Encyclopedia Astronautica
August 12


August 12 Chronology


1941 August 12 - . Launch Vehicle: JATO.
  • Ercoupe first flight. - . Nation: USA. Summary: An Ercoupe light aircraft, impelled by 12 powder rockets of 50 pounds thrust each, piloted by Lt. Homer A. Boushey, first flew on rocket power alone after an initial boost from a towing automobile..

1944 August 12 - . Launch Site: Peenemuende. Launch Complex: Peenemuende GWO. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 18200.
1951 August 12 - .
1952 August 12 - . Launch Site: White Sands. LV Family: Corporal. Launch Vehicle: Corporal. LV Configuration: Corporal 29R.
  • Test mission - . Nation: USA. Apogee: 30 km (18 mi).

1953 August 12 - . LV Family: R-5. Launch Vehicle: R-5M.
  • Test of 400 kiloton lightweight thermonuclear warhead - . Nation: USSR. Related Persons: Korolev. Summary: The explosion of the RD5-6 400 kiloton warhead at Semiplatinsk proved the design of a lightweight thermonuclear warhead. Korolev began work in 1953 to develop a re-entry vehicle for this warhead..

1954 August 12 - . Launch Site: Edwards. LV Family: Navaho. Launch Vehicle: Navaho X-10. LV Configuration: X-10 s/n 4 GM-19310.
  • Navaho X-10 flight 8 - . Nation: USA. Program: Navaho. Summary: Structural test flight, extreme dive and then pull up at Mach 1.3..

1954 August 12 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: R-5. Launch Vehicle: R-5.
  • Phase 3 state trials launch - . Nation: USSR. Agency: Korolev. Apogee: 300 km (180 mi).

1957 August 12 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC10. LV Family: Navaho. Launch Vehicle: Navaho G-26. LV Configuration: Navaho II SM-64 09.
  • Navaho G-26 Flight 5 - . Nation: USA. Agency: USAF. Apogee: 25 km (15 mi). After a 15 hour 18 minute countdown G-26 number four finally left the pad. The boost phase was completed successfully; but then a guidance system malfunction prevented the cruise stage from separating from the booster until an altitude of 25 km was reached. However the autopilot successfully overcome drastic pitch oscillations created by the lofted trajectory, and the ramjets were successfully ignited. The stage cruised at Mach 2.93 for 280 km. However then the vehicle began drifting off course. The ground pilot banked, but the fuselage screened the airflow to the left ramjet intake, resulting in that engine flaming out. The vehicle lost speed and altitude, and the right engine flamed out a minute later. The missile was ordered into a terminal dive, impacting 425 km downrange.

1957 August 12 - . 07:48 GMT - . Launch Site: Atlantic Ocean. Launch Pad: 64.7 N x 54.0 W. Launch Platform: LSD-29. LV Family: Rockoon. Launch Vehicle: Loki Rockoon. LV Configuration: Loki Rockoon II5.12F. FAILURE: Failure.
  • SUI 67 Aeronomy / aurora / chemical release mission - . Nation: USA. Agency: SUI. Apogee: 0 km ( mi). Summary: Launched at IGY Rockoon Launch Site 1, Atlantic Ocean LP12 - - Latitude: 64.68 N - Longitude: 53.95 W..

1957 August 12 - . 13:55 GMT - . Launch Site: Atlantic Ocean. Launch Pad: 63.1 N x 53.7 W. Launch Platform: LSD-29. LV Family: Rockoon. Launch Vehicle: Loki Rockoon. LV Configuration: Loki Rockoon II5.13F.
  • SUI 68 Aurora / fields mission - . Nation: USA. Agency: SUI. Apogee: 100 km (60 mi). Summary: Launched at IGY Rockoon Launch Site 1, Atlantic Ocean LP13 - - Latitude: 63.05 N - Longitude: 53.72 W..

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp. FAILURE: Failure.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Johnston Island. LV Family: Asp. Launch Vehicle: Ascamp.
  • Hardtack Aeronomy mission - . Nation: USA. Agency: Livermore. Apogee: 100 km (60 mi).

1958 August 12 - . Launch Site: Santa Barbara Channel DZ. Launch Pad: 34.2 N x 120.0 W. Launch Platform: F4D-1 747. LV Family: Project Pilot. Launch Vehicle: Project Pilot. LV Configuration: Project Pilot 2. FAILURE: Vehicle exploded at ignition.. Failed Stage: 1.
  • Pilot 2 - . Payload: Diagnostic Payload 2. Nation: USA. Agency: USN. Class: Technology. Type: Navigation technology satellite. Spacecraft: Pilot. Decay Date: 1958-08-12 . COSPAR: F580812A. Apogee: 12 km (7 mi).

