Encyclopedia Astronautica
September 28


September 28 Chronology


1902 September 28 - .
  • Birth of Vladimir Mikhailovich Myasishchev - . Nation: Russia. Summary: Soviet Chief Designer 1951-1960 of OKB-23. Developed innovative M-4, M-50 bombers, Buran cruise missiles, and VKA spaceplane. Bureau merged with Chelomei, 1960. Later Director of TsAGI. Regained his own design bureau just before his death..

1908 September 28 - .
  • Birth of Max Ernst Nowak - . Nation: Germany; USA. Summary: German engineer in WW2, member of the Rocket Team in the United States thereafter..

1940 September 28 - .
  • Birth of Aleksandr Segeyevich Ivanchenkov - . Nation: Russia. Summary: Russian engineer cosmonaut. Flew on Salyut 6 EO-2, Salyut 7 EP-1. Graduated MAI, 1964 Civilian Engineer, Korolev OKB. Trained for a Buran flight. From 1993 served as deputy director of 29th Department, RKK Energia..

1944 September 28 - . Launch Site: Peenemuende. Launch Complex: Peenemuende P10. LV Family: V-2. Launch Vehicle: V-2. LV Configuration: V-2 V-238. FAILURE: Possibly correct launch date is 27.09.1944..
1945 September 28 - . Launch Site: White Sands. Launch Complex: White Sands LC33. LV Family: Wac. Launch Vehicle: WAC. LV Configuration: WAC 2.
  • Dummy launch - . Nation: USA. Agency: USA OR. Apogee: 2.00 km (1.20 mi). Summary: Launcher/booster stage test. No upper stage..

1949 September 28 - . Launch Site: Kapustin Yar. Launch Complex: Kapustin Yar V-2. LV Family: R-1. Launch Vehicle: R-1. LV Configuration: R-1 II-10.
  • Test mission - . Nation: USSR. Agency: Korolev. Apogee: 100 km (60 mi).

1950 September 28 - .
  • Birth of Vitali Aleksandrovich Lopota - . Nation: Russia. Summary: Chechen engineer. General Designer of TsNII-RTK from 1991 to 2007. General Designer of RKK Energia from 2007.

1954 September 28 - . Launch Site: Edwards. LV Family: Navaho. Launch Vehicle: Navaho X-10. LV Configuration: X-10 s/n 4 GM-19310.
  • Navaho X-10 flight 10 - . Nation: USA. Program: Navaho. Structural test flight. Successfully made extreme maneuvers at Mach 1.84. However automated landing system attempted to make landing flare 6 m below the runway level. Vehicle impacted at high speed and was destroyed. However the flight set a speed record for a turbojet-powered aircraft.

1955 September 28 - . 01:13 GMT - . Launch Site: Atlantic Ocean. Launch Pad: 58.5 N x 54.0 W. Launch Platform: AGB-5. LV Family: Rockoon. Launch Vehicle: Loki Rockoon. FAILURE: Failure.
  • SUI 43 Ionosphere / aeronomy mission - . Nation: USA. Agency: SUI. Apogee: 100 km (60 mi). Summary: Launched at Atlantic Ocean Launch Site 13 Launch Point 6 - - Latitude: 58.45 N - Longitude: 53.95 W..

1955 September 28 - . 14:54 GMT - . Launch Site: Atlantic Ocean. Launch Pad: 61.2 N x 55.3 W. Launch Platform: AGB-5. LV Family: Rockoon. Launch Vehicle: Deacon Rockoon.
  • SUI 44 Ionosphere / aeronomy mission - . Nation: USA. Agency: SUI. Apogee: 100 km (60 mi). Summary: Launched at Atlantic Ocean Launch Site 13 Launch Point 7 - - Latitude: 61.17 N - Longitude: 55.25 W..

1955 September 28 - . 19:22 GMT - . Launch Site: Atlantic Ocean. Launch Pad: 62.0 N x 56.1 W. Launch Platform: AGB-5. LV Family: Rockoon. Launch Vehicle: Deacon Rockoon Loki. FAILURE: Failure.
  • SUI 45 test - . Nation: USA. Agency: SUI. Apogee: 102 km (63 mi). Summary: Launched at Atlantic Ocean Launch Site 13 Launch Point 8 - - Latitude: 62.03 N - Longitude: 56.08 W..

