Encyclopedia Astronautica
November 08


November 08 Chronology


1932 November 8 - .
1936 November 8 - .
1942 November 8 - . Launch Vehicle: EA 1941.
  • EA 1941 program suspended - . Nation: France. Related Persons: Barre. A third of the test material for the Algerian flight tests had been unloaded in Oran, and the team and the rest of the material were ready to embark at Marseilles. Then news comes of the Allied landings in North Africa. The flight tests were immediately called off, and the team hid all materials in Algeria and France. At the end of 1942, the Germans occupy Vichy France and all further work on the project is supended.

1942 November 8 - .
1944 November 8 - . Launch Site: Heidekraut. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 19509. FAILURE: Failed after launch.
  • V-2 Ma259 232 L6 - . Nation: Germany. Summary: Planned range 250 km. Failed - accuracy was 6.9 km to the left of the planned trajectory. Circular error 249.1 km from aim point..

1947 November 8 - .
  • Birth of Dr Margaret Rhea Seddon - . Nation: USA. Summary: American physician mission specialist astronaut. Flew on STS-51-D, STS-40, STS-58. Physician. Was married to astronaut Robert Lee (Hoot) Gibson..

1948 November 8 - .
  • Birth of Dale Allan Gardner - . Nation: USA. Summary: American engineer mission specialist astronaut. Flew on STS-8, STS-51-A..

1951 November 8 - . Launch Site: Wallops Island.
  • Helium gun catapult. - . Nation: USA. Summary: First successful launching of a research model propelled by the helium gun catapult, by Langley's PARD at Wallops Island..

1952 November 8 - .
  • Birth of Charles Edward 'Chuck' Jones - . Nation: USA. Summary: American engineer military spaceflight engineer astronaut, 1982-1987. Killed in 9-11 hijacking..

1952 November 8 - . Launch Site: Hammaguira. Launch Complex: Hammaguira Bechar. LV Family: Veronique. Launch Vehicle: Veronique. LV Configuration: Veronique N4. FAILURE: Failure.
  • Test mission - . Nation: France. Agency: LRBA. Apogee: 10 km (6 mi).

1954 November 8 - . Launch Site: White Sands. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 2813A.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1955 November 8 - . LV Family: Jupiter. Launch Vehicle: Jupiter.
  • Thor and Jupiter projects approved. - . Nation: USA. Summary: Secretary of Defense approved Jupiter and Thor IRBM programs, the first based on experience gained by Redstone Arsenal team from V-2 and Redstone, the latter on experience gained from Atlas program..

1957 November 8 - . LV Family: Redstone. Launch Vehicle: Jupiter C.
  • Von Braun ordered to launch satellite. - . Nation: USA. Related Persons: von Braun; McElroy. Program: Explorer. Secretary of Defense Neil McElroy directed the Army to proceed with the launching of the Explorer earth satellites. This order, in effect, resumed the Orbiter project that had been eliminated from the IGY satellite planning program on September 9, 1955. Von Braun was to modify two Jupiter-C missiles (modified Redstones) and attempt to place an artificial earth satellite in orbit by March 58.

1957 November 8 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC3. LV Family: X-17. Launch Vehicle: X-17. LV Configuration: X-17 3-204-4.
  • Re-entry Vehicle test - . Nation: USA. Agency: USN. Apogee: 100 km (60 mi).

1957 November 8 - . 14:57 GMT - . Launch Site: Holloman. Launch Complex: Holloman A. LV Family: Aerobee. Launch Vehicle: Aerobee. LV Configuration: Aerobee USAF-90. FAILURE: Failure.
  • Test / ionosphere mission - . Nation: USA. Agency: USAF. Apogee: 100 km (60 mi).

1957 November 8 - . 20:43 GMT - . Launch Site: Pacific Ocean. Launch Pad: 48.3 S x 173.9 E. Launch Platform: AGB-4. LV Family: Rockoon. Launch Vehicle: Loki Rockoon. LV Configuration: Loki Rockoon SUI 108.
  • II5.84F Aeronomy / Chemical release mission - . Nation: USA. Agency: SUI. Apogee: 110 km (60 mi).