1958 August 12 - . 09:27 GMT - . Launch Site: Johnston Island. Launch Complex: Johnston Island LC2. LV Family: Redstone. Launch Vehicle: Redstone. LV Configuration: Redstone CC-51. FAILURE: Guidance system malfunction at 70 seconds which did not preclude subsequent system operations and successful mission accomplishment..
  • Hardtack Orange Nuclear test - . Nation: USA. Agency: USA. Apogee: 41 km (25 mi). Orange was a rocket-launched test of the W-39 warhead. Purpose was to measure the effects of high altitude nuclear explosions in order to design warheads for Nike-Zeus anti-ballistic missile system. The Hardtack Configuration Redstone shot the 3.8 megaton warhead to an altitude of 43 km.

1959 August 12 - .
  • NASA's future manned space program - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM; CSM Parachute; CSM Source Selection. The STG New Projects Panel (proposed by H. Kurt Strass in June) held its first meeting to discuss NASA's future manned space program. Present were Strass, Chairman, Alan B. Kehlet, William S. Augerson, Jack Funk, and other STG members. Strass summarized the philosophy behind NASA's proposed objective of a manned lunar landing : maximum utilization of existing technology in a series of carefully chosen projects, each of which would provide a firm basis for the next step and be a significant advance in its own right. Additional Details: NASA's future manned space program.

1959 August 12 - . Launch Site: Vandenberg. LV Family: Terrier. Launch Vehicle: Terrier ASROC Cajun. LV Configuration: Terrier ASROC Cajun Terasca. FAILURE: Failure.
  • Ultraviolet Scanner test - . Nation: USA. Agency: USN. Apogee: 0 km ( mi).

1960 August 12 - . LV Family: DF-2; Kosmos 2; R-2. Launch Vehicle: DF-1.
  • Soviet/China break. - . Nation: China. Related Persons: Tsien. In the preceding months relations between the Soviet advisors and Chinese engineers had been strained by increasing Soviet secrecy. The Russians catch Chinese students at the Moscow Aviation Institute stealing restricted missile data. Finally Khrushchev declared the suspension of military assistance to China. All 1,343 Soviet specialists are withdrawn from the Fifth Academy in Beijing and return to Russia. They leave behind 343 uncompleted contracts. A total of 257 technical development projects were cancelled as a result.

1960 August 12 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LC-B. LV Family: Hopi. Launch Vehicle: Kiva/Hopi.
  • Aeronomy mission - . Nation: USA. Agency: AFCRL. Apogee: 300 km (180 mi).

1960 August 12 - . 09:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Thor Delta. LV Configuration: Thor Delta 270/D2.
  • 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: 47.3000 deg. Period: 117.30 min. Summary: 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 12 - . 13:00 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC11. LV Family: Atlas. Launch Vehicle: Atlas D. LV Configuration: Atlas D 66D.
  • Research and development launch - . Nation: USA. Agency: USAF. Apogee: 1,800 km (1,100 mi).

1960 August 12 - . 16:48 GMT - . Launch Site: Silver Lake DZ. Launch Pad: 35.3 N x 116.1 W. Launch Platform: NB-52 003. LV Family: X-15. Launch Vehicle: X-15. LV Configuration: X-15 1-10-19.
  • X-15A High Alt test - . Nation: USA. Agency: NASA; USAF. Apogee: 41 km (25 mi). Maximum Speed - 2851 kph. Maximum Altitude - 41605 m. Established a new altitude record for a manned vehicle of 136,500 feet. This topped Captain Kincheloe's record altitude of 126,200 feet attained on September 7, 1956, in the X-2 rocket research aircraft.

1960 August 12 - . 18:28 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC25A. LV Family: Polaris. Launch Vehicle: Polaris A1. LV Configuration: Polaris A1X-47.
  • Test mission - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1961 August 12 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 602. LV Family: Polaris. Launch Vehicle: Polaris A1. LV Configuration: Polaris A1E-34.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1961 August 12 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 602. LV Family: Polaris. Launch Vehicle: Polaris A1. LV Configuration: Polaris A1E-42.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1961 August 12 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 602. LV Family: Polaris. Launch Vehicle: Polaris A1. LV Configuration: Polaris A1E-35.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1961 August 12 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 602. LV Family: Polaris. Launch Vehicle: Polaris A1. LV Configuration: Polaris A1E-43.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1961 August 12 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 602. LV Family: Polaris. Launch Vehicle: Polaris A1. LV Configuration: Polaris A1E-36.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1961 August 12 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 602. LV Family: Polaris. Launch Vehicle: Polaris A1. LV Configuration: Polaris A1E-37.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1961 August 12 - . 10:57 GMT - . Launch Site: Wallops Island. LV Family: Aerobee. Launch Vehicle: Aerobee 150A. LV Configuration: Aerobee 150A NASA 04.42NP.
  • LeRC LH2 test Technology test - . Nation: USA. Agency: NASA. Apogee: 153 km (95 mi).