1956 September 28 - .
  • X-1B Flight 15 - . Crew: McKay. Payload: X-1B flight 15. Nation: USA. Related Persons: McKay. Class: Manned. Type: Manned rocketplane. Spacecraft: X-1B. Summary: NACA flight 5. Three-chamber engine run to 18300 m to obtain heating data..

1958 September 28 - . 19:42 GMT - . Launch Site: Pacific Ocean. Launch Pad: 40.0 N x 150.0 W. Launch Platform: LSD-31. LV Family: Asp. Launch Vehicle: Nike Asp. LV Configuration: Nike Asp NN8.57F.
  • Test / solar ultraviolet mission - . Nation: USA. Agency: USN. Apogee: 225 km (139 mi). Summary: Nike-Asp test flight from Navy LSD Point Defiance near Puka Island reached 225 km, the highest altitude ever reached by ship-launched rocket, in preliminary test of Nike-Asp for use in IGY solar eclipse studies..

1959 September 28 - .
  • Lenticular-shaped vehicle proposed for the lunar mission - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM; CSM Heat Shield; CSM Source Selection. At the third meeting of STG's New Projects Panel, Alan B. Kehlet presented suggestions for the multimanned reentry capsule. A lenticular-shaped vehicle was proposed, to ferry three occupants safely to earth from a lunar mission at a velocity of about 36,000 feet per second.

1959 September 28 - .
1960 September 28 - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC19. LV Family: Titan. Launch Vehicle: Titan 1. LV Configuration: Titan I J-8.
  • Mk 4 re-entry vehicle test - . Nation: USA. Agency: USAF. Apogee: 1,000 km (600 mi).

1960 September 28 - . 22:45 GMT - . Launch Site: Fort Churchill. LV Family: Cajun. Launch Vehicle: Nike Cajun. LV Configuration: Nike Cajun OB6.07.
  • H2O / ne Aeronomy mission - . Nation: USA. Agency: USAF. Apogee: 105 km (65 mi).

1961 September 28 - . Launch Site: Fairchild AFB. LV Family: Atlas. Launch Vehicle: Atlas E.
  • Atlas SMS 567 operational. - . Nation: USA. Summary: Fairchild AFB SMS 567 operational.

1961 September 28 - .
  • Tiros 2 rocket test. - . Nation: USA. Program: Tiros. Summary: Pair of spinup rockets on Tiros II successfully fired after more than 10 months in orbit..

1961 September 28 - . LV Family: Atlas. Launch Vehicle: Atlas Centaur LV-3C.
  • Mariner moved to Atlas-Agena due to Centaur delay. - . Nation: USA. Program: Mariner. Class: Venus. Type: Venus probe. Spacecraft: Mariner 1-2. Summary: NASA announced that instrumented Venus probe to be launched next year would be launched by an Atlas-Agena B rather than a Centaur rocket as originally planned..

1961 September 28 - . 17:50 GMT - . Launch Site: Hidden Hills DZ. Launch Pad: 36.1 N x 116.0 W. Launch Platform: NB-52 008. LV Family: X-15. Launch Vehicle: X-15. LV Configuration: X-15 2-19-35.
  • X-15A Mach 5, Heat Trans. test - . Nation: USA. Agency: NASA; USAF. Apogee: 31 km (19 mi). Summary: Maximum Speed - 5792 kph. Maximum Altitude - 31030 m. Test reentry heat limit. Smoke in cockpit due to scorching paint..

1962 September 28 - . Launch Site: Ellsworth AFB. LV Family: Titan. Launch Vehicle: Titan 1.
  • Titan I ICBM 850th SMS (nine missiles) declared operational at Ellsworth AFB - . Nation: USA.

1962 September 28 - . Launch Site: Vandenberg.
  • First international satellite launch - Vandenberg - . Nation: USA.

1962 September 28 - . 18:04 GMT - . Launch Site: Hidden Hills DZ. Launch Pad: 36.1 N x 116.0 W. Launch Platform: NB-52 008. LV Family: X-15. Launch Vehicle: X-15. LV Configuration: X-15 2-29-50.
  • X-15A Heating, VO Stab test - . Nation: USA. Agency: NASA; USAF. Apogee: 20 km (12 mi). Summary: This and most following flights without lower ventral. Maximum Speed - 4450 kph. Maximum Altitude - 20790 m..