1957 November 8 - . 23:15 GMT - . Launch Site: Pacific Ocean. Launch Pad: 48.0 S x 173.8 E. Launch Platform: AGB-4. LV Family: Rockoon. Launch Vehicle: Loki Rockoon. LV Configuration: Loki Rockoon SUI 109.
  • II5.85F Aeronomy / Chemical release mission - . Nation: USA. Agency: SUI. Apogee: 110 km (60 mi).

1958 November 8 - . 01:53 GMT - . Launch Site: Fort Churchill. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun CC6.01.
  • Infrared airglow Aeronomy mission - . Nation: Canada. Agency: CARDE. Apogee: 139 km (86 mi).

1958 November 8 - . 07:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Thor Able I. LV Configuration: Thor Able I 129. 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 . COSPAR: F581108A. Apogee: 1,550 km (960 mi). Summary: 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..

1959 November 8 - .
  • Design of the Mercury Control Center was completed. - . Nation: USA. Program: Mercury. Spacecraft: Mercury. Between this date and December 5, 1959, the tentative design and layout of the Mercury Control Center to be used to monitor the orbiting flight of the Mercury spacecraft were completed. The control center would have trend charts to indicate the astronaut's condition and world map displays to keep continuous track of the Mercury spacecraft.

1960 November 8 - .
  • Mercury Little Joe 5 (LJ-5) - . Nation: USA. Program: Mercury. Spacecraft: Mercury; Mercury Escape Tower. LJ-5, the first of the series with a McDonnell production spacecraft, was launched from Wallops Island to check the spacecraft in an abort simulating the most severe launch conditions. The launch was normal until 15.4 seconds after lift-off, at which time the escape rocket motor was prematurely ignited. The spacecraft did not detach from the launch vehicle until impact and was destroyed. Failure to attain mission objectives was attributed to several possible causes. One of these was failure of the spacecraft-to-adpater clamp-ring limit switches. Another possibility was failure of the escape tower clamp-ring limit switches. And the third was improper rigging of the limit switches in either of those locations so that vibration or deflection could have caused switch closure. Since the test objectives were not met, a repeat of the mission was planned.

1960 November 8 - . 13:18 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC18A. Launch Pad: LC18A. LV Family: Scout. Launch Vehicle: Blue Scout Jr. LV Configuration: Blue Scout Jr D-2. FAILURE: Failure.
  • HETS Magnetospheric mission - . Nation: USA. Agency: USAF. Apogee: 200 km (120 mi).

1960 November 8 - . 15:18 GMT - . Launch Site: Wallops Island. Launch Complex: Wallops Island LA1. LV Family: Little Joe. Launch Vehicle: Little Joe 1 2P. LV Configuration: Little Joe 1-2P LJ-5. FAILURE: At 15.4 seconds the escape rocket motor and tower jettison motor ignited prematurely..
  • Mercury LJ-5 - . Nation: USA. Agency: NASA. Program: Mercury. Spacecraft: Mercury. Apogee: 16 km (9 mi). Little Joe 5 with a Mercury production spacecraft was launched from Wallops Island to test the spacecraft in an abort simulating the most severe launch conditions. At 15.4 seconds after liftoff, the escape rocket motor and tower jettison motor ignited prematurely. Booster, capsule, and tower remained mated through ballistic trajectory until destroyed on impact.

1961 November 8 - . 09:00 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Pad: LA2 SL. LV Family: Skylark. Launch Vehicle: Skylark 2. LV Configuration: Skylark-2 SL35.
  • Ozone / Meteors / SpE Aeronomy / chemical / ionosphere mission - . Nation: Australia. Agency: WRE; RAE. Apogee: 152 km (94 mi).