1962 August 12 - . 08:02 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Vostok 8K72K.
  • Vostok 4 - . Call Sign: Berkut (Golden Eagle ). Crew: Popovich. Backup Crew: Komarov; Volynov. Payload: Vostok 3KA s/n 6. Mass: 4,728 kg (10,423 lb). Nation: USSR. Related Persons: Nikolayev; Popovich; Komarov; Volynov. Agency: RVSN. Program: Vostok. Class: Manned. Type: Manned spacecraft. Flight: Vostok 4. Spacecraft: Vostok. Duration: 2.96 days. Decay Date: 1962-08-15 . USAF Sat Cat: 365 . COSPAR: 1962-A-Nu-1. Apogee: 211 km (131 mi). Perigee: 159 km (98 mi). Inclination: 65.0000 deg. Period: 88.20 min. Joint flight with Vostok 3. Acquisition of experimental data on the possibility of establishing a direct link between two space ships; coordination of astronauts' operations; study of the effects of identical spaceflight conditions on the human organism. The launch of Popovich proceeds exactly on schedule, the spacecraft launching with 0.5 seconds of the planned time, entering orbit just a few kilometers away from Nikolayev in Vostok 3. Popovich had problems with his life support system, resulting in the cabin temperature dropping to 10 degrees Centigrade and the humidity to 35%. The cosmonaut still managed to conduct experiments, including taking colour motion pictures of the terminator between night and day and the cabin interior.

    Despite the conditions, Popovich felt able to go for the full four days scheduled. But before the mission, Popovich had been briefed to tell ground control that he was 'observing thunderstorms' if he felt the motion sickness that had plagued Titov and needed to return on the next opportunity. Unfortunately he actually did report seeing thunderstorms over the Gulf of Mexico, and ground control took this as a request for an early return. He was ordered down a day early, landing within a few mintutes of Nikolayev. Only on the ground was it discovered that he was willing to go the full duration, and that ground control had thought he had given the code.


1964 August 12 - .
  • Voskhod State Commission - . Nation: USSR. Related Persons: Korolev; Volynov; Katys; Lazarev; Yegorov; Komarov; Feoktistov; Sorokin. Program: Voskhod. Flight: Voskhod 1. Spacecraft: Voskhod. The readiness of two crews is certified (the prime crew of Volynov, Katys, and Yegorov and backup crew of Komarov, Feoktistov, and Sorokin). Korolev presses for Feoktistov to be included in the prime crew, citing his unequalled technical knowledge of the spacecraft. Kamanin and the VVS doctors oppose this, citing his poor medical condition which makes him uncertifiable for flight. A very heated discussion ensues, with the final decision to continue training all seven cosmonauts, with the first candidates for flight being Volynov, Katys, and Yegorov, with Komarov, Lazarev, and Sorokin being reserve cosmonauts. The question of Feoktistov's flight certification will be taken up by a special panel of physicians.

1964 August 12 - . 00:43 GMT - . Launch Site: Kronogard. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.56DA.
  • K64-S-2 Air sampling Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 121 km (75 mi).

1964 August 12 - . 01:49 GMT - . Launch Site: Wallops Island. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun NASA 10.84GA.
  • Grenades Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 114 km (70 mi).

1964 August 12 - . 02:15 GMT - . Launch Site: Fort Churchill. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun NASA 10.105GA.
  • Grenades Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 126 km (78 mi).

1964 August 12 - . 18:12 GMT - . Launch Site: Hidden Hills DZ. Launch Pad: 36.1 N x 116.0 W. Launch Platform: NB-52 003. LV Family: X-15. Launch Vehicle: X-15. LV Configuration: X-15 3-32-53.
  • X-15A Heat tran/LF/BLN test - . Nation: USA. Agency: NASA; USAF. Apogee: 24 km (14 mi). Summary: Maximum Speed - 5688 kph. Maximum Altitude - 24750 m..

1965 August 12 - .
  • Six key checkpoints in development of Apollo hardware listed - . Nation: USA. Related Persons: Phillips, Samuel. Program: Apollo. Spacecraft: Apollo CSM. Samuel C. Phillips, Apollo Program Director, listed the six key checkpoints in the development of Apollo hardware:

    1. Preliminary Design Review (PDR)
    2. Critical Design Review (CDR)
    3. Flight Article Configuration Inspection (FACI)
    4. Certification of Flight Worthiness (COFR)
    5. Design Certification Review (DCR)
    6. Flight Readiness Review (FRR)
    Additional Details: Six key checkpoints in development of Apollo hardware listed.

1965 August 12 - . 17:15 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 CRL AE3.519.
  • Extreme ultraviolet Mon Solar extreme ultraviolet mission - . Nation: USA. Agency: USAF. Apogee: 241 km (149 mi).

