Encyclopedia Astronautica
September 14


September 14 Chronology


1910 September 14 - .
  • Birth of Bernard A Schriever - . Nation: Germany; USA. Summary: Key German-American military manager of development of the Thor, Atlas, Titan, and Minuteman ballistic missiles..

1919 September 14 - .
  • Birth of Vladislav Nikolayevich Bogomolov - . Nation: Russia. Summary: Russian chief designer. Chief Designer 1971-1985 of Isayev rocket engine design bureau. Succeeded Isayev after his death..

1934 September 14 - . LV Family: Goddard. Launch Vehicle: Goddard A.
  • Goddard obtained funding allowing liquid rocket flight tests to be resumed in Roswell, New Mexico. - . Nation: USA. Related Persons: Goddard. This funding would continue through 1941. The first test series was designated the A Series (A1-A14). The A series rockets used simple pressure feed, gyroscopic control by means of vanes, and parachute. The rockets in this series averaged in length from 13 ft 6 in. to 15 ft 3 1/4 in.; their weight empty varied from 58 lb to 85 lb.

1944 September 14 - . Launch Site: Heidekraut. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 18745. FAILURE: Air-burst of rocket but explosion of warhead at ground level..
  • V-2 Ma160 132 A5 - . Nation: Germany. Summary: Planned range 225 km. Air-burst of rocket but explosion of warhead at ground level 7.1 km to the left of the planned trajectory. Circular error 10.0 km from aim point..

1948 September 14 - . Launch Site: White Sands. Launch Complex: White Sands LC33. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 23R.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1949 September 14 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: R-1. Launch Vehicle: R-1. LV Configuration: R-1 II-4.
  • Test mission - . Nation: USSR. Agency: Korolev. Apogee: 100 km (60 mi).

1950 September 14 - .
1950 September 14 - . Launch Site: White Sands. Launch Complex: White Sands LC33. LV Family: Hermes. Launch Vehicle: Hermes A-1. LV Configuration: Hermes A-1 2. FAILURE: Failure.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 0 km ( mi).

1951 September 14 - .
  • Final flight of the 346-3 rocketplane. - . Nation: USSR. Spacecraft: 346. Summary: The aircraft went out of control and Ziese bailed out of the aircraft. The destruction of this rocketplane resulted in further tests being abandoned..

1953 September 14 - . Launch Site: White Sands. LV Family: Corporal. Launch Vehicle: Corporal. LV Configuration: Corporal 1352R.
  • Test mission - . Nation: USA. Apogee: 30 km (18 mi).

1954 September 14 - .
  • Birth of Itzhak Mayo - . Nation: Israel. Summary: Jewish-Israeli pilot payload specialist astronaut, 1997-2000..

1954 September 14 - . Launch Site: White Sands. LV Family: Nike. Launch Vehicle: Nike. LV Configuration: Nike 2803T.
  • Test mission - . Nation: USA. Agency: USA. Apogee: 10 km (6 mi).

1955 September 14 - . 13:30 GMT - . Launch Site: Holloman. Launch Complex: Holloman A. LV Family: Aerobee. Launch Vehicle: Aerobee AJ10-27. LV Configuration: Aerobee AJ10-27 USAF 58.
  • UM wind vanes Test / aeronomy mission - . Nation: USA. Agency: USAF. Apogee: 95 km (59 mi). Summary: Rocket aerodynamics test. Launched at 0630 local time. Reached 95 km..

1956 September 14 - .
  • X-1E Flight 11 - . Crew: Walker, Joseph. Payload: X-1E flight 11. Nation: USA. Related Persons: Walker, Joseph. Class: Manned. Type: Manned rocketplane. Spacecraft: X-1E. Summary: NACA flight 10. Mach 2.1 at 18910 m. Stabilizer, rudder, and aileron pulses..

1957 September 14 - . 03:00 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Agency: MVS. Apogee: 85 km (52 mi).

1958 September 14 - . Launch Site: Cuxhaven. Launch Vehicle: Mohr Rocket.
  • Mohr Rocket reaches 50 km altitude - . Nation: Germany. Three launches were made from Arensch, including two successful launches of the prototype of the large meteorological rocket developed by Ernst Mohr of Wuppertall. The launches were witnessed by Vice-President Ross. The redesigned Mohr rockets were 2.5 m long, 30 cm in diameter, had a total mass of 80 kg and produced 7.8 tonnes thrust. Cutoff velocity was 1200 m/s at 1200 m altitude. The payload dart then separated and coasted up to 50 km altitude. It was later planned to install meteorological instruments on these rockets.

1958 September 14 - .
1958 September 14 - . 05:24 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC14. LV Family: Atlas. Launch Vehicle: Atlas B. LV Configuration: Atlas B 8B.
  • Research and development / AFSWC-2 test - . Nation: USA. Agency: USAF. Apogee: 900 km (550 mi).

