Nation: USA. Agency: NOAA. Manufacturer: Lockheed. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Advanced Tiros N. USAF Sat Cat: 28654 . COSPAR: 2005-018A. Apogee: 866 km (538 mi). Perigee: 847 km (526 mi). Inclination: 98.70 deg. Period: 102.10 min. Delayed from June 30, 2004, February 12, March 10 and 19, May 11, 12, 13 and 14..

2005 September 26 - . 03:37 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 183 - . Payload: GPS 2R-14M / Navstar 57. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 28874 . COSPAR: 2005-038A. Apogee: 20,187 km (12,543 mi). Perigee: 20,006 km (12,431 mi). Inclination: 55.00 deg. Period: 714.50 min.
Delayed from December 2004; February 1, March 17, 2005. Moved up from May 20 2005. Then delayed from May 4, July 29, August 26, September 22, 2005. Became operational at 23:30 GMT on 16 December. First GPS Block IIR-M version, which added extra navigation signals for both civil and military users. The NASA-funded L2C tracking demonstration was managed by JPL and explored the use of a new Civilian code signal (L2C). The data was collected with Trimble NetRS receivers L2C-enabled firmware. The sites were globally distributed: South Africa, Norway, Antarctica, Hawaii, and Alaska.

2006 April 28 - . 10:02 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

Cloudsat - . Mass: 848 kg (1,869 lb). Nation: USA. Agency: CSA, NASA, USAF. Manufacturer: Ball. Class: Earth. Type: Weather satellite. Spacecraft: BCP-2000. USAF Sat Cat: 29107 . COSPAR: 2006-016A. Apogee: 704 km (437 mi). Perigee: 702 km (436 mi). Inclination: 98.20 deg. Period: 98.80 min. Cloudsat carried a 94 GHz cloud profiling radar. Both the Cloudsat and Calipso satellites were in the A-train polar constellation, in the same orbit as the large Aqua and Aura satellites..

Calipso - . Mass: 587 kg (1,294 lb). Nation: USA. Agency: CNES, NASA. Manufacturer: Alenia. Class: Earth. Type: Weather satellite. Spacecraft Bus: Proteus. Spacecraft: Calipso. USAF Sat Cat: 29108 . COSPAR: 2006-016B. Apogee: 703 km (436 mi). Perigee: 702 km (436 mi). Inclination: 98.20 deg. Period: 98.80 min. Calipso carried a 1-meter laser lidar telescope to study clouds and aerosols, and an imaging infrared radiometer..

2006 June 21 - . 22:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 187 - . Payload: MiTEx-A. Mass: 225 kg (496 lb). Nation: USA. Agency: DARPA. Manufacturer: OSC. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: GEOStar-1. Spacecraft: Mitex. USAF Sat Cat: 29240 . COSPAR: 2006-024A. Apogee: 36,222 km (22,507 mi). Perigee: 184 km (114 mi). Inclination: 25.25 deg. Period: 639.26 min.
The Microsatellite Technology Experiment was a classified mission, believed to be a test of prototype inspect-and-disable satellites that would control the constellation of geostationary satellites on which the world depends for television reception and communications. Each microsatellite, one built by Orbital Sciences, and the other by Lockheed Martin, had a mass of about 250 kg. They were believed to be solar-powered and equipped with propulsion systems that would allow them to rendezvous with geosynchronous satellites. Once they had reached the satellite, they would presumably be capable of destroying, disabling, or jamming them. To deliver the two satellites to near-synchronous orbit, a Naval Research Laboratory liquid propellant bus equipped with a 400 N main engine and solar panels was used.

USA 188 - . Payload: MiTEx-B. Mass: 225 kg (496 lb). Nation: USA. Agency: DARPA. Manufacturer: Lockheed. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: GEOStar-1. Spacecraft: Mitex. USAF Sat Cat: 29241 . COSPAR: 2006-024B.

USA 189 - . Payload: MiTEx Vehicle. Mass: 250 kg (550 lb). Nation: USA. Agency: NRL. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: GEOStar-1. Spacecraft: Mitex. USAF Sat Cat: 29242 . COSPAR: 2006-024C.