1966 August 12 - .
  • M2 Flight 3 - . Crew: Thompson. Payload: M2-F2 flight 3. Nation: USA. Related Persons: Thompson. Program: NASA Lifting Body. Class: Manned. Type: Manned spaceplane. Spacecraft: M2-F2. Summary: Maximum Speed - 656 kph. Maximum Altitude - 13720 m. Flight Time - 278 sec..

1966 August 12 - . 18:25 GMT - . Launch Site: Delamar Dry Lake DZ. Launch Pad: 37.3 N x 114.9 W. Launch Platform: NB-52 003. LV Family: X-15. Launch Vehicle: X-15. LV Configuration: X-15 2-48-85.
  • X-15A-2 ST,Pitot,Base drag test - . Nation: USA. Agency: NASA; USAF. Apogee: 70 km (43 mi). Summary: Maximum Speed - 5586 kph. Maximum Altitude - 70440 m..

1967 August 12 - . 06:30 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NRL NC3.187.
  • Ion Composition Aeronomy / ionosphere mission - . Nation: USA. Agency: NRL. Apogee: 222 km (137 mi).

1968 August 12 - . LV Family: Saturn V. Launch Vehicle: Saturn V.
  • Apollo 8 lunar mission scheduled for December 20. - . Nation: USA. Related Persons: Low, George. Program: Apollo. Flight: Apollo 8. Spacecraft: Apollo LTA; Apollo CSM. On August 12 Kraft informed Low that December 20 was the day if they wanted to launch in daylight. With everyone agreeing to a daylight launch, the launch was planned for December 1 with a "built-in hold" until the 20th, which would have the effect of giving assurance of meeting the schedule. LTA (LM test article)-B was considered as a substitute; it had been through a dynamic test vehicle program, and all except Kotanchik agreed this would be a good substitute. Grumman suggested LTA-4 but Low decided on LTA-B.

1968 August 12 - . 07:00 GMT - . Launch Site: Natal. LV Family: Nike. Launch Vehicle: Nike Iroquois. LV Configuration: Nike Iroquois CRL AG07.275.
  • Meteorites Meteorites mission - . Nation: USA. Agency: USAF. Apogee: 153 km (95 mi).

1968 August 12 - . 08:38 GMT - . Launch Site: White Sands. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.336UA.
  • Pandora D Meteorites mission - . Nation: USA. Agency: NASA. Apogee: 155 km (96 mi).

1969 August 12 - .
  • Apollo LM-6 (Apollo 12) guidance computer removed and replaced - . Nation: USA. Program: Apollo. Flight: Apollo 12. Spacecraft: Apollo LM; LM Guidance. Summary: During lunar module checkout activities at KSC, the LM-6 (for Apollo 12) guidance computer was removed and replaced because of an unexpected restart during panel revalidation..

1969 August 12 - . 11:01 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36A. LV Family: Atlas. Launch Vehicle: Atlas Centaur SLV-3C. LV Configuration: SLV-3C Centaur AC-18 / Centaur D-1A 5402C.
  • ATS 5 - . Payload: ATS E. Mass: 821 kg (1,809 lb). Nation: USA. Agency: NASA Greenbelt. Program: ATS. Class: Technology. Type: Communications technology satellite. Spacecraft: ATS-5. Completed Operations Date: 1984-01-01 . USAF Sat Cat: 4068 . COSPAR: 1969-069A. Apogee: 36,024 km (22,384 mi). Perigee: 35,992 km (22,364 mi). Inclination: 14.5000 deg. Period: 1,447.40 min. Applications Technology Satellite; communications tests. Launch vehicle successfully put the payload into a geosynchronous transfer orbit. The spacecraft maneuvered into geostationary orbit at 108 degrees W. The purpose of this flight was to demonstrate North-South Stationkeeping of a geosynchronous satellite. ATS-5 was equipped with an ion engine package identical to that on ATS-4. Once in geosynchronous orbit the spacecraft could not be despun as planned, and thus the spacecraft gravity gradient stabilization could not be implemented. The spacecraft spin rate was about 76 revolutions per minute, and this caused an effective 4g acceleration on the cesium feed system. The high g-loading on the cesium feed system caused flooding of the discharge chamber, and normal operation of the thruster with ion beam extraction could not be performed. The IPS was instead be operated as a neutral plasma source, without high-voltage ion extraction, along with the wire neutralizer to examine spacecraft charging effects. The neutralizer was also operated by itself to provide electron injection for the spacecraft charging experiments. Positioned in geosynchronous orbit over the Americas at 105 deg W in 1969-1977; over the Americas at 70 deg W in 1977-1983. As of 1 September 2001 located at 15.48 deg E drifting at 2.807 deg W per day. As of 2007 Mar 10 located at 111.70E drifting at 2.819W degrees per day.