1961 November 8 - . 16:10 GMT - . Launch Site: ETR Launch Area. Launch Platform: SSBN 608. LV Family: Polaris. Launch Vehicle: Polaris A2. LV Configuration: Polaris A2E-X2.
  • Test mission - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1962 November 8 - . Launch Site: White Sands. Launch Complex: White Sands LC38. LV Family: Nike Zeus. Launch Vehicle: Nike Zeus. LV Configuration: Nike Zeus-3.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 200 km (120 mi).

1963 November 8 - . LV Family: Saturn I. Launch Vehicle: Saturn IB.
  • Uprated H-1 engine for the first stage of the Saturn IB - . Nation: USA. Program: Apollo. MSFC directed Rocketdyne to develop an uprated H-1 engine to be used in the first stage of the Saturn IB. In August, Rocketdyne had proposed that the H-1 be uprated from 85,275 to 90,718 kilograms (188,000 to 200,000 pounds) of thrust. The uprated engine promised a 907-kilogram (2,000 pound) increase in the Saturn IB's orbital payload, yet required no major systems changes and only minor structural modifications.

1963 November 8 - .
  • Go-ahead to RCA to develop the Apollo LEM radar - . Nation: USA. Program: Apollo. Spacecraft: Apollo LM; LM Communications; LM Guidance. Grumman issued a go-ahead to RCA to develop the LEM radar. Negotiations on the $23.461 million cost- plus-fixed-fee contract were completed on December 10. Areas yet to be negotiated between the two companies were LEM communications, inflight test, ground support, and parts of the stabilization and control systems.

1964 November 8 - . 08:22 GMT - . Launch Site: Hammaguira. Launch Complex: Hammaguira Blandine. LV Family: Veronique. Launch Vehicle: Veronique. LV Configuration: Veronique AGI52.
  • Ultraviolet Spectrum / CU point Solar ultraviolet mission - . Nation: France. Agency: CNES. Apogee: 98 km (60 mi). Summary: FU111 UV Solar Astronomy / Ptr mission..

1965 November 8 - . LV Family: Titan. Launch Vehicle: Titan 2.
  • The Combined Systems Acceptance Test of Gemini launch vehicle (GLV) 8 was conducted at Martin-Baltimore. - . Nation: USA. Flight: Gemini 8. The vehicle acceptance team convened November 16 and completed its inspection November 19, deeming the vehicle excellent. GLV-8 was deerected December 13-14 and was formally accepted by the Air Force on December 23. Stage I was airlifted to Cape Kennedy on January 4, 1966, followed by stage II on January 6. Both stages were placed in storage.

1965 November 8 - . 05:05 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-1.
  • Test / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 228 km (141 mi).

1965 November 8 - . 19:26 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4E. LV Family: Atlas. Launch Vehicle: Atlas Agena D SLV-3. LV Configuration: SLV-3 Agena D 7113 / Agena D 7113.
  • KH 7-23 - . Payload: KH-7 no. 23 / OPS 8293. Mass: 2,000 kg (4,400 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-7. Decay Date: 1965-11-11 . USAF Sat Cat: 1727 . COSPAR: 1965-090A. Apogee: 352 km (218 mi). Perigee: 280 km (170 mi). Inclination: 93.9000 deg. Period: 90.80 min. Summary: Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .
  • OPS 6232/Agena D - . Payload: Agena Pickaback / OPS 6232. Mass: 60 kg (132 lb). Nation: USA. Agency: USAF. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: SSF. Decay Date: 1965-11-09 . USAF Sat Cat: 1728 . COSPAR: 1965-090B. Apogee: 284 km (176 mi). Perigee: 155 km (96 mi). Inclination: 93.9000 deg. Period: 88.90 min. Summary: Not identified as a subsatellite ferret by McDowell..

1966 November 8 - .
  • Launch of Gemini XII postponed. - . Nation: USA. Flight: Gemini 12. The scheduled launch of Gemini XII was postponed by a malfunctioning power supply in the launch vehicle secondary autopilot, discovered before the countdown for the November 9 launch began. The secondary autopilot package and the secondary stage I rate gyro package were replaced, and the mission was rescheduled for November 10. During tests of the replacement autopilot on November 9, another malfunction occurred, which was resolved by again replacing the secondary autopilot package. The launch was rescheduled for November 11.