1962 September 28 - . 21:01 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF04. LV Family: Minuteman. Launch Vehicle: Minuteman 1A. LV Configuration: Minuteman 1A 503. FAILURE: Failure.
  • Research and development Category I test - . Nation: USA. Agency: USAF. Apogee: 50 km (31 mi). Summary: Initial launch of a Minuteman I from Vandenberg.

1963 September 28 - .
  • Gagarin attends the IAF Congress - . Nation: USSR. Related Persons: Gagarin. Summary: Gagarin receives a 20,000 franc prize from the International Astronautical Federation at the 14th IAF Congress..

1963 September 28 - . Launch Site: Vandenberg.
  • Initial launch of Thor/Able-Star from Vandenberg - . Nation: USA.

1963 September 28 - . Launch Site: Baikonur. Launch Complex: Baikonur LC67/21. LV Family: Tsiklon. Launch Vehicle: R-36 8K67. LV Configuration: R-36 8K67 G22500-02L. FAILURE: Failure.
  • State trials launch (1) - . Nation: USSR. Agency: RVSN. Apogee: 0 km ( mi).

1963 September 28 - . 14:43 GMT - . Launch Site: Wallops Island. LV Family: Aerobee. Launch Vehicle: Aerobee 150A. LV Configuration: Aerobee 150A NASA 04.64GI.
  • Ionosphere mission - . Nation: USA. Agency: NASA. Apogee: 226 km (140 mi).

1963 September 28 - . 20:22 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC2E. LV Family: Delta. Launch Vehicle: Thor Able-Star. LV Configuration: Thor Ablestar-2 375 AB013.
  • Transit 5BN-1 - . Mass: 70 kg (154 lb). Nation: USA. Agency: USN. Program: Transit. Class: Navigation. Type: Navigation satellite. Spacecraft: Transit. USAF Sat Cat: 670 . COSPAR: 1963-038B. Apogee: 1,125 km (699 mi). Perigee: 1,066 km (662 mi). Inclination: 90.1000 deg. Period: 107.20 min. First test of nuclear-powered Transit operational prototype. Carried SNAP-9A nuclear power source. The satellite achieved gravity-gradient stabilization, but upside down, making the signal level too low for operational users with low-gain antennas. However, geodetic and navigational evaluation data were obtained.
  • Transit 5E-1 - . Payload: APL SN 39. Mass: 61 kg (134 lb). Nation: USA. Agency: USN. Program: Transit. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Transit. USAF Sat Cat: 671 . COSPAR: 1963-038C. Apogee: 1,123 km (697 mi). Perigee: 1,065 km (661 mi). Inclination: 90.1000 deg. Period: 107.10 min. The missions of Satellite 1963-038C were to measure omnidirectional flux of protons and electrons at various energy levels, radiation effects on transistors, and the effectiveness of thermal coatings. The satellite was launched together with a classified Department of Defense spacecraft on September 28, 1963. Its planned orbit was apogee 1120 kilometres, perigee 1070 kilometres, inclination 88.9 degrees. The satellite weighed 62 kg; its body was in the shape of an 0.46 m x 0.25 m octagonal prism. It was powered by four solar blades and transmited on 136, 162, and 324 mcs. The spacecraft was built for the Bureau of Naval Weapons. In 1967 it was still sending usable data from all systems.

1964 September 28 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 627. LV Family: Polaris. Launch Vehicle: Polaris A3. LV Configuration: Polaris A3P-57.
  • Operational test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1965 September 28 - . LV Family: Titan. Launch Vehicle: Titan 2.
  • Gemini launch vehicle (GLV) 8 was erected in the west cell of the vertical test facility at Martin-Baltimore. - . Nation: USA. Flight: Gemini 8. Summary: Power was applied to the vehicle October 13, following the deerection of GLV-7. Subsystems Functional Verification Tests of GLV-8 were completed November 4..