1970 August 12 - . 18:26 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 CRL A03.903-2.
  • Extreme ultraviolet Solar ultraviolet mission - . Nation: USA. Agency: USAF. Apogee: 222 km (137 mi).

1970 August 12 - . 18:52 GMT - . Launch Site: White Sands. LV Family: Aerobee. Launch Vehicle: Aerobee 170. LV Configuration: Aerobee 170 CRL A04.002-1.
  • Extreme ultraviolet Solar extreme ultraviolet mission - . Nation: USA. Agency: AFCRL. Apogee: 246 km (152 mi).

1971 August 12 - . 05:30 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A511L.
  • Cosmos 434 - . Payload: Lunar Craft T2K no. 3. Mass: 5,500 kg (12,100 lb). Nation: USSR. Agency: MOM. Program: Lunar L3. Class: Moon. Type: Manned lunar lander. Spacecraft: LK. Duration: 8,296.77 days. Decay Date: 1981-08-22 . USAF Sat Cat: 5407 . COSPAR: 1971-069A. Apogee: 1,253 km (778 mi). Perigee: 193 km (119 mi). Inclination: 51.6000 deg. Period: 99.30 min. Final LK moon lander test using the T2K version.
    Maneuver Summary:
    188km X 267km orbit to 190km X 1261km orbit. Delta V: 266 m/s
    188km X 1262km orbit to 180km X 11384km orbit. Delta V: 1333 m/s
    Total Delta V: 1599 m/s. Ten years later the spacecraft was due to re-enter over Australia soon after the Skylab scare. The Soviet Union told the people of Australia not to worry, it was only an experimental lunar cabin - the first inadvertent admission that their manned lunar project even existed!

1971 August 12 - . 15:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4W. LV Family: Titan. Launch Vehicle: Titan 24B. LV Configuration: Titan 24B 24B-1 (3B-32).
  • OPS 8607 - . Payload: KH-8 no. 32 / Agena D. Mass: 3,000 kg (6,600 lb). Nation: USA. Agency: NRO; USAF. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: KH-8. Decay Date: 1971-09-03 . USAF Sat Cat: 5409 . COSPAR: 1971-070A. Apogee: 424 km (263 mi). Perigee: 137 km (85 mi). Inclination: 111.0000 deg. Period: 90.10 min. Summary: KH-8 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1971 August 12 - . 21:14 GMT - . Launch Site: White Sands. LV Family: Aerobee. Launch Vehicle: Aerobee 170. LV Configuration: Aerobee 170 NASA 13.62DS.
  • NRL NE4.251 Solar mission - . Nation: USA. Agency: NASA. Apogee: 200 km (120 mi).

1972 August 12 - . 02:15 GMT - . Launch Site: Thumba. LV Family: Belier. Launch Vehicle: Centaure. LV Configuration: Centaure ISRO 5.14.
  • ISRO 5.14 Ionosphere mission - . Nation: India. Agency: ISRO. Apogee: 150 km (90 mi).

1972 August 12 - . 09:25 GMT - . Launch Site: Green River. LV Family: Athena RTV. Launch Vehicle: Athena H. LV Configuration: Athena H H004.
  • RVTO-3B-2 re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 200 km (120 mi).

1974 August 12 - . 06:25 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 672 - . Payload: Soyuz ASTP s/n 72-EPSA. Mass: 6,570 kg (14,480 lb). Nation: USSR. Agency: MOM. Program: ASTP. Class: Manned. Type: Manned spacecraft. Spacecraft: Soyuz 7K-TM. Duration: 5.94 days. Decay Date: 1974-08-18 . USAF Sat Cat: 7413 . COSPAR: 1974-064A. Apogee: 226 km (140 mi). Perigee: 222 km (137 mi). Inclination: 51.7000 deg. Period: 88.90 min. ASTP precursor. Recovered August 18, 1974 5:02 GMT. Soyuz ASTP test.
    Maneuver Summary:
    195km X 305km orbit to 195km X 221km orbit. Delta V: 24 m/s
    195km X 221km orbit to 223km X 223km orbit. Delta V: 8 m/s
    231km X 231km orbit to 231km X 231km orbit. Delta V: 1 m/s
    223km X 223km orbit to 231km X 231km orbit. Delta V: 4 m/s
    231km X 231km orbit to 227km X 237km orbit. Delta V: 2 m/s
    Total Delta V: 39 m/s.
    Officially: Investigation of the upper atmosphere and outer space.