1959 September 14 - . 17:27 GMT - . Launch Site: Fort Churchill. LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.07GI.
  • Ionosphere mission - . Nation: USA. Agency: NASA. Apogee: 218 km (135 mi).

1961 September 14 - . 04:45 GMT - . Launch Site: Kola Peninsula Launch Area. Launch Pad: 70.0 N x 40.0 E. Launch Platform: ZULUV?. Launch Vehicle: R-13.
  • Nuclear test - . Nation: USSR. Agency: RVSN. Apogee: 150 km (90 mi).

1962 September 14 - . Launch Site: ETR Launch Area. Launch Platform: EAG-154. LV Family: Polaris. Launch Vehicle: Polaris A1. LV Configuration: Polaris A1T-6.
  • Test mission - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1963 September 14 - . LV Family: Titan. Launch Vehicle: Titan 2.
  • Gemini Project Office reported a delay of about three weeks in the battery qualification program. - . Nation: USA. McDonnell had sent a team to investigate the problem of high porosity welds in titanium battery cases. Another problem had turned up with the batteries in prequalification vibration test. The batteries vibrated excessively, although they did not fail electrically; the vibration's amplification factor was apparently low enough to be remedied by potting.

1964 September 14 - . LV Family: N1; Proton; R-7; UR-700.
  • Voskhod abort system - . Nation: USSR. Related Persons: Korolev; Krylov; Feoktistov; Komarov; Volynov; Lazarev; Yegorov. Program: Voskhod; Lunar L1; Lunar L3. Flight: Voskhod 1. Spacecraft: Voskhod; LK-1. Kamanin reviews the Voskhod abort system with Korolev. Up to T+27 seconds, there is no possibility of saving the crew in the event of a booster failure; from T+27 seconds to T+44 seconds, escape would be difficult, but is possible; and from T+44 seconds to T+501 seconds abort should be possible, with the capsule landing on Soviet territory. Afterwards, Korolev speaks with Kamanin secretly and privately. Korolev reveals that he has discussed a greater VVS role in space with Marshal Krylov, but that Krylov is adamantly opposed to the VVS assuming such a mission. Korolev is seeking a resolution from the Communist Party that will authorise him to develop a manned lunar flyby and landing system using his N1 booster. He believes that Chelomei's UR-500 booster will not have sufficient payload to mount a manned flyby - a docking in low earth orbit will be required. But Chelomei has rejected the use of docking, and is even designing his UR-700 to allow a lunar landing without the use of docking.

    Finally Korolev gets to the purpose of the secret meeting. He wants Feoktistov to be aboard Voskhod 1, despite the opinion of Kamanin and the physicians. Kamanin reiterates that the most qualified crew would be Komarov, Volynov, and Lazarev; and if he gives in on Feoktistov, then Komarov, Feoktistov, Lazarev. But Korolev is opposed to Lazarev, and insists that the crew should be Komarov, Feoktistov, and Yegorov. From Kamanin's point of view this is flying a space mission with two invalids aboard. Lazarev is a qualified and fit flight surgeon, a qualified pilot as well as a physician with 15 years of research experience in aviation medicine. Korolev is adamant that the two passengers should be civilian, not military. No agreement is possible.


1964 September 14 - . 22:53 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC3W. LV Family: Delta. Launch Vehicle: Thor Agena D SLV-2A/D. LV Configuration: Thor SLV-2A Agena D 405 / Agena D 1178.
  • KH-4A 1010 - . Payload: KH-4A s/n 1010 / Agena D 1178 / OPS 3497. Mass: 1,330 kg (2,930 lb). Nation: USA. Agency: NRO; CIA. Class: Surveillance. Type: Military surveillance satellite. 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: 84.9000 deg. Period: 90.90 min. Summary: KH-4A. Small out of focus areas on both cameras at random times throughout the mission..

1965 September 14 - .
  • Perkin-Elmer and Chrysler to study lasers and large telescopes in future extended Apollo flights. - . Nation: USA. Spacecraft: Apollo X. NASA selected the Perkin-Elmer and Chrysler corporations to study feasibility of including optical-technology experiments, particularly lasers and large telescopes, in future extended Apollo flights. NASA was also interested in optical communication in deep space, the effects of space environment on optical systems, and related experiments. The program would be directed by MSFC.

1965 September 14 - . 05:45 GMT - . Launch Site: Green River. Launch Complex: Green River Pad 1. LV Family: Athena RTV. Launch Vehicle: Athena RTV. LV Configuration: Athena B004.
  • USN B004 re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 200 km (120 mi).

1965 September 14 - . 07:45 GMT - . Launch Site: Green River. Launch Complex: Green River Pad 3. LV Family: Athena RTV. Launch Vehicle: Athena RTV. LV Configuration: Athena D033.
  • USAF D033 re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 200 km (120 mi).