1965 September 28 - . 09:09 GMT - . Launch Site: White Sands. Launch Complex: White Sands LC35. Launch Pad: LC35 (L-21). LV Family: Aerobee. Launch Vehicle: Aerobee 150. LV Configuration: Aerobee 150 NASA 04.150GA-GI-GB.
  • Meteors / Ionosphere Meteorites / biology mission - . Nation: USA. Agency: NASA. Apogee: 183 km (113 mi).

1965 September 28 - . 14:35 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA5B. Launch Pad: LA5B?. LV Family: Black Knight. Launch Vehicle: Black Knight 301/C2. LV Configuration: Black Knight-301/C2 BK.24.
  • Dazzle re-entry vehicle test - . Nation: UK. Agency: RAE. Apogee: 605 km (375 mi).

1965 September 28 - . 18:07 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 3-49-73.
  • X-15A N.Scan/BLN/Tail test - . Nation: USA. Agency: NASA; USAF. Apogee: 90 km (55 mi). Summary: Maximum Speed - 6005 kph. Maximum Altitude - 90099 m. Astronaut wings flight (USAF definition)..

1966 September 28 - .
  • M2 Flight 9 - . Crew: Sorlie. Payload: M2-F2 flight 9. Nation: USA. Related Persons: Sorlie. Program: NASA Lifting Body. Class: Manned. Type: Manned spaceplane. Spacecraft: M2-F2. Summary: Maximum Speed - 713 kph. Maximum Altitude - 13720 m. Flight Time - 233 sec..

1966 September 28 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 619. LV Family: Polaris. Launch Vehicle: Polaris A2. LV Configuration: Polaris A2P.
  • Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1966 September 28 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 619. LV Family: Polaris. Launch Vehicle: Polaris A2. LV Configuration: Polaris A2P.
  • Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 1,000 km (600 mi).

1966 September 28 - . 18:16 GMT - . Launch Site: Fort Churchill. LV Family: Black Brant. Launch Vehicle: Black Brant 2. LV Configuration: Black Brant II CRL AC17.604D.
  • Ionosphere mission - . Nation: USA. Agency: AFCRL. Apogee: 116 km (72 mi).

1966 September 28 - . 19:12 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg SLC4W. LV Family: Titan. Launch Vehicle: Titan 3B. LV Configuration: Titan IIIB 3B-2.
  • OPS 4096 - . Payload: KH-8 no. 02 / 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: 1966-10-07 . USAF Sat Cat: 2433 . COSPAR: 1966-086A. Apogee: 287 km (178 mi). Perigee: 146 km (90 mi). Inclination: 93.9000 deg. Period: 88.80 min. Summary: KH-8 type satellite. Space craft engaged in investigation of spaceflight techniques and technology (US Cat A). .

1967 September 28 - .
  • Elimination of all flammables from the Apollo cabin not possible - . Nation: USA. Program: Apollo. Spacecraft: Apollo CSM; CSM Cockpit. In spite of efforts to eliminate all flammable materials from the interior of the spacecraft cabin during flight, it was apparent that this could not be completely accomplished. For example, silicone rubber hoses, flight logs, food, tissues, and other materials would be exposed with in the cabin during portions of the mission. However, flammable materials would be outside their containers only when actually needed. Special fire extinguishers would be carried during flight.

1967 September 28 - . 00:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Delta. Launch Vehicle: Delta E1. LV Configuration: Thor Delta E1 442/D52.
  • Intelsat 2 F-4 - . Mass: 87 kg (191 lb). Nation: International. Agency: INTELSAT. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 2. Completed Operations Date: 1977-05-01 . USAF Sat Cat: 2969 . COSPAR: 1967-094A. Apogee: 35,885 km (22,297 mi). Perigee: 35,729 km (22,200 mi). Inclination: 13.0000 deg. Period: 1,437.10 min. Spacecraft engaged in practical applications and uses of space technology such as weather or communication (US Cat C). Positioned in geosynchronous orbit over the Pacific Ocean at 176 deg E in 1967-1970; over the Pacific Ocean 166 deg W in 1971; over the Atlantic Ocean 30-42 deg W in 1972 As of 1 August 2001 located at 36.36 deg W drifting at 0.096 deg E per day. As of 2007 Mar 7 located at 168.68W drifting at 0.093W degrees per day.