1966 November 8 - .
  • Approved mission sequence for Apollo Applications missions 209 through 212. - . Nation: USA. Spacecraft: Orbital Workshop. In accordance with decisions made by Associate Administrator George E. Mueller, Saturn/Apollo Applications Deputy Director John H. Disher notified Robert F. Thompson, Robert C. Hock, and Leland F. Belew, Apollo Applications Program Managers at MSC, KSC, and MSFC, respectively, of the approved mission sequence for missions 209 through 212. SAA-209: manned block II CSM flight of 28-day duration, with the CSM fuel cells providing primary electrical power. SAA-210: launch of the unmanned airlock Orbital Workshop multiple docking adapter combination, with solar cells as the chief source of power. SAA-211: manned CSM flight of 56-day duration. SAA-212: unmanned lunar module-Apollo telescope mount flight. Disher said that mission planning directives were being expedited to implement this mission sequence.

1966 November 8 - . 17:32 GMT - . Launch Site: Wallops Island. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk NASA 18.04GE.
  • Fields Plasma mission - . Nation: USA. Agency: NASA. Apogee: 216 km (134 mi).

1966 November 8 - . 19:53 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC1W. LV Family: Delta. Launch Vehicle: Thorad Agena D SLV-2G. LV Configuration: Thorad SLV-2G Agena D 507 / Agena D SS-01B 1632.
  • KH-4A 1037 - . Payload: KH-4A s/n 1037 / Agena D 1632 / OPS 1866. Mass: 1,500 kg (3,300 lb). Nation: USA. Agency: NRO; CIA. Class: Surveillance. Type: Military surveillance satellite. 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: 100.0000 deg. Period: 89.20 min. Summary: KH-4A. Second pan geometry mission. Higher than normal base plus fog encountered on both main camera records..

1967 November 8 - .
  • Full scale Apollo CSM be tested to evaluate fire propagation in orbit and on the ground - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM; CSM ECS. The MSC Director of Engineering and Development pointed out that a fullscale CSM would soon be tested to evaluate the hazard of fire propagation both in orbit (cabin atmosphere of oxygen at pressure of 3.8 newtons per square centimeter - 5.5 pounds per square inch absolute) and on the pad (oxygen at 11.4 newtons per sq cm-16.5 psia). There was a reasonable probability that the CSM might qualify in the first but not the second case. In such event, it was proposed that the prelaunch cabin atmosphere be changed from 100-percent oxygen to a mixture of 60-percent oxygen and 40percent helium or to a mixture of 60-percent oxygen and 40-percent nitrogen. This proposal was made on the assumption that those mixtures at 11.4 newtons per sq cm would not offer more of a fire hazard than 100percent oxygen at 3.8 newtons. It was also assumed that these mixtures would be physiologically suitable after being bled down to orbital pressure without subsequent purging or being enriched with additional oxygen. Structures and Mechanics Division (SMD) was requested to make flammability tests to determine the relative merit of the two mixtures and to outline a minimum test program to provide confidence that the mixed gas atmosphere might be considered equivalent to oxygen at 3.8 newtons.

1968 November 8 - . 09:46 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Delta. Launch Vehicle: Delta E1. LV Configuration: Thor Delta E1 479/D60.
  • Pioneer 9 - . Payload: Pioneer D / TTS 2. Mass: 63 kg (138 lb). Nation: USA. Agency: NASA Ames. Program: Pioneer. Class: Astronomy. Type: Solar astronomy satellite. Spacecraft: Pioneer 6-7-8-9-E. USAF Sat Cat: 3533 . COSPAR: 1968-100A. Summary: 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: 32.9000 deg. Period: 98.00 min. Summary: 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). .