1965 September 14 - . 18:01 GMT - . Launch Site: Delamar Dry Lake DZ. Launch Pad: 37.3 N x 114.9 W. Launch Platform: NB-52 008. LV Family: X-15. Launch Vehicle: X-15. LV Configuration: X-15 3-48-72.
  • X-15A N.Radiom,BLN Test/Aeronomy mission? - . Nation: USA. Agency: NASA; USAF. Apogee: 72 km (44 mi). Summary: Maximum Speed - 5662 kph. Maximum Altitude - 72847 m..

1966 September 14 - . LV Family: N1. Launch Vehicle: N1.
  • N1 plans approved. - . Nation: USSR. Spacecraft: LK; Soyuz 7K-LOK. Summary: Academy of Sciences Decree 'On course of work on the N1-L3' was issued..

1966 September 14 - . 01:35 GMT - . Launch Site: Fort Churchill. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.278CA.
  • Ionosphere / TMA Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 157 km (97 mi).

1966 September 14 - . 04:23 GMT - . Launch Site: Fort Churchill. LV Family: Apache. Launch Vehicle: Nike Apache. LV Configuration: Nike Apache NASA 14.279CA.
  • Ionosphere / TMA Aeronomy mission - . Nation: USA. Agency: NASA. Apogee: 186 km (115 mi).

1966 September 14 - . 12:49 GMT - .
  • EVA Gemini 11-3 - . Crew: Gordon. EVA Type: Stand-Up External Vehicular Activity. EVA Duration: 0.0903 days. Nation: USA. Related Persons: Gordon. Program: Gemini. Class: Manned. Type: Manned spacecraft. Flight: Gemini 11. Spacecraft: Gemini. Summary: Photographed earth and stars..

1966 September 14 - . 20:01 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 3-55-82.
  • X-15A MuMet/Solar spec Technology/Meteor/Solar mission - . Nation: USA. Agency: NASA; USAF. Apogee: 77 km (47 mi). Summary: Maximum Speed - 5770 kph. Maximum Altitude - 22980 m. JPL spectrometer measured solar flux; radiometer characterized exhaust plume in UV for reconnsat sensors; collected micrometeorites..

1967 September 14 - . Launch Site: Green River. Launch Complex: Green River Pad 1. LV Family: Athena RTV. Launch Vehicle: Athena RTV. LV Configuration: Athena D056.
  • USAF D056 re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 200 km (120 mi).

1968 September 14 - . 06:50 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 240 - . Payload: Zenit-2 11F61 s/n 66. Mass: 4,720 kg (10,400 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-2. Duration: 7.00 days. Decay Date: 1968-09-21 . USAF Sat Cat: 3388 . COSPAR: 1968-075A. Apogee: 283 km (175 mi). Perigee: 203 km (126 mi). Inclination: 51.8000 deg. Period: 89.30 min. Summary: Area survey photo reconnaissance satellite..

1968 September 14 - . 21:42 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/23. LV Family: Proton. Launch Vehicle: Proton-K/D. LV Configuration: Proton-K/D 234-01.
  • Zond 5 - . Payload: Soyuz 7K-L1 s/n 9L. Mass: 5,390 kg (11,880 lb). Nation: USSR. Agency: MOM. Program: Lunar L1. Class: Manned. Type: Manned spacecraft. Spacecraft: Soyuz 7K-L1 . Duration: 5.76 days. Decay Date: 1968-09-21 . USAF Sat Cat: 3394 . COSPAR: 1968-076A. Apogee: 385,000 km (239,000 mi). Perigee: 200 km (120 mi). Inclination: 51.5000 deg. Period: 14,722.06 min. First successful circumlunar flight with recovery. Test flight of manned spacecraft; launched from an earth parking orbit to make a lunar flyby and return to earth. On September 18, 1968, the spacecraft flew around the moon at an altitude of 1950 km. High quality photographs of the earth were taken at a distance of 90,000 km. A biological payload of turtles, wine flies, meal worms, plants, seeds, bacteria, and other living matter was included in the flight. Before re-entry the gyroscopic platform went off line due to ground operator failure. However this time the self destruct command was not given. After a ballistic 20G re-entry the capsule splashed down in the Indian Ocean at 32:63 S, 65:55 E on September 21, 1968 16:08 GMT. Soviet naval vessels were 100 km from the landing location and recovered the spacecraft the next day, shipping it via Bombay back to Soviet Union. Additional Details: Zond 5.

1970 September 14 - . 23:30 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF25. LV Family: Minuteman. Launch Vehicle: Minuteman 2.
  • OT GT67F operational test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1971 September 14 - . 04:20 GMT - . Launch Site: Kourou. Launch Complex: Kourou ALFS. LV Family: Stromboli. Launch Vehicle: Dauphin. LV Configuration: Dauphin DA005.
  • PHARE (FU-196) Aeronomy mission - . Nation: France. Agency: CNES. Apogee: 103 km (64 mi).

1971 September 14 - . 13:00 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 438 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4MK. Duration: 13.00 days. Decay Date: 1971-09-27 . USAF Sat Cat: 5475 . COSPAR: 1971-077A. Apogee: 279 km (173 mi). Perigee: 205 km (127 mi). Inclination: 65.4000 deg. Period: 89.30 min. Summary: High resolution photo reconnaissance satellite; returned film capsule; maneuverable..