1967 September 28 - . 16:35 GMT - . Launch Site: Fort Churchill. LV Family: Black Brant. Launch Vehicle: Black Brant 5A. LV Configuration: Black Brant VA AFF-VA-119.
  • Test / ionosphere mission - . Nation: Canada. Agency: NRCC. Apogee: 165 km (102 mi).

1968 September 28 - .
  • Cosmonaut exams are held for Beregovoi, Shatalov, and Volynov. - . Nation: USSR. Related Persons: Beregovoi; Shatalov; Volynov; Leonov; Makarov; Kuklin; Bykovsky; Rukavishnikov; Klimuk; Popovich; Sevastyanov; Voloshin. Program: Soyuz; Lunar L1. Flight: Soyuz 3; Soyuz 4; Soyuz 5; Soyuz 7K-L1 mission 1; Soyuz 7K-L1 mission 2; Soyuz 7K-L1 mission 3. Spacecraft: Soyuz 7K-OK; Soyuz 7K-L1. The results will establish the order in which they will fly as Soyuz commanders. A 25-person board, consisting of spacecraft designers and cosmonauts, conduct the oral examinations. Each cosmonaut must answer five mandatory essay questions and select two two-part questions. All three are certified for flight and have a complete mastery of the Soyuz systems.

    Mishin and Kamanin meet and decide on L1 crews: Leonov-Makarov (with Kuklin as back-up); Bykovsky-Rukavishnikov (Klimuk back-up); and Popovich-Sevastyanov (Voloshin back-up). But that evening Leonov has yet another automobile accident. He hit a bus with his Volga at kilometre 24 near Shchelkovsky. This was his second accident in four months. Kamanin decides to prohibit him from driving automobiles for six months.


1968 September 28 - .
1969 September 28 - .
  • Soyuz 6-7-8 flight preparations - . Nation: USSR. Related Persons: Nikolayev. Program: Soyuz. Flight: Soyuz 6; Soyuz 7; Soyuz 8. It is Sunday, but the cosmonauts are at work, training on the scientific equipment for the flight and preparing for the autonomous navigation experiment. Nikolayev is preparing the work plan for the launch of the first spacecraft. The cosmonauts have been working ten hours per day for weeks now without interruption. The use of a new anti-radiation vitamin preparation the cosmonauts will take during the flights is discussed.

1970 September 28 - .
  • Centrifuge negotiations. - . Nation: USSR. Summary: Kamanin prepares Nikolayev and Tereshkova for their trips to West Germany and the USA. A Soviet delegation goes to Sweden to negotiate a contract for purchase of a TsF-20 centrifuge..

1970 September 28 - . 01:20 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-5.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 108 km (67 mi).

1970 September 28 - . 09:01 GMT - . Launch Site: White Sands. LV Family: Aerobee. Launch Vehicle: Aerobee 170. LV Configuration: Aerobee 170 NASA 13.26CG.
  • Astronomy mission - . Nation: USA. Agency: NASA. Apogee: 200 km (120 mi).

1971 September 28 - .
1971 September 28 - . 04:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-4S. LV Configuration: Mu-4S M-4S-3.
  • SS-01 Shinsei - . Payload: MS-F2. Mass: 65 kg (143 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SS. USAF Sat Cat: 5485 . COSPAR: 1971-080A. Apogee: 1,866 km (1,159 mi). Perigee: 872 km (541 mi). Inclination: 32.0000 deg. Period: 113.10 min. Summary: Scientific observations in outer space. Injection point 29 deg 7 min N, 145 deg 8 min E. .

1971 September 28 - . 07:40 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. Launch Pad: LC1 or LC31. LV Family: R-7. Launch Vehicle: Voskhod 11A57.
  • Cosmos 441 - . Mass: 6,300 kg (13,800 lb). Nation: USSR. Agency: MOM. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: Zenit-4M. Duration: 12.00 days. Decay Date: 1971-10-10 . USAF Sat Cat: 5486 . COSPAR: 1971-081A. Apogee: 266 km (165 mi). Perigee: 207 km (128 mi). Inclination: 