1969 November 8 - . Launch Site: Kourou. Launch Complex: Kourou ALFS. LV Family: Veronique. Launch Vehicle: Vesta. LV Configuration: Vesta 006.
  • FU-189 Star pt test - . Nation: France. Agency: CNES. Apogee: 204 km (126 mi).

1969 November 8 - . 01:52 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC5. LV Family: Scout. Launch Vehicle: Scout B. LV Configuration: Scout B S169C.
  • Azur - . Payload: GRS A. Mass: 71 kg (156 lb). Nation: Germany. Agency: DFVLR. Class: Earth. Type: Magnetosphere satellite. Spacecraft: AZUR. USAF Sat Cat: 4221 . COSPAR: 1969-097A. Apogee: 2,127 km (1,321 mi). Perigee: 373 km (231 mi). Inclination: 102.7000 deg. Period: 110.50 min. Summary: German Research Satellite A; examined Van Allen belts, solar particles, aurora. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B). .

1969 November 8 - . 07:30 GMT - . Launch Site: Wallops Island. LV Family: Black Brant. Launch Vehicle: Black Brant 5B. LV Configuration: Black Brant VB NRL NF9.207.
  • Infrared astronomy mission - . Nation: USA. Agency: NRL. Apogee: 189 km (117 mi).

1970 November 8 - . 07:50 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF09. Launch Pad: LF09?. LV Family: Minuteman. Launch Vehicle: Minuteman 1B.
  • FOT GT79B Follow-on Test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1971 November 8 - . 04:28 GMT - . Launch Site: Barking Sands. LV Family: Tomahawk Sandia. Launch Vehicle: Terrier Tomahawk. LV Configuration: Terrier Tomahawk SECEDE I R23.
  • DARDABASI-A Aeronomy / Fields mission - . Nation: USA. Agency: Sandia. Apogee: 198 km (123 mi).

1971 November 8 - . 09:54 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA2. Launch Vehicle: Cockatoo. LV Configuration: Cockatoo 1022.
  • Aeronomy mission - . Nation: Australia. Agency: WRE. Apogee: 100 km (60 mi).

1972 November 8 - . 08:30 GMT - . Launch Site: White Sands. LV Family: Aerobee. Launch Vehicle: Aerobee 170. LV Configuration: Aerobee 170 NASA 13.86GG.
  • Astronomy mission - . Nation: USA. Agency: NASA. Apogee: 200 km (120 mi).

1972 November 8 - . 22:56 GMT - . Launch Site: Andoya. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P41A.
  • Particles / substorm Aurora mission - . Nation: UK. Agency: SRC. Apogee: 140 km (80 mi).

1973 November 8 - . 16:06 GMT - . Launch Site: Wallops Island. Launch Vehicle: Rocketsonde.
  • Met Para - . Nation: USA. Agency: MRN. Apogee: 63 km (39 mi).

1974 November 8 - . 20:30 GMT - . Launch Site: Poker Flat. Launch Vehicle: Rocketsonde.
  • Met Para, Datasonde - . Nation: USA. Agency: MRN. Apogee: 60 km (37 mi).

1975 November 8 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 635. Launch Vehicle: Poseidon.
  • FOT-15? Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1975 November 8 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 635. Launch Vehicle: Poseidon.
  • FOT-15? Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1975 November 8 - . 05:20 GMT - . Launch Site: White Sands. LV Family: Aerobee. Launch Vehicle: Aerobee 170. LV Configuration: Aerobee 170 NASA 13.49UH.
  • X-ray astronomy mission - . Nation: USA. Agency: NASA. Apogee: 177 km (109 mi).

1976 November 8 - .
  • Buran specification approved. - . Nation: USSR. Spacecraft: Buran. Summary: Decree 'On approval of a tactical-technical requirement for Buran' was issued..

1976 November 8 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF26. Launch Pad: LF26?. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • FOT GT56GB Follow-on Test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1977 November 8 - . 22:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC29B. LV Family: Polaris. Launch Vehicle: Polaris A3. LV Configuration: Polaris A3TK-PB.
  • Chevaline warhead test launch - . Nation: UK. Agency: RN. Apogee: 1,000 km (600 mi).