1971 September 14 - . 19:10 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: MR-12. Launch Vehicle: MR-12.
  • Aeronomy mission - . Nation: USSR. Apogee: 165 km (102 mi).

1971 September 14 - . 22:40 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: MR-12. Launch Vehicle: MR-12.
  • Aeronomy mission - . Nation: USSR. Apogee: 165 km (102 mi).

1972 September 14 - . 22:00 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 88 km (54 mi).

1973 September 14 - . 00:31 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/2. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 53714-106.
  • Cosmos 586 - . Mass: 550 kg (1,210 lb). Nation: USSR. Agency: MO. Class: Navigation. Type: Navigation satellite. Spacecraft: Tsiklon. USAF Sat Cat: 6828 . COSPAR: 1973-065A. Apogee: 1,003 km (623 mi). Perigee: 961 km (597 mi). Inclination: 82.9000 deg. Period: 104.70 min. Summary: Military navigation satellite..

1974 September 14 - .
  • Charles Kowal's Discovery of Jupiter Moon Leda - . Nation: USA.

1974 September 14 - . 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).

1976 September 14 - . 21:06 GMT - . Launch Site: Kheysa. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 90 km (55 mi).

1977 September 14 - . 00:15 GMT - . Launch Site: Jiuquan. Launch Complex: Jiuquan LA2B. LV Family: CZ. Launch Vehicle: FB-1. LV Configuration: Feng Bao 1 701(II)-01.
  • DDDS test - . Nation: China. Agency: PRC. Apogee: 200 km (120 mi).

1977 September 14 - . 07:10 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF09. Launch Pad: LF09?. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • OT GT35GM operational test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1977 September 14 - . 12:22 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-13.
  • Ultraviolet astronomy / extreme ultraviolet astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 204 km (126 mi).

1978 September 14 - . 02:25 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/24. LV Family: Proton. Launch Vehicle: Proton-K/D-1. LV Configuration: Proton-K/D-1 296-02.
  • Venera 12 - . Payload: 4V-1 s/n 361. Mass: 4,715 kg (10,394 lb). Nation: USSR. Agency: MOM. Program: Venera. Class: Venus. Type: Venus probe. Spacecraft: Venera 4V-1. USAF Sat Cat: 11025 . COSPAR: 1978-086A. Venera 12 was part of a two-spacecraft mission to study Venus and the interplanetary medium. Each of the two spacecraft, Venera 11 and Venera 12, consisted of a flight platform and a lander probe. Identical instruments were carried on both spacecraft. Venera 12 was launched into a 177 x 205 km, 51.5 degree inclination Earth orbit from which it was propelled into a 3.5 month Venus transfer orbit which involved two mid-course corrections, on 21 September and 14 December. After ejection of the lander probe on 19 December, two days before encounter, the flight platform continued on past Venus in a heliocentric orbit. Near encounter with Venus occurred on December 21, 1978, at approximately 34,000 km altitude. The flight platform acted as a data relay for the descent craft for 110 minutes until it flew out of range and returned to its own measurements on interplanetary space. The Venera 12 descent craft entered the Venus atmosphere at 11.2 km/sec two days after separation from the flight bus. During the descent, it employed aerodynamic braking followed by parachute braking and ending with atmospheric braking. It made a soft landing on the surface at 06:30 Moscow time on 21 December after a descent time of approximately 1 hour. The touchdown speed was 7-8 m/s.

    Both Venera 11 and 12 landers failed to return colour television views of the surface and perform soil analysis experiments. All of the camera protective covers failed to eject after landing (the cause was not established) The soil drilling experiment was apparently damaged by a leak in the soil collection device, the interior of which was exposed to the high Venusian atmospheric pressure. The leak had probably formed during the descent phase because the lander was less aerodynamically stable than had been thought. Therefore the landing gear of the following two landers (Venera-13/14) were equipped with tooth-shaped stabilisers.

    Results reported included evidence of lightning and thunder, a high Ar36/Ar40 ratio, and the discovery of carbon monoxide at low altitudes.

    The Venera-12 flyby bus continued in solar orbit and successfully used its Soviet-French ultraviolet spectrometer to study Comet Bradfield on 13 February 1980 (one year and two months after its Venus encounter). At that time the spacecraft was 190,373,790 km from Earth.


1979 September 14 - . Launch Site: Baikonur. LV Family: MR-UR-100. Launch Vehicle: MR-UR-100U 15A16.
  • SLI? - . Nation: USSR. Agency: RVSN. Apogee: 1,000 km (600 mi).

1979 September 14 - . 15:30 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1128 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4MKM. Duration: 13.00 days. Decay Date: 1979-09-27 . USAF Sat Cat: 11529 . COSPAR: 1979-081A. Apogee: 328 km (203 mi). Perigee: 173 km (107 mi). Inclination: 62.8000 deg. Period: 89.50 min. Summary: High resolution photo reconnaissance satellite; returned film capsule; maneuverable..