1975 August 12 - . Launch Site: Baikonur. Launch Complex: Baikonur LC177. LV Family: MR-UR-100. Launch Vehicle: MR-UR-100.
  • State trials missile test - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 August 12 - . Launch Site: Baikonur. Launch Complex: Baikonur LC173. LV Family: MR-UR-100. Launch Vehicle: MR-UR-100.
  • State trials missile test - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 August 12 - . Launch Site: Baikonur. Launch Complex: Baikonur LC173. LV Family: MR-UR-100. Launch Vehicle: MR-UR-100.
  • Operational test launch - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 August 12 - . 13:30 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 848 - . Mass: 6,000 kg (13,200 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-2M. Duration: 13.00 days. Decay Date: 1976-08-25 . USAF Sat Cat: 9280 . COSPAR: 1976-082A. Apogee: 303 km (188 mi). Perigee: 206 km (128 mi). Inclination: 62.8000 deg. Period: 89.60 min. Summary: Area survey photo reconnaissance satellite; returned film capsule; separated science capsule..
  • Nauka Cosmos 848 - . Payload: Nauka. Nation: USSR. Agency: MOM. Spacecraft: Nauka. Decay Date: 1976-09-01 . USAF Sat Cat: 9374 . COSPAR: 1976-082D. Apogee: 280 km (170 mi). Perigee: 199 km (123 mi). Inclination: 62.8000 deg. Period: 89.29 min.

1976 August 12 - . 15:54 GMT - . Launch Site: Wallops Island. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk NASA 18.168UE.
  • NASA 18.1006UE Plasma mission - . Nation: USA. Agency: NASA. Apogee: 148 km (91 mi).

1977 August 12 - . Launch Site: Edwards. LV Family: Shuttle. Launch Vehicle: Shuttle.
  • Enterprise flight 4 - . Call Sign: Enterprise. Crew: Fullerton; Haise. Nation: USA. Related Persons: Fullerton; Haise. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft: Enterprise. Summary: Conduct first free flight, ALT, tail cone on, Edwards (5 minutes, 21 seconds), Enterprise (OV-101), lake bed Runway 17.

1977 August 12 - . 06:29 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36B. LV Family: Atlas. Launch Vehicle: Atlas Centaur SLV-3D. LV Configuration: SLV-3D Centaur AC-45 / Centaur D-1AR 5025.
  • HEAO 1 - . Payload: HEAO A. Mass: 2,720 kg (5,990 lb). Nation: USA. Agency: NASA Huntsville. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: HEAO. Decay Date: 1979-03-15 . USAF Sat Cat: 10217 . COSPAR: 1977-075A. Apogee: 447 km (277 mi). Perigee: 429 km (266 mi). Inclination: 22.7000 deg. Period: 93.40 min. Summary: High Energy Astronomical Observatory; surveyed sky in X-ray band. Spacecraft engaged in research and exploration of the upper atmosphere or outer space (US Cat B)..

1978 August 12 - . 15:12 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Delta. Launch Vehicle: Delta 2914. LV Configuration: Delta 2914 633/D144.
  • 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: 1.0000 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. Additional Details: ISEE 3.

1979 August 12 - .
  • Ferry flight, St. Louis to Tulsa - . Nation: USA. Program: STS. Class: Manned. Type: Manned spaceplane. Spacecraft: Enterprise. Summary: Ferry flight, shuttle carrier aircraft/Enterprise (OV-101), St. Louis to Tulsa (1 hour, 35 minutes).

1980 August 12 - . 11:50 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1205 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-6U. Duration: 14.00 days. Decay Date: 1980-08-26 . USAF Sat Cat: 11924 . COSPAR: 1980-068A. Apogee: 302 km (187 mi). Perigee: 195 km (121 mi). Inclination: 72.8000 deg. Period: 89.50 min. Summary: Photo surveillance; returned film capsule; maneuverable..

1981 August 12 - . 05:46 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/2. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 47198-324.
  • Cosmos 1295 - . Mass: 700 kg (1,540 lb). Nation: USSR. Agency: MO. Class: Navigation. Type: Navigation satellite. Spacecraft: Parus. USAF Sat Cat: 12681 . COSPAR: 1981-077A. Apogee: 1,009 km (626 mi). Perigee: 947 km (588 mi). Inclination: 82.9000 deg. Period: 104.70 min. Summary: Military navigation satellite. Replaced Cosmos 1181..

1982 August 12 - . 00:30 GMT - . Launch Site: Kiruna. LV Family: Hawk. Launch Vehicle: Nike Orion. LV Configuration: Nike Orion SSC S37 SOAP/2.
  • CAMP / SOAP-2 Aeronomy mission - . Nation: Sweden. Agency: SSC. Apogee: 135 km (83 mi).

1983 August 12 - . 07:40 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: MUSSON. Launch Vehicle: MMR-06.
  • Aeronomy mission - . Nation: USSR. Agency: GMS. Apogee: 56 km (34 mi).