1978 November 8 - . 21:29 GMT - . Launch Site: Barking Sands. Launch Vehicle: Rocketsonde. LV Configuration: AN/DMQ-9.
  • - . Nation: USA. Agency: MRN. Apogee: 89 km (55 mi).

1979 November 8 - . Launch Site: White Sands. Launch Complex: White Sands LC36. LV Family: Honest John. Launch Vehicle: Taurus Orion. LV Configuration: Taurus Orion NASA 33.08UL.
  • Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 200 km (120 mi).

1979 November 8 - . 22:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC29A. LV Family: Polaris. Launch Vehicle: Polaris A3. LV Configuration: Polaris A3TK P-6.
  • Chevaline warhead test launch - . Nation: UK. Agency: RN. Apogee: 1,000 km (600 mi).

1982 November 8 - .
  • Wethersfield Meteorite Fall (Fell Through Roof of A House) - . Nation: USA.

1983 November 8 - . Launch Site: Vandenberg.
  • Space Shuttle orbiter Discovery at Vandenberg AFB - . Nation: USA. Program: STS. Summary: Space Shuttle orbiter Discovery at Vandenberg AFB for a series of fit checks at the orbiter lifting frame..

1984 November 8 - . 12:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39A. LV Family: Shuttle. Launch Vehicle: Shuttle. LV Configuration: Space Shuttle STS-19/51-A.
  • STS-51-A - . Call Sign: Discovery. Crew: Allen; Fisher; Gardner; Hauck; Walker, Dave. Payload: Discovery F02 / PLT. Mass: 20,550 kg (45,300 lb). Nation: USA. Related Persons: Allen; Fisher; Gardner; Hauck; Walker, Dave. Agency: NASA Houston. Program: STS. Class: Manned. Type: Manned spaceplane. Flight: STS-51-A. Spacecraft: Discovery. Duration: 7.99 days. Decay Date: 1984-11-16 . USAF Sat Cat: 15382 . COSPAR: 1984-113A. Apogee: 297 km (184 mi). Perigee: 289 km (179 mi). Inclination: 28.4000 deg. Period: 90.40 min. Manned five crew. First retrieval of two satellites (PALAPA B-2 and WESTAR Vl) for return to earth. Deployed Anik D2, Leasat 2; recovered Westar 6, Palapa B2. Payloads: Telesat (Canada communications satellite)-H with Payload Assist Module (PAM)-D deploy-ment, Syncom IV-1 communications satellite deployment with its unique stage, retrieval of PALAPA B-2 and WESTAR VI communications satellites with PAM-D which failed to ignite on the STS-41-B mission. Manned maneuvering unit (MMU) used for retrieval. Diffusive Mixing of Organic Solutions (DMOS) experiment.
  • Syncom IV-1 - . Payload: Discovery F2 / Anik D2 / Syncom-4 1. Mass: 1,315 kg (2,899 lb). Nation: USA. Agency: HCI. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 381. Completed Operations Date: 1992-09-26 . USAF Sat Cat: 15384 . COSPAR: 1984-113C. Apogee: 36,403 km (22,619 mi). Perigee: 36,152 km (22,463 mi). Inclination: 7.6000 deg. Period: 1,461.20 min. Released from STS 51A 10 November 1984; 105 deg W; leased to U.S. government. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit at 15 deg W in 1984-1992 As of 3 September 2001 located at 170.37 deg W drifting at 6.220 deg W per day. As of 2007 Mar 10 located at 100.08W drifting at 6.233W degrees per day.
  • Anik D2 - . Payload: Anik D2 [PAM-D]. Mass: 1,100 kg (2,400 lb). Nation: Canada. Agency: Telesat. Program: Anik. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. Completed Operations Date: 1995-02-10 . USAF Sat Cat: 15383 . COSPAR: 1984-113B. Apogee: 36,271 km (22,537 mi). Perigee: 36,076 km (22,416 mi). Inclination: 6.7000 deg. Period: 1,455.90 min. Released 9 November 1984 from STS 51A; 82 deg W. Telecommunications. Longitude 111.5 deg W. Operating entity Telesat Canada. Transmitter power 8.9 watts at each frequency. Frequencies 3720 to 4180 MHz spaced by 20 MHz. Positioned in geosynchronous orbit at 111 deg W in 1984-1986; 110 deg W in 1986-1991; 82 deg W in 1991-1993; 20 deg E in 1993-1995 As of 28 August 2001 located at 178.69 deg W drifting at 4.912 deg W per day. As of 2007 Mar 10 located at 25.98W drifting at 4.913W degrees per day.