1981 September 14 - . 20:31 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC90/19. Launch Pad: LC90/pad?. LV Family: Tsiklon. Launch Vehicle: Tsiklon-2.
  • Cosmos 1306 - . Mass: 3,000 kg (6,600 lb). Nation: USSR. Agency: RVSN. Program: EORSAT. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: US-P. Decay Date: 1982-07-16 . USAF Sat Cat: 12828 . COSPAR: 1981-089A. Apogee: 424 km (263 mi). Perigee: 168 km (104 mi). Inclination: 65.0000 deg. Period: 90.40 min. Summary: Ocean monitoring; replaced Cosmos 1260..

1982 September 14 - . 20:05 GMT - . Launch Site: Kheysa. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 86 km (53 mi).

1983 September 14 - . 10:25 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC41/1. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1498 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Program: Resurs. Class: Earth. Type: Earth resources satellite. Spacecraft: Resurs F1-17F41. Duration: 15.00 days. Decay Date: 1983-09-29 . USAF Sat Cat: 14334 . COSPAR: 1983-096A. Apogee: 274 km (170 mi). Perigee: 206 km (128 mi). Inclination: 82.3000 deg. Period: 89.30 min. High resolution photo surveillance; film capsule; maneuverable; also performed earth resource tasks. Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation.

1984 September 14 - . 21:43 GMT - . Launch Site: Barking Sands. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 67 km (41 mi).

1985 September 14 - . 14:40 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-78.
  • CBR Submillimeter radio astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 297 km (184 mi).

1988 September 14 - . 13:55 GMT - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 78 km (48 mi).

1989 September 14 - . Launch Site: Palmachim. LV Family: Jericho. Launch Vehicle: Jericho 2.
  • Test mission - . Nation: Israel. Agency: IDF. Apogee: 300 km (180 mi).

1989 September 14 - . 09:49 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32. Launch Pad: LC32/pad?. LV Family: Tsiklon. Launch Vehicle: Tsiklon-3.
  • Cosmos 2038 - . Payload: Strela-3 no. 35. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 20232 . COSPAR: 1989-074A. Apogee: 1,410 km (870 mi). Perigee: 1,392 km (864 mi). Inclination: 82.6000 deg. Period: 113.80 min. Summary: Eight satellites launched by a single carrier rocket..
  • Cosmos 2043 - . Payload: Strela-3 no. 40. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 20237 . COSPAR: 1989-074F. Apogee: 1,410 km (870 mi). Perigee: 1,408 km (874 mi). Inclination: 82.6000 deg. Period: 114.00 min.
  • Cosmos 2039 - . Payload: Strela-3 no. 36. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 20233 . COSPAR: 1989-074B. Apogee: 1,410 km (870 mi). Perigee: 1,386 km (861 mi). Inclination: 82.6000 deg. Period: 113.70 min.
  • Cosmos 2040 - . Payload: Strela-3 no. 37. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 20234 . COSPAR: 1989-074C. Apogee: 1,416 km (879 mi). Perigee: 1,409 km (875 mi). Inclination: 82.6000 deg. Period: 114.10 min.
  • Cosmos 2041 - . Payload: Strela-3 no. 38. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 20235 . COSPAR: 1989-074D. Apogee: 1,410 km (870 mi). Perigee: 1,397 km (868 mi). Inclination: 82.6000 deg. Period: 113.90 min.
  • Cosmos 2042 - . Payload: Strela-3 no. 39. Mass: 220 kg (480 lb). Nation: USSR. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft: Strela-3. USAF Sat Cat: 20236 . COSPAR: 1989-074E. Apogee: 1,410 km (870 mi). Perigee: 1,403 km (871 mi). Inclination: 82.6000 deg. Period: 113.90 min.

1989 September 14 - . 19:00 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF02. Launch Vehicle: Peacekeeper. LV Configuration: Peacekeeper 01PA. FAILURE: Failure.
  • Operational test - . Nation: USA. Agency: USAF SAC. Apogee: 200 km (120 mi).

1990 September 14 - . 05:59 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 65048-403.
  • Cosmos 2100 - . Mass: 810 kg (1,780 lb). Nation: USSR. Agency: MO. Class: Navigation. Type: Navigation satellite. Spacecraft: Parus. USAF Sat Cat: 20804 . COSPAR: 1990-083A. Apogee: 1,012 km (628 mi). Perigee: 958 km (595 mi). Inclination: 82.9000 deg. Period: 104.80 min. Summary: Military navigation satellite..