1985 August 12 - . 15:09 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC16/2. LV Family: R-7. Launch Vehicle: Molniya 8K78M. LV Configuration: Molniya 8K78M-2BL.
  • Cosmos 1675 - . Payload: Oko #41. Mass: 1,250 kg (2,750 lb). Nation: USSR. Agency: MOM. Class: Military. Type: Early warning satellite. Spacecraft: Oko. USAF Sat Cat: 15952 . COSPAR: 1985-071A. Apogee: 36,967 km (22,970 mi). Perigee: 3,363 km (2,089 mi). Inclination: 67.4000 deg. Period: 717.30 min. Summary: Replaced Cosmos 1581. Covered Oko constellation plane 8 - 195 degree longitude of ascending node..

1986 August 12 - . 20:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: H-1. LV Configuration: H-1 H-15(F).
  • 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: 50.0000 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: 50.0000 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: 50.0000 deg. Period: 117.00 min. Summary: MABES (Jindai). Experiment on the levitation of the magnetic bearing flywheel under zero-g condition. .

1987 August 12 - . 16:30 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 79 km (49 mi).

1988 August 12 - . 12:53 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Molniya 8K78M. LV Configuration: Molniya 8K78M-ML.
  • Molniya 1-73 - . Payload: Molniya-1T. Mass: 1,800 kg (3,900 lb). Nation: USSR. Agency: MOM. Program: Molniya. Class: Communications. Type: Military communications satellite. Spacecraft: Molniya-1T. Decay Date: 1999-12-16 . USAF Sat Cat: 19377 . COSPAR: 1988-069A. Apogee: 38,629 km (24,002 mi). Perigee: 1,726 km (1,072 mi). Inclination: 64.8000 deg. Period: 717.80 min. Summary: Operation of the long-range telephone and telegraph radio communications system in the USSR; transmission of USSR Central Television programmes to stations in the Orbita network. .

1992 August 12 - . 05:44 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 65078-421.
  • Cosmos 2208 - . Mass: 900 kg (1,980 lb). Nation: Russia. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-2M. USAF Sat Cat: 22080 . COSPAR: 1992-053A. Apogee: 803 km (498 mi). Perigee: 785 km (487 mi). Inclination: 74.0000 deg. Period: 100.80 min. Summary: Still operating in 1995..

1993 August 12 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC39B. LV Family: Shuttle. Launch Vehicle: Shuttle.
  • Shuttle Discovery Pad Abort - . Nation: USA. Program: STS. Flight: STS-51. Spacecraft: Discovery. The countdown for Discovery's third launch attempt ended at the T-3 second mark when on-board computers detected the failure of one of four sensors in main engine #2 which monitor the flow of hydrogen fuel to the engine. All of Discovery's main engines were ordered replaced on the launch pad, delaying the Shuttle's fourth launch attempt until September 12, 1993.

1994 August 12 - . 00:53 GMT - . Launch Site: Andoya. LV Family: Hawk. Launch Vehicle: Nike Orion. LV Configuration: Nike Orion DLR A-NO-212.
  • Echo 94 F-101 CONE Ionosphere mission - . Nation: Germany. Agency: DLR. Apogee: 140 km (80 mi).

1996 August 12 - . 18:58 GMT - . Launch Site: White Sands. LV Family: Hawk. Launch Vehicle: Nike Orion. LV Configuration: Nike Orion NASA 31.114UP.
  • HOMER Aeronomy / education mission - . Nation: USA. Agency: NASA Greenbelt. Apogee: 100 km (60 mi).

1997 August 12 - . 12:10 GMT - . Launch Site: Wallops Island. LV Family: Loki. Launch Vehicle: Super Loki. LV Configuration: Super Loki Falling Sphere.
  • CRISTA Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 111 km (68 mi).

1997 August 12 - . 12:15 GMT - . Launch Site: Wallops Island. LV Family: Viper. Launch Vehicle: Viper 3A. LV Configuration: Viper 3A Falling Sphere.
  • CRISTA Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 124 km (77 mi).

1997 August 12 - . 12:26 GMT - . Launch Site: Wallops Island. LV Family: Loki. Launch Vehicle: Super Loki. LV Configuration: Super Loki Falling Sphere.
  • CRISTA Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 118 km (73 mi).

1997 August 12 - . 21:41 GMT - . Launch Site: Wallops Island. LV Family: Loki. Launch Vehicle: Super Loki. LV Configuration: Super Loki Falling Sphere.
  • CRISTA Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 112 km (69 mi).

1998 August 12 - . 11:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. LV Family: Titan. Launch Vehicle: Titan Centaur 401A. LV Configuration: Titan 401A/Centaur 4A-20/TC-9 (K-17). FAILURE: Due to guidance system loss of heading after power interrupt, booster pitched over 40 seconds after launch, and was destroyed by range safety.. Failed Stage: G.
  • Mercury ELINT - . Payload: Mercury ELINT 3. Nation: USA. Agency: NRO; NSA. Manufacturer: TRW. Class: Military. Type: Electronic intelligence satellite. Spacecraft: Mercury ELINT. COSPAR: F980812A. Summary: Third launch of Mercury ELINT satellite..