1985 November 8 - . 14:21 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: SHIR. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 87 km (54 mi).

1987 November 8 - . Launch Site: Natal. LV Family: Sonda. Launch Vehicle: Sonda 4. LV Configuration: Sonda 4 PT-03. FAILURE: Failure.
  • Test mission - . Nation: Brazil. Agency: IAE. Apogee: 130 km (80 mi).

1988 November 8 - . 14:11 GMT - . Launch Site: Zingst. Launch Vehicle: MMR-06.
  • MMR06-M Zingst launch 4 - . Nation: USSR. Agency: GMS. Apogee: 78 km (48 mi). Summary: Test launch. Earth impacted at 637 seconds. Reached 78.3 km. Probe crashed with no braking..

1989 November 8 - . 14:07 GMT - . Launch Site: Molodezhnaya. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 87 km (54 mi).

1991 November 8 - . 07:07 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4E. LV Family: Titan. Launch Vehicle: Titan 403A. LV Configuration: Titan 403A K-8 (45F-2).
  • USA 72 - . Payload: NOSS 10. Nation: USA. Agency: NRO; NRL. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: NOSS-2. USAF Sat Cat: 21775 . COSPAR: 1991-076A. Apogee: 1,321 km (820 mi). Perigee: 799 km (496 mi). Inclination: 63.4000 deg. Period: 106.40 min. Summary: Second launch by Titan 4 of new generation of NOSS naval reconnaissance satellites. However earlier NOSS weighed only 2,000 kg; Titan 4 booster has seven times this capacity. What else was launched?.
  • USA 77 - . Payload: NOSS-Subsat 10-3. Nation: USA. Agency: NRO; NRL. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: NOSS-2 subsatellite. USAF Sat Cat: 21809 . COSPAR: 1991-076E. Apogee: 1,270 km (789 mi). Perigee: 954 km (593 mi). Inclination: 63.4270 deg. Period: 107.44 min.
  • USA 74 - . Payload: NOSS-Subsat 10-1. Nation: USA. Agency: NRO; NRL. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: NOSS-2 subsatellite. USAF Sat Cat: 21799 . COSPAR: 1991-076C. Apogee: 1,270 km (789 mi). Perigee: 954 km (593 mi). Inclination: 63.4270 deg. Period: 107.44 min.
  • USA 76 - . Payload: NOSS-Subsat 10-2. Nation: USA. Agency: NRO; NRL. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: NOSS-2 subsatellite. USAF Sat Cat: 21808 . COSPAR: 1991-076D. Apogee: 1,270 km (789 mi). Perigee: 954 km (593 mi). Inclination: 63.4280 deg. Period: 107.44 min.

1992 November 8 - . LV Family: Shuttle. Launch Vehicle: Shuttle.
  • Columbia OMDP-1 - . Nation: USA. Program: STS. Spacecraft: Columbia. Shuttle Columbia begins its OMDP-1 Orbiter Maintenance Down Period at the Palmdale, returning to service in 1995 for the STS-73 mission. These are undertaken every 10 to 12 shuttle missions. Modifications made included a complete mid-life refurbishment, corrosion control on the wing leading edge spar, and implementation of 96 Master Change Requests.