1993 September 14 - .
  • Mir News 186: SPACE-WALKS (EVA-S) - . Nation: Russia. Program: Mir. Flight: Mir EO-14. Some weeks ago TsUP announced that the 3 EVA-s, which had been planned for Sept. this year had been put back and that this crew (the 14th main expedition to Mir) would not make any EVA-s at all. Later on there happened to be a plan to execute an EVA on 10.09.93. This EVA has been put back also. Meanwhile it was obvious that 1 or more EVA-s are badly needed for the inspection of the outer surface of the whole complex. Experts even considered the use of the SPK (MMU) for EVA-s. Board- engineer Serebrov knows how to fly with the SPK: he was the first cosmonaut to fly with it on 1.02.90. Radio traffic during recent passes revealed that the crew is preparing an EVA. Whether they will use the SPK or not is not clear.

    CONSEQUENCES OF THE PERSEID METEORITE STREAM ON 12.08.93:

    After a long period of silence the Russians officially admitted that the station suffered from hits caused by minuscule particles during the Perseid-meteorite stream. One hit even caused a hole in a solar battery with the diameter of appr. 6 cm. Meanwhile messages and questions about the damages reached the Mir crew by amateur radio. Experts are evaluating the eventual influence of the damages on the power supply of the complex. The crew cannot see the whole outer surface of the station from inside and so EVA-s must be carried out to inspect it thoroughly.

    RADIO-AMATEUR TRAFFIC:

    For some weeks again a lot of Packet radio tfc on 145.550 mc. Sometimes there are also calls by 'phone' on that frequency. On 12 and 13.09.93 the crew used 145.500 mc to contact the Irish amateur EI3SI by speech.

    Chris v.d. Berg, NL-9165/A-UK3202.


1997 September 14 - . 01:36 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/23. LV Family: Proton. Launch Vehicle: Proton-K/17S40. LV Configuration: Proton-K/17S40 (DM2) 391-01.
  • Iridium 29 - . Payload: Iridium s/n SV029. 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: 24944 . COSPAR: 1997-051A. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 3. Ascending node 230.9 degrees..
  • Iridium 31 - . Payload: Iridium s/n SV031. 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: 24950 . COSPAR: 1997-051G. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 3. Ascending node 230.9 degrees..
  • Iridium 32 - . Payload: Iridium s/n SV032. 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: 24945 . COSPAR: 1997-051B. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 3. Ascending node 230.9 degrees..
  • Iridium 33 - . Payload: Iridium s/n SV033. 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: 24946 . COSPAR: 1997-051C. Apogee: 778 km (483 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 3. Ascending node 230.9 degrees. Active when it collided with Cosmos 2251 at 16:56 GMT on 10 February 2009, destroying both satellites and creating a debris cloud im MEO..
  • Iridium 27 - . Payload: Iridium s/n SV027. 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: 2002-02-01 . USAF Sat Cat: 24947 . COSPAR: 1997-051D. Apogee: 553 km (343 mi). Perigee: 542 km (336 mi). Inclination: 86.6500 deg. Period: 95.61 min. Summary: Plane 3. Ascending node 223.2 degrees. Failed in low orbit..
  • Iridium 28 - . Payload: Iridium s/n SV028. 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: 24948 . COSPAR: 1997-051E. Apogee: 779 km (484 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 3. Ascending node 230.9 degrees..
  • Iridium 30 - . Payload: Iridium s/n SV030. 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: 24949 . COSPAR: 1997-051F. Apogee: 780 km (480 mi). Perigee: 776 km (482 mi). Inclination: 86.4000 deg. Period: 100.40 min. Summary: Plane 3. Ascending node 230.8 degrees..

1998 September 14 - .
  • Mir News 438: Mir-routine - . Nation: Russia. Program: Mir. Flight: Mir EO-26; Mir EO-26/-27. After the return of the freighter Progress-M39, the cosmonauts were able to execute a number of experiments. From 1 until 3.09.98 they worked on geophysical, astrophysical and medical experiments. During the geophysical experiments they used the lidar Alisa. Apart from medical experiments the cosmonauts also underwent routine check-ups of their cardiovascular system.

    In this period, but also thereafter, not much was reported about technical failures. Now and then the CO2 scrubber, Vozdukh, in the Base Block received extra attention and the BKV-3, the a.c., was less capricious and mostly functioned without hiccups after it had been switched off and on some times. The internal pressure of the system remained the problem.

    Communications:

    Meanwhile the passes of the Mir-complex for Western Europe shifted to the night. So not much radio traffic can be monitored. Observers in Finland and Sweden confirmed that Luch-1/Gelios is used for Russian manned spaceflight and produces very strong signals. To be able to do somewhat with those signals they have to do a lot of experimental work before they can do with Luch-1 what we could do with Altair-1 and later on with Altair-2. One of them has a dish with a diameter of 3.5 Meter and via a channel not in use for Mir-TsUP traffic, he produced nice pictures of a Proton launch relayed by Luch-1/Gelios.

    Radio-amateurism:

    Until 2.09.98 the 145.940 mc was in use for Packet Radio. As of 2.09 Packet Radio they use 145.985 mc again.