2006 September 25 - . 18:50 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 190 - . Payload: GPS 2R-15M / Navstar 52. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: Seal Beach. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 29486 . COSPAR: 2006-042A. Apogee: 20,342 km (12,639 mi). Perigee: 20,020 km (12,430 mi). Inclination: 54.90 deg. Period: 717.90 min. Second GPS Block IIR-M version, which added extra navigation signals for both civil and military users..

2006 October 26 - . 00:52 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925-10L.

Stereo Ahead - . Mass: 1,240 kg (2,730 lb). Nation: USA. Agency: Seal Beach. Class: Astronomy. Type: Solar satellite. Spacecraft: Stereo. USAF Sat Cat: 29510 . COSPAR: 2006-047A.
The booster was used to put the twin spacecraft in a 182 km x 403,810 km x 28.5 deg lunar transfer orbit. They would use a series of lunar flybys to eventually place themselves in two different solar orbits: Stereo Ahead in a 0.95 AU x 0.97 AU x 0.12 Deg / 344 day orbit around the Sun leading the Earth, and Stereo Behind in a 0.99 AU x 1.09 AU x 0.03 deg / 389 day orbit trailing the Earth. The satellites were equipped with optical, ultraviolet, radio, and particle sensors that would allow them to form a three-dimensional image of the sun's corona using identical sensors from two vantage points at the same moment.

Stereo Behind - . Nation: USA. Agency: Seal Beach. Class: Astronomy. Type: Solar satellite. Spacecraft: Stereo. USAF Sat Cat: 29511 . COSPAR: 2006-047B.
Communications with the STEREO-B science craft in solar orbit had been lost on 2014 Oct 1 for unknown reasons; by 2016 it was assumed the mission had been lost, but on Aug 21 the big DSS-14 dish at Goldstone picked up a signal from it. This was great news for the heliophysics community, but attempts to recover full communications with the tumbling and underpowered spacecraft have met with mixed success, and as of Oct 11 recovery attempts were scaled back until STEREO-B drifts into a more favorable attitude and orbital position.

2006 November 17 - . 19:12 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 192 - . Payload: GPS 2R-16M / Navstar 59. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 29601 . COSPAR: 2006-052A. Apogee: 20,367 km (12,655 mi). Range: 55 km (34 mi). Perigee: 20,206 km (12,555 mi). Inclination: 54.90 deg. Period: 722.20 min. Set operational at 03:07 GMT on 12 December..

2006 December 14 - . 21:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

USA 193 - . Nation: USA. Agency: Seal Beach. Class: Technology. Type: Military technology satellite. Spacecraft: USA 193. Decay Date: 2008-02-29 . USAF Sat Cat: 29651 . COSPAR: 2006-057A. Apogee: 376 km (233 mi). Perigee: 354 km (219 mi). Inclination: 58.50 deg. Period: 91.83 min.
Classifed NRO mission of uncertain objectives, possibly military observation with a mixed payload. Later it was revealed the on-board propulsion system had completely failed, putting the satellite in a rapidly-decaying orbit. The Pentagon said that the hydrazine propellant aboard consituted a risk and announced they would shoot the satellite down. The real objective may have been to demonstrate US antisatellite capability after a Chinese test in 2007. In any case, on 21 February 2008 the satellite was down to a 242 km x 257 km orbit. At 03:26 GMT an SM-3 missile was fired from the Aegis cruiser USS Lake Erie stationed west of Hawaii to intercept the satellite. The hit-to-kill warhead successfully rammed the satellite, breaking it up into 153 catalogued items of debris with perigees of 170-250 km and apogees of up to 2700 km.

2007 February 17 - . 23:01 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925-10C.

Themis P1 - . Payload: Themis A. Mass: 125 kg (275 lb). Nation: USA. Agency: NASA. Manufacturer: Swales. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Themis. USAF Sat Cat: 30580 . COSPAR: 2007-004A. Apogee: 87,254 km (54,217 mi). Perigee: 1,003 km (623 mi). Inclination: 14.10 deg. Period: 1,882.70 min.
The five simultaneously-launched Time History of Events and Macroscale Interactions during Substorms (THEMIS) satellites were the fifth medium-class mission under NASA's Explorer Program. They formed part of a combined ground- and space- based system designed to determine what physical process in near-Earth space initiate the violent eruptions of the aurora that occur during substorms in the Earth's magnetosphere.