1999 August 12 - . 22:52 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 42P. LV Configuration: Ariane 42P-3 V118.
  • Telkom 1 - . Mass: 2,763 kg (6,091 lb). Nation: Indonesia. Agency: PT Telkom. Manufacturer: Lockheed. Program: Palapa. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 25880 . COSPAR: 1999-042A. Apogee: 35,796 km (22,242 mi). Perigee: 35,779 km (22,231 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. The launch vehicle delivered its H-10-3 third stage and the Telkom 1 payload into a 221 km x 35687 km x 7.0 degree geosynchronous transfer orbit 21 minutes after launch. Telkom 1 was owned by PT Telkomunikasi of Indonesia and was a successor to the Palapa series of satellites. Mass of Telkom 1 was 1700 kg in geosynchronous orbit after its on-board engine made the apogee burn. Stationed at 108 deg E. Positioned in geosynchronous orbit at 108 deg E in 1999. As of 3 September 2001 located at 107.98 deg E drifting at 0.011 deg W per day. As of 2007 Mar 11 located at 107.98E drifting at 0.014W degrees per day.

2001 August 12 - .
  • STS-105 Mission Status Report #04 - . Nation: USA. Related Persons: Barry; Culbertson; Dezhurov; Forrester; Helms; Horowitz; Sturckow; Tyurin; Voss. Program: ISS. Flight: ISS EO-2; ISS EO-3; STS-105. The crew of Discovery, trailing the International Space Station by less than 2,000 statute miles, was awakened at 5:10 a.m. Central time to the sounds of "The White Eagle," a traditional Russian folk song played for Expedition Three Pilot Vladimir Dezhurov. Dezhurov and his crewmates, Expedition Three Commander Frank Culbertson and Flight Engineer Mikhail Tyurin are just hours from reaching their new home aboard the International Space Station (ISS). Additional Details: STS-105 Mission Status Report #04.

2001 August 12 - .
  • Death of Robert Everett Stevenson at Princeville, Hawaii. Cancer. - . Nation: USA. Related Persons: Stevenson. Summary: American oceanographer payload specialist astronaut, 1984-1984..

2002 August 12 - . 13:48 GMT - . Launch Site: Thumba. LV Family: RH. Launch Vehicle: RH-200.
  • Middle Atmosphere Aeronomy mission - . Nation: India. Agency: ISRO. Apogee: 70 km (43 mi).

2003 August 12 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC47. LV Family: Loki. Launch Vehicle: Super Loki.
  • Shadow Education mission - . Nation: USA. Agency: FLASPACE. Apogee: 110 km (60 mi).

2003 August 12 - . 14:20 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 2399 - . Mass: 6,750 kg (14,880 lb). Nation: Russia. Agency: VKS. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Orlets-1. Decay Date: 2003-12-09 . USAF Sat Cat: 27856 . COSPAR: 2003-035A. Apogee: 289 km (179 mi). Perigee: 180 km (110 mi). Inclination: 64.9000 deg. Period: 89.20 min. Originally to have launched September 2002; June 2003. A Russian newspaper report (Kommersant, 13 August) stated that Cosmos 2399 was a Neman (Yantar-4KS1M) imaging satellite, which used data relay satellites to return CCD imagery rather than physically recovering film. However some Western observors, when Cosmos 2399 raised its perigee on August 14 to 205 km and lowered the apogee to 330 km, believed this was more like the standard operational orbit for an Orlets-1 Don 17F12 film-return capsule imaging satellite. This seemed confirmed when debris was tracked around the satellite later on, which was then said to be due to a failed film capsule recovery attempt. Destroyed in orbit on December 9 after completing its mission.

2003 August 12 - . 18:23 GMT - . Launch Site: White Sands. LV Family: Black Brant. Launch Vehicle: Black Brant 9. LV Configuration: Black Brant IX NASA 36.205UE.
  • LASP / CU-9 (SEE) Plasma mission - . Nation: USA. Agency: NASA Greenbelt. Apogee: 300 km (180 mi).

2005 August 12 - . 11:43 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC41. Launch Pad: SLC41. LV Family: Atlas V. Launch Vehicle: Atlas V 401. LV Configuration: Atlas V 401 AV-007.
  • Mars Reconnaissance Orbiter - . Mass: 2,180 kg (4,800 lb). Nation: USA. Agency: NASA; JPL. Manufacturer: Lockheed. Class: Mars. Type: Mars probe. Spacecraft: Mars Reconnaissance Orbiter. USAF Sat Cat: 28788 . COSPAR: 2005-029A. Summary: Transferred from Atlas 3B. Delayed from August 10 and 11, 2005..

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