1992 November 8 - . 10:25 GMT - . Launch Site: Kiruna. Launch Vehicle: Maxus. LV Configuration: Maxus MAXUS 1B.
  • Microgravity mission - . Nation: Germany. Agency: SSC; DLR. Apogee: 717 km (445 mi). Summary: Microgravity experiments. Relaunch of the Maxu 1 mission..

1997 November 8 - . 02:05 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. LV Family: Titan. Launch Vehicle: Titan Centaur 401A. LV Configuration: Titan 401A/Centaur 4A-17/TC-16 (45E-?).
  • USA 136 - . Payload: Trumpet 3. Mass: 5,200 kg (11,400 lb). Nation: USA. Agency: NRO; USAF. Manufacturer: Kent. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: Trumpet. USAF Sat Cat: 25034 . COSPAR: 1997-068A. Apogee: 39,059 km (24,270 mi). Perigee: 1,100 km (600 mi). Inclination: 63.6000 deg.

1999 November 8 - .
2000 November 8 - .
  • ISS Status Report: ISS 00-53 - . Nation: USA. Related Persons: Bloomfield; Garneau; Gidzenko; Jett; Noriega; Shepherd; Tanner. Program: ISS. Flight: ISS EO-1. The Expedition One crew today installed the final cables and sensors into the prime oxygen-generation system aboard the International Space Station and continued to set up laptop computers and communications gear as they neared the end of a full week aboard the outpost. Additional Details: ISS Status Report: ISS 00-53.

2002 November 8 - .
2004 November 8 - . 18:30 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC43/4. LV Family: R-7. Launch Vehicle: Soyuz ST.
  • Soyuz 2 flight test. - . Nation: Russia. Agency: KVR. First flight test of a modernized version of the Soyuz ST equipped with a digital control system. Suborbital launch; carried an obsolete Zenit-8 reconnaisance satellite as a mass model and impacted in the Pacific Ocean. Launch delayed from October 15 and 29, November 6.

2005 November 8 - . 14:07 GMT - . Launch Site: Kiritimati. Launch Pad: 0.0 N x 154.0 W. Launch Platform: ODYSSEY. LV Family: Zenit. Launch Vehicle: Zenit-3SL. LV Configuration: Zenit-3SL 23.
  • Inmarsat 4F-2 - . Payload: Inmarsat 4B; Eurostar 3000GM. Mass: 5,958 kg (13,135 lb). Nation: USA. Agency: Inmarsat. Program: Inmarsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Eurostar 3000. USAF Sat Cat: 28899 . COSPAR: 2005-044A. Apogee: 35,965 km (22,347 mi). Perigee: 35,902 km (22,308 mi). Inclination: 2.9000 deg. Period: 1,443.60 min. Summary: The satellite was fitted with a 10 meter diameter antenna for mobile communications. Payload moved from Ariane 5 EC-A. Launch delayed from September, November 4 and 5, 2005. As of 2007 Mar 11 located at 52.87W drifting at 0.010W degrees per day..

2006 November 8 - . 20:01 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC200/39. LV Family: Proton. Launch Vehicle: Proton/Briz M. LV Configuration: Proton-M/Briz-M 535-15.
  • Badr 4 ARABSAT 4B - . Mass: 3,280 kg (7,230 lb). Nation: Arab States. Agency: Arabsat. Manufacturer: EADS Astrium. Class: Communications. Type: Civilian communications satellite. Spacecraft: Eurostar 2000. USAF Sat Cat: 29526 . COSPAR: 2006-051A. Apogee: 35,807 km (22,249 mi). Perigee: 35,764 km (22,222 mi). Inclination: 0.1000 deg. Period: 1,436.00 min. Summary: Dry mass 1487 kg. The satellite provided Ku-band communications services for Arab League countries. As of 2007 Mar 10 located at 26.06E drifting at 0.011E degrees per day..

2008 November 8 - .
  • Death of John Sumter Bull at South Lake Tahoe, California - . Nation: USA. Related Persons: Bull. Summary: American test pilot astronaut, 1966-1968..

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