Themis P2 - . Payload: Themis B. Mass: 125 kg (275 lb). Nation: USA. Agency: NASA. Manufacturer: Swales. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Themis. USAF Sat Cat: 30581 . COSPAR: 2007-004B. Apogee: 87,114 km (54,130 mi). Perigee: 1,004 km (623 mi). Inclination: 14.10 deg. Period: 1,878.80 min.

Themis P3 - . Payload: Themis C. Mass: 125 kg (275 lb). Nation: USA. Agency: NASA. Manufacturer: Swales. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Themis. USAF Sat Cat: 30582 . COSPAR: 2007-004C. Apogee: 87,792 km (54,551 mi). Perigee: 736 km (457 mi). Inclination: 14.20 deg. Period: 1,890.30 min.

Themis P4 - . Mass: 125 kg (275 lb). Nation: USA. Agency: NASA. Manufacturer: Swales. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Themis. USAF Sat Cat: 30797 . COSPAR: 2007-004D. Apogee: 67,517 km (41,953 mi). Perigee: 4,048 km (2,515 mi). Inclination: 4.60 deg. Period: 1,435.90 min.

Themis P5 - . Mass: 125 kg (275 lb). Nation: USA. Agency: NASA. Manufacturer: Swales. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Themis. USAF Sat Cat: 30798 . COSPAR: 2007-004E. Apogee: 67,523 km (41,956 mi). Perigee: 4,045 km (2,513 mi). Inclination: 5.10 deg. Period: 1,436.00 min.

2007 June 8 - . 02:34 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

Cosmo-SkyMed 1 - . Mass: 1,700 kg (3,700 lb). Nation: Italy. Agency: ASI. Manufacturer: Alenia. Class: Surveillance. Type: Civilian Radarsat. Spacecraft Bus: Prima. Spacecraft: Cosmo-SkyMed. USAF Sat Cat: 31598 . COSPAR: 2007-023A. Apogee: 626 km (388 mi). Perigee: 622 km (386 mi). Inclination: 97.90 deg. Period: 97.20 min. The first of four Constellation of Small Satellites for Mediterranean basin Observation, Synthetic Aperture Radar satellites for primarily Italian military surveillance, but with products made available to civilian users as well..

2007 August 4 - . 09:26 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

Phoenix - . Mass: 680 kg (1,490 lb). Nation: USA. Agency: NASA. Class: Mars. Type: Mars probe. Spacecraft: Phoenix. Decay Date: 2008-05-25 . USAF Sat Cat: 32003 . COSPAR: 2007-034A.
Mars lander based on surplus hardware from the cancelled Mars Surveyor 2001 and the failed Mars Polar Lander (whence the Phoenix designation). The planned landing location was in the north of Mars, at Vastitas Borealis. The spacecraft consisted of a cruise stage, aeroshell for re-entry, backshell for protection of the lander, parachute system for braking the lander after re-entry, and liquid propellant rocket system for a soft touchdown on the surface. The lander was equipped with a robotic arm, soil analysis instruments, meteorology instruments, and cameras.

2007 September 18 - . 18:35 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

WorldView 1 - . Mass: 2,500 kg (5,500 lb). Nation: USA. Agency: Martin. Class: Surveillance. Type: Civilian surveillance satellite. Spacecraft Bus: BCP-5000. Spacecraft: WorldView. USAF Sat Cat: 32060 . COSPAR: 2007-041A. Apogee: 496 km (308 mi). Perigee: 492 km (305 mi). Inclination: 97.50 deg. Period: 94.50 min. Spacecraft was equipped with a 0.6-m aperture telescope for high resolution surveillance. Civilian, but primary customer was to be the US National Geospatial Intelligence Agency..

2007 September 27 - . 11:34 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925H.

Dawn - . Mass: 1,218 kg (2,685 lb). Nation: USA. Agency: Martin. Class: Surveillance. Type: Civilian surveillance satellite. Spacecraft: Dawn. USAF Sat Cat: 32249 . COSPAR: 2007-043A.
Asteroid belt unmanned probe designed to first orbit and survey the asteroid Vesta, and then fly on to the largest asteroid, Ceres. The Delta upper stage boosted the spacecraft and PAM-D solid third stage to 9.01 km/sec and a 185 km x 6835 km orbit. The PAM-D fired at 12:29 GMT and released Dawn after accelerating it to 11.50 km/sec and sending it into a 1.00 AU x 1.62 AU x 0.5 deg solar orbit. The ion engines were ignited on 6 October. Using its ion engines and a Mars flyby in February 2009, Dawn was scheduled to reach Vesta in 2011 and Ceres in 2015.

2007 October 17 - . 12:23 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 196 - . Payload: GPS 2R-17M / Navstar 55. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: USAF. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 32260 . COSPAR: 2007-047A. Apogee: 20,213 km (12,559 mi). Perigee: 20,149 km (12,519 mi). Inclination: 54.90 deg. Period: 717.90 min. Set operational at 22:46 GMT on 31 October..

2007 December 9 - . 02:31 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

Cosmo-SkyMed 2 - . Mass: 1,700 kg (3,700 lb). Nation: Italy. Agency: ASI. Manufacturer: Alenia. Class: Surveillance. Type: Civilian Radarsat. Spacecraft Bus: Prima. Spacecraft: Cosmo-SkyMed. USAF Sat Cat: 32376 . COSPAR: 2007-059A. Apogee: 624 km (387 mi). Perigee: 621 km (385 mi). Inclination: 97.90 deg. Period: 97.20 min. Second Italian military radar satellite in the Cosmo-Skymed system..

2007 December 20 - . 20:04 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 199 - . Payload: GPS 2R-5M / Navstar 61. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: Martin. Manufacturer: Lockheed. Program: Navstar. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 32384 . COSPAR: 2007-062A. Apogee: 20,283 km (12,603 mi). Perigee: 20,082 km (12,478 mi). Inclination: 55.00 deg. Period: 718.00 min. Fifth GPS SV with L2C capability..

2008 March 15 - . 06:10 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 201 - . Payload: GPS 2R-19M / Navstar 62 / SVN 48. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: Martin. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 32711 . COSPAR: 2008-012A. Apogee: 20,223 km (12,565 mi). Perigee: 20,142 km (12,515 mi). Inclination: 55.10 deg. Period: 718.00 min.
The Delta's second stage first cutoff at 06:20 GMT put the stage and payload into a 174 km x 205 km parking orbit. The stage fired again to place the satellite into a 188 km x 20325 km x 40.0 deg transfer orbit. USA 201 fired its apogee motor at 09:21 GMT on 17 March in and placed itself into its operational final orbit.

2008 June 11 - . 16:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7920H.

Fermi Gamma Ray Space Telescope - . Payload: SA-200HP. Mass: 500 kg (1,100 lb). Nation: USA. Agency: Martin. Class: Astronomy. Type: Gamma ray astronomy satellite. Spacecraft: SA-200. USAF Sat Cat: 33053 . COSPAR: 2008-029A. Apogee: 562 km (349 mi). Perigee: 542 km (336 mi). Inclination: 25.60 deg. Period: 95.70 min. Gamma-ray Large Area Space Telescope; renamed Fermi GST after launch..

2008 June 20 - . 07:46 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7320-10C.

Jason 2 - . Mass: 506 kg (1,115 lb). Nation: France. Agency: Martin. Class: Earth. Type: Earth resources satellite. Spacecraft: Proteus. USAF Sat Cat: 33105 . COSPAR: 2008-032A. Apogee: 1,344 km (835 mi). Perigee: 1,332 km (827 mi). Inclination: 66.00 deg. Period: 112.40 min. Ocean Surface Topography Mission follow-on to Jason 1. Carried Poseidon-3 altimeter for precision measurement of ocean surface and the NASA Advanced Microwave Radiometer to measure atmospheric moisture in the path of the altimeter beam..

2008 September 6 - . 18:51 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

GeoEye-1 - . Mass: 1,923 kg (4,239 lb). Nation: USA. Agency: Martin. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: SA-200. USAF Sat Cat: 33331 . COSPAR: 2008-042A. Apogee: 687 km (426 mi). Perigee: 670 km (410 mi). Inclination: 98.10 deg. Period: 98.30 min. Commercial optical surveillance satellite with an 0.4-meter resolution. Primary customer was the US National Geospatial Intelligence Agency..