    1st Spacewalk (internal Spacewalk) crew Main Expedition Mir nr. 26:

    After 3.09.98 most attention of the cosmonauts was dedicated to the preparations for the Internal spacewalk scheduled for half September. Until 15.09.98 the crew used some days to check spacesuits and equipment, but also to prepare the complicated procedures in relation to the disconnection of cables in order to close some hatches of the P.Kh.O. during the IVA. The internal spacewalk (IVA) inside the module Spektr will be executed in the night from 15 to 16.09.98. The IVA will last approx. 3 hrs, but the times still have to be confirmed. Possibly the hatch between the P.Kh.O. (transition section) and Spektr will be opened on 15.09.1998 at 2100 UTC. Radio traffic during the preparations and the IVA itself will be handled via the Eastern tracking stations in Russia and the Luch-1/Gelios satellite. During some small windows radio communications might be monitored in Western Europe during the first passes of the Mir-complex, to begin with that in orbit 71828, 2247-2255 UTC.

    Chris v.d. Berg, NL-9165/A-UK3202.


1999 September 14 - . 11:06 GMT - . Launch Site: Andoya. LV Family: Viper. Launch Vehicle: Viper 3A. LV Configuration: Viper 3A TR-S-13 Sphere.
  • TRAMP-99 Aeronomy mission - . Nation: Norway. Agency: DLR. Apogee: 75 km (46 mi).

2000 September 14 - . 22:54 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G. LV Configuration: Ariane 5G V130 (506).
  • Astra 2B - . Mass: 3,320 kg (7,310 lb). Nation: Europe. Agency: SES. Manufacturer: Toulouse. Program: Astra. Class: Communications. Type: Civilian communications satellite. Spacecraft: Eurostar 2000. USAF Sat Cat: 26494 . COSPAR: 2000-054A. Apogee: 35,801 km (22,245 mi). Perigee: 35,772 km (22,227 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Direct Broadcasting satellite. Launch postponed from July 25. Astra 2B was an Astrium/Toulouse Eurostar 2000+ television broadcast satellite owned by the Luxembourg-based Societe Europeene de Satellites. The satellite was to be stationed at 28.2E to replace the German DFS Kopernikus. It carried 28 Ku-band transponders. By September 19 Astra 2B was in a 31,153 x 35,762 km x 0.3 deg orbit, approaching geosynchronous altitude. Stationed at 28 deg E. Positioned in geosynchronous orbit at 28 deg E in 2000. As of 20 August 2001 located at 28.50 deg E drifting at 0.011 deg E per day. As of 2007 Mar 10 located at 28.15E drifting at 0.017W degrees per day.
  • GE 7 - . Mass: 3,320 kg (7,310 lb). Nation: USA. Agency: GE Americom. Manufacturer: Lockheed. Program: Americom. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 26495 . COSPAR: 2000-054B. Apogee: 35,797 km (22,243 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Direct Broadcasting satellite. GE Americom satellite to provide cable TV distribution coverage to the USA. Equipped with 24 C-band transponders. Its dry mass was 912 kg and it carried 1023 kg of fuel at launch. The satellite is an A2100A model built by Lockheed Martin/Lockheed, the first lightweight A2100 with a mass about half that of earlier A2100 satellites. By September 19 GE 7 was in a 35,832 x 35,869 km x 0.1 deg orbit drifting over 146 deg W. Stationed at 137 deg W. Positioned in geosynchronous orbit at 137 deg W in 2000. As of 4 September 2001 located at 136.92 deg W drifting at 0.003 deg E per day. As of 2007 Mar 9 located at 137.03W drifting at 0.000E degrees per day.

2001 September 14 - . 23:34 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz 11A511U. LV Configuration: Soyuz 11A511U 677.
  • Progress M-SO1 - . Payload: Progress M-SO1 s/n 301. Mass: 6,900 kg (15,200 lb). Nation: Russia. Agency: RAKA. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Flight: ISS EO-3. Spacecraft: Progress M-SO. Duration: 12.00 days. Decay Date: 2001-09-26 . USAF Sat Cat: 26908 . COSPAR: 2001-041A. Apogee: 335 km (208 mi). Perigee: 329 km (204 mi). Inclination: 51.6000 deg. Period: 91.20 min. Progress M-SO1 was the designation given to the service module section of a Progress M; the 3900 kg Pirs docking and airlock module for the ISS replaced the standard cargo and fuel sections. It also carried an astronaut chair, a space suit, a small crane, and some equipment for the Zvezda module of the ISS. Progress-M No. 301 was launched into an initial 180 km circular orbit. By September 16 it had maneuvered into a 238 x 264 km orbit; by 0038 GMT on September 17, a 385 x 395 km x 51.6 deg orbit upon rendezvous with the ISS. The Progress began a fly around of the station and lined up with the nadir port on Zvezda. Docking of Pirs with Zvezda came at 0105 GMT on September 17. The Progress M-SO1 later undocked from the Pirs nadir port to leave it free for future dockings. Pirs gave extra clearance from the Station for ships docking underneath Zvezda, and was also used as an airlock for spacewalks using the Russian Orlan EVA suits. Progress M-SO1 service module undocked from the Pirs module at 1536 GMT on September 26 and was deorbited over the Pacific at 2330 GMT the same day.