2008 October 25 - . 02:28 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

COSMO 3 - . Mass: 1,900 kg (4,100 lb). Nation: Italy. Agency: Martin. Class: Surveillance. Type: Civilian Radarsat. Spacecraft Bus: Prima. Spacecraft: Cosmo-SkyMed. USAF Sat Cat: 33412 . COSPAR: 2008-054A. Apogee: 623 km (387 mi). Perigee: 622 km (386 mi). Inclination: 97.90 deg. Period: 97.20 min. Part of Italy's all-weather military surveillance constellation; carried X-band synthetic aperture radar..

2009 February 6 - . 10:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7320-10C.

NOAA 19 - . Payload: NOAA-O. Mass: 1,420 kg (3,130 lb). Nation: USA. Agency: NOAA. Manufacturer: Lockheed. Program: Tiros. Class: Earth. Type: Weather satellite. Spacecraft: Advanced Tiros N. USAF Sat Cat: 33591 . COSPAR: 2009-005A. Apogee: 867 km (538 mi). Perigee: 845 km (525 mi). Inclination: 98.80 deg. Period: 102.10 min.

2009 March 7 - . 03:50 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7925-10L.

Kepler - . Mass: 1,050 kg (2,310 lb). Nation: USA. Agency: Martin. Class: Astronomy. Type: Interstellar planetary detection satellite. Spacecraft: Kepler. USAF Sat Cat: 34380 . COSPAR: 2009-011A.
Used a 0.95-meter aperture differential photometer with a 105 deg2 field of view to constantly view 145,000 main-sequence stars, detecting planets orbiting around those stars when the planets passed in front of them, dimming them during transit. In its first three years of operation, Kepler detected over 2,000 possible planets, and it was determined that 5.4% of all stars host Earth-size planet candidates, and that 17% of all stars had planets.

2009 March 24 - . 08:34 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 203 - . Payload: Navstar 63 / GPS SVN 49. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: Martin. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 34661 . COSPAR: 2009-014A. Apogee: 20,272 km (12,596 mi). Perigee: 20,093 km (12,485 mi). Inclination: 55.10 deg. Period: 718.00 min. Carried the first civil L5 signal..

2009 May 5 - . 20:24 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

USA 205 - . Payload: STSS-ATRR. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: Martin. Class: Surveillance. Type: Orbital object tracking satellite. Spacecraft: SA-200. USAF Sat Cat: 34903 . COSPAR: 2009-023A. Space Tracking and Surveillance System Advanced Technology Risk Reduction satellite..

2009 August 17 - . 10:35 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. Launch Pad: SLC17A. LV Family: Thor. Launch Vehicle: Delta 7925-9.5.

USA 206 - . Payload: Navstar 64 / GPS SVN 50. Mass: 2,032 kg (4,479 lb). Nation: USA. Agency: Martin. Class: Navigation. Type: Navigation satellite. Spacecraft Bus: AS 4000. Spacecraft: GPS Block 2R. USAF Sat Cat: 35752 . COSPAR: 2009-043A. Apogee: 20,228 km (12,569 mi). Perigee: 20,138 km (12,513 mi). Inclination: 54.90 deg. Period: 718.00 min. Last launch from LC17A. Final Block IIR-M Global Positioning System satellite..

2009 September 25 - . 12:20 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

USA 208 - . Payload: STSS 1;STSS DEMO 1. Mass: 1,122 kg (2,473 lb). Nation: USA. Agency: Martin. Class: Military. Type: Anti-satellite system target. Spacecraft: STSS. USAF Sat Cat: 35937 . COSPAR: 2009-052A. Space Tracking and Surveillance System for missile launch and flight monitoring using infrared sensors..

USA 209 - . Payload: STSS 2;STSS DEMO 2. Mass: 1,122 kg (2,473 lb). Nation: USA. Agency: Martin. Class: Military. Type: Anti-satellite system target. Spacecraft: STSS. USAF Sat Cat: 35938 . COSPAR: 2009-052B. Space Tracking and Surveillance System for missile launch and flight monitoring using infrared sensors..

2009 October 8 - . 18:51 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

WorldView-2 - . Mass: 2,615 kg (5,765 lb). Nation: USA. Agency: Martin. Class: Surveillance. Type: Surveillance satellite. Spacecraft Bus: BCP-5000. Spacecraft: WorldView. USAF Sat Cat: 35946 . COSPAR: 2009-055A. Apogee: 769 km (477 mi). Perigee: 766 km (475 mi). Inclination: 98.50 deg. Period: 100.20 min. Commercial 0.5-meter-resolution, 8-band imaging satellite..

2009 December 14 - . 14:09 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7320-10C.

WISE - . Mass: 674 kg (1,485 lb). Nation: USA. Agency: Martin. Class: Astronomy. Type: Infrared astronomy satellite. Spacecraft: RS-300. USAF Sat Cat: 36119 . COSPAR: 2009-071A. Apogee: 532 km (330 mi). Perigee: 527 km (327 mi). Inclination: 97.50 deg. Period: 95.20 min.
Wide Field Infrared Explorer astronomy satellite, designed to conduct an all-sky survey at infrared frequencies of 3.4, 4.6, 12 and 22 microns, detecting objects 100 times fainter than the earlier IRAS and Akari satellites. Primary instrument is a 40 cm telescope cooled to 12 K by a cryostat filled with solid hydrogen. The survey was expected to detect tens of thousands of new asteroids, brown dwarf stars, and planets orbiting nearby stars.

2010 November 6 - . 02:20 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

Cosmo-SkyMed 4 - . Mass: 1,900 kg (4,100 lb). Nation: Italy. Class: Surveillance. Type: Civilian Radarsat. Spacecraft Bus: Prima. Spacecraft: Cosmo-SkyMed. USAF Sat Cat: 37216 . COSPAR: 2010-060A. Apogee: 623 km (387 mi). Perigee: 622 km (386 mi). Inclination: 97.90 deg. Period: 97.20 min. X-band radar satellite..

2011 June 10 - . 14:20 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7320-10C.

SAC-D/Aquarius - . Mass: 1,350 kg (2,970 lb). Nation: Argentina. Program: SAC. Class: Earth. Type: Climate satellite. Spacecraft: SAC-D. USAF Sat Cat: 37673 . COSPAR: 2011-024A. Apogee: 655 km (406 mi). Perigee: 653 km (405 mi). Inclination: 98.00 deg. Period: 97.80 min.
Argentinian 'Satelite de Aplicaciones Cientificas-D' satellite. Carried NASA Aquarius L-band radiometer/scatterometer map sea salinity; a Ka-band microwave radiometer; a an infrared scanner to measure sea surface temperature; a high sensitivity camera to study light sources at night; and an Italian experiment which measured atmospheric deflection of GPS signals to determine air temperature and humidity.

2011 September 10 - . 13:08 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. Launch Pad: SLC17B. LV Family: Thor. Launch Vehicle: Delta 7920H.

Grail A Ebb - . Mass: 202 kg (445 lb). Nation: USA. Class: Moon. Type: Lunar probe. Spacecraft: LM-300. Decay Date: 2012-12-17 . USAF Sat Cat: 37801 . COSPAR: 2011-046A.
NASA dual-spacecraft lunar gravity mapping mission. Grail A was deployed from the Delta upper stage at 14:28 GMT and Grail B at 14:37 GMT. The spacecraft reached the Sun-Earth L1 point 1.5 million km from Earth and then fell back towards the Moon. Lunar orbit insertion was at 01:00 GMt on 1 January 2012 for Grail A, and at 02:00 GMT on 2 January for Grail B. After completing their mission, the satellites were intentionally crashed onto the lunar surface at 75.62 deg N / 26.63 deg W on 17 December 2012 at 22:29 GMT.

Grail B Flow - . Mass: 202 kg (445 lb). Nation: USA. Class: Moon. Type: Lunar probe. Spacecraft: LM-300. Decay Date: 2012-12-17 . USAF Sat Cat: 37802 . COSPAR: 2011-046B.

2011 October 28 - . 09:48 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

NPP - . Mass: 1,976 kg (4,356 lb). Nation: USA. Class: Earth. Type: Weather satellite. Spacecraft: BCP-2000. USAF Sat Cat: 37849 . COSPAR: 2011-061A. Apogee: 823 km (511 mi). Perigee: 818 km (508 mi). Inclination: 98.70 deg. Period: 101.30 min.
NPP Preparatory Project weather satellite, using payloads from the cancelled National Polar Orbiting Environmental Satellite System. The NPP provided a stopgap between the last of the Advanced TIROS-N polar weather satellites and the first Joint Polar Satellite System satellite to be launched in a few years.

AubieSat-1 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 37854 . COSPAR: 2011-061E. Apogee: 817 km (507 mi). Perigee: 457 km (283 mi). Inclination: 101.70 deg. Period: 97.50 min. Auburn University, Alabama 1U cubesat. First CubeSat from Auburn University. Successful..

DICE-X - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Cubesat. USAF Sat Cat: 37851 . COSPAR: 2011-061B. Apogee: 816 km (507 mi). Perigee: 458 km (284 mi). Inclination: 101.70 deg. Period: 97.50 min. Utah State University 1.5U cubesat. Deployed 10-m span electric field antennae to study magnetosphere..

DICE-Y - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Cubesat. USAF Sat Cat: 37852 . COSPAR: 2011-061C. Apogee: 816 km (507 mi). Perigee: 458 km (284 mi). Inclination: 101.70 deg. Period: 97.50 min. Utah State University 1.5U cubesat. Deployed 10-m span electric field antennae to study magnetosphere..

Explorer-1 PRIME Flight Unit 2 - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Cubesat. Decay Date: 2011-11-29 . USAF Sat Cat: 37856 . COSPAR: 2011-061G. Apogee: 815 km (506 mi). Perigee: 458 km (284 mi). Inclination: 101.70 deg. Period: 97.50 min. Montana State University 1U cubesat. Carried one of Van Allen's original Geiger tubes..

M-Cubed - . Mass: 1.00 kg (2.20 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 37855 . COSPAR: 2011-061F. Apogee: 815 km (506 mi). Perigee: 457 km (283 mi). Inclination: 101.70 deg. Period: 97.40 min. University of Michigan 1U cubesat. Michigan Multipurpose Mission. Objective was to obtain a mid-resolution image of the earth covering at least 60% land mass and a maximum of 20% cloud coverage from a single CubeSat platform..

RAX-2 - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Cubesat. Decay Date: 2011-11-29 . USAF Sat Cat: 37853 . COSPAR: 2011-061D. Apogee: 817 km (507 mi). Perigee: 456 km (283 mi). Inclination: 101.70 deg. Period: 97.50 min. University of Michigan 3U cubesat. National Science Foundation funded Radio Aurora Explorer..

2014 July 2 - . 09:56 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7320-10C.

OCO 2 - . Mass: 407 kg (897 lb). Nation: USA. Spacecraft: Leostar-2. USAF Sat Cat: 40059 . COSPAR: 2014-035A. Apogee: 704 km (437 mi). Perigee: 701 km (435 mi). Inclination: 98.20 deg. Period: 98.83 min. Was to have provided space-based observation of atmospheric carbon dioxide..

2015 January 31 - . 14:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7320-10C.

SMAP - . Mass: 944 kg (2,081 lb). Nation: USA. Class: Earth. Type: Atmosphere satellite. Spacecraft: SMAP. USAF Sat Cat: 40376 . COSPAR: 2015-003A. Apogee: 683 km (424 mi). Perigee: 681 km (423 mi). Inclination: 98.12 deg. Period: 98.40 min.
The Soil Moisture Active Passive satellite, carried a 6-m L-band antenna for synthetic aperture radar and radiometry measurements to map microwave emissions from water molecules in the soil. Sun synchronous orbit; 0600 GMT local time of the descending node.

FIREBIRD IIA - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Science. Type: Space science. Spacecraft: Cubesat. USAF Sat Cat: 40377 . COSPAR: 2015-003B. Apogee: 643 km (399 mi). Perigee: 431 km (267 mi). Inclination: 99.10 deg. Period: 95.38 min. 1.5U cubesat by NSF/Montana State/U. New Hampshire space science satellite. Sun synchronous orbit; 0600 GMT local time of the descending node..

FIREBIRD IIB - . Mass: 2.00 kg (4.40 lb). Nation: USA. Class: Science. Type: Space science. Spacecraft: Cubesat. USAF Sat Cat: 40378 . COSPAR: 2015-003C. Apogee: 643 km (399 mi). Perigee: 431 km (267 mi). Inclination: 99.10 deg. Period: 95.38 min. 1.5U cubesat by NSF/Montana State/U. New Hampshire space science satellite. Sun synchronous orbit; 0600 GMT local time of the descending node..

GRIFEX - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 40379 . COSPAR: 2015-003D. Apogee: 648 km (402 mi). Perigee: 433 km (269 mi). Inclination: 99.10 deg. Period: 95.45 min. 3U cubesat by Michigan/JPL; technology satellite. Sun synchronous orbit; 0600 GMT local time of the descending node..

ExoCube CP10 - . Mass: 4.00 kg (8.80 lb). Nation: USA. Class: Earth. Type: Atmosphere satellite. Spacecraft: Cubesat. USAF Sat Cat: 40380 . COSPAR: 2015-003E. Apogee: 652 km (405 mi). Perigee: 434 km (269 mi). Inclination: 99.10 deg. Period: 95.51 min. 3U cubesat by California Polytechnic. Sun synchronous orbit; 0600 GMT local time of the descending node..

2017 November 18 - . 09:46 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7920-10C.

NOAA-20 - . Payload: JPSS-1; NOAA 20. Nation: USA. USAF Sat Cat: 43013 . COSPAR: 2017-073A. Apogee: 827 km (513 mi). Perigee: 826 km (513 mi). Inclination: 98.75 deg. Period: 101.44 min. See JPSS 1 → NOAA 20. ..

Buccaneer-RMM - . Nation: Australia. USAF Sat Cat: 43014 . COSPAR: 2017-073B. Apogee: 813 km (505 mi). Perigee: 459 km (285 mi). Inclination: 97.72 deg. Period: 97.43 min. See Buccaneer RMM. ..

MiRaTA - . Nation: USA. USAF Sat Cat: 43015 . COSPAR: 2017-073C. Apogee: 812 km (504 mi). Perigee: 455 km (282 mi). Inclination: 97.72 deg. Period: 97.38 min. See MiRaTA. ..

MakerSat-0 - . Nation: USA. USAF Sat Cat: 43016 . COSPAR: 2017-073D. Apogee: 814 km (505 mi). Perigee: 454 km (282 mi). Inclination: 97.72 deg. Period: 97.39 min. See MakerSat 0. ..

RadFxSat - . Payload: Fox-1B; AO-91. Nation: USA. USAF Sat Cat: 43017 . COSPAR: 2017-073E. Apogee: 815 km (506 mi). Perigee: 454 km (282 mi). Inclination: 97.72 deg. Period: 97.40 min. See RadFxSat (Fox 1B, AO 91, AMSAT-OSCAR 91). ..

EagleSat - . Nation: USA. USAF Sat Cat: 43018 . COSPAR: 2017-073F. Apogee: 813 km (505 mi). Perigee: 454 km (282 mi). Inclination: 97.72 deg. Period: 97.38 min. See EagleSat. ..

2018 September 12 - . 13:02 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2W. LV Family: Thor. Launch Vehicle: Delta 7420-10C.

ICESAT 2 - . Payload: ICESAT-2. Nation: USA. USAF Sat Cat: 43613 . COSPAR: 2018-070A. Apogee: 483 km (300 mi). Perigee: 479 km (297 mi). Inclination: 92.00 deg. Period: 94.22 min. See ICESAT 2. ..

ELFIN - . Nation: USA. USAF Sat Cat: 43614 . COSPAR: 2018-070B. Apogee: 469 km (291 mi). Perigee: 442 km (274 mi). Inclination: 93.04 deg. Period: 93.69 min. See ELFIN (ELFIN A). ..

ELFIN-STAR - . Nation: USA. USAF Sat Cat: 43615 . COSPAR: 2018-070C. Apogee: 469 km (291 mi). Perigee: 442 km (274 mi). Inclination: 93.04 deg. Period: 93.70 min. See ELFIN-STAR (ELFIN B). ..

CP7 - . Payload: DAVE; ELFIN B. Nation: USA. USAF Sat Cat: 43616 . COSPAR: 2018-070D. Apogee: 468 km (290 mi). Perigee: 441 km (274 mi). Inclination: 93.04 deg. Period: 93.68 min. See CP 7 (DAVE). ..

SurfSat - . Nation: USA. USAF Sat Cat: 43617 . COSPAR: 2018-070E. Apogee: 468 km (290 mi). Perigee: 441 km (274 mi). Inclination: 93.04 deg. Period: 93.68 min. See SurfSat. ..

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