2002 September 14 - . 10:27 GMT - . Launch Site: Andoya. LV Family: Viper. Launch Vehicle: Viper 3A.
  • RO-A-FS-09 Aeronomy mission - . Nation: Germany. Agency: DLR. Apogee: 75 km (46 mi).

2005 September 14 - . 08:01 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF09. Launch Pad: LF09?. LV Family: Minuteman. Launch Vehicle: Minuteman 3. LV Configuration: Minuteman 3 ALCS.
  • GT-188GM operational test launch - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,300 km (800 mi).

2006 September 14 - . 13:41 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC31. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 2423 - . Mass: 6,750 kg (14,880 lb). Nation: Russia. Agency: VKS. Manufacturer: Kozlov. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Orlets-1. Duration: 64.00 days. Decay Date: 2006-11-17 . USAF Sat Cat: 29402 . COSPAR: 2006-039A. Apogee: 306 km (190 mi). Perigee: 208 km (129 mi). Inclination: 64.9000 deg. Period: 89.70 min. Summary: Military surveillance; believed to be a derivative of the Orlets-1 multiple-capsule-return reconnaisance sattelite. Destroyed in orbit on November 17 at the end of its mission..

2007 September 14 - . 01:31 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2022. LV Configuration: H-IIA 2022 H-IIA-13.
  • Kaguya - . Payload: Selene. Nation: Japan. Agency: Mitsubishi. Class: Moon. Type: Lunar probe. Spacecraft: Kaguya. USAF Sat Cat: 32054 . COSPAR: 2007-039A. Another of a series of new lunar probes to be launched in the next few years by China, India, Japan, USA, and Europe. Selene was dubbed Kaguya, a Japanese moon goddess, after launch. It included an HDTV camera. In lunar orbit two subsatellites would be released to provide continuous communications as well as better characterize the moon's gravity field. By 30 September Kaguya was in a 2243 km x 378,132 km lunar transfer orbit. On 3 October at 21:00 GMT it entered its initial 101 km x 11741 km x 95 deg lunar orbit. It then began maneuvers to enter its operational 100 km circular orbit, releasing the subsatellites on 9 and 12 October.
  • Okina - . Payload: Selene. Nation: Japan. Agency: Mitsubishi. Class: Moon. Type: Lunar probe. Spacecraft: Kaguya. USAF Sat Cat: 32055 . COSPAR: 2007-039B. Summary: The Okina relay satellite was released from Kaguya into a 115 km x 2,399 km lunar orbit at 00:36 GMT on 9 October 2007..
  • Ouna - . Payload: Selene. Nation: Japan. Agency: Mitsubishi. Class: Moon. Type: Lunar probe. Spacecraft: Kaguya. USAF Sat Cat: 32056 . COSPAR: 2007-039C. Summary: The Ouna (VRAD) subsatellite was released from Kaguya into a 127 km x 795 km lunar orbit at 04:28 GMT on 12 October 2007..

2007 September 14 - . 11:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz 11A511U. LV Configuration: Soyuz-U 098.
  • Foton M-3 - . Mass: 6,500 kg (14,300 lb). Nation: Russia. Agency: RAKA. Manufacturer: Kozlov. Class: Materials. Type: Materials science satellite. Spacecraft: Foton. Decay Date: 2007-09-26 . USAF Sat Cat: 32058 . COSPAR: 2007-040A. Apogee: 280 km (170 mi). Perigee: 258 km (160 mi). Inclination: 62.9000 deg. Period: 89.90 min. Recoverable spacecraft derived from the Vostok. Carried Russian and European microgravy, life sciences and technology experiments. After deploying the YES-2 tether on 25 September, Foton M-3 was deorbited at 07:23 GMT on 26 September and successfully landed at 07:58 GMT in Kazakhstan.
  • YES-2 - . Payload: Young Engineers Satellite. Mass: 5.00 kg (11.00 lb). Nation: Europe. Agency: ESA. Manufacturer: ESTEC. Class: Technology. Type: Navigation technology satellite. Spacecraft: YES. COSPAR: 2007-040x. YES-2/Fotino space tether for re-entry experiment. The YES-2 tether was deployed from the Nauka module at the front end of Foton at 04:47 on 25 September, and releaed at 07:20 after reaching only 8.5 km of the planned 30 km tether length. The 5 kg Fotino reentry capsule separated from the MASS data support system at the end of the tether at around 07:30. The idea was to toss the Fotino against the direction of orbital motion to push it into a lower orbit and re-entry without the need for a retrorocket. Unfortunately the final outcome of the experiment remained unknown.

2009 September 14 - . 17:40 GMT - . Launch Site: White Sands. LV Family: Black Brant. Launch Vehicle: Black Brant 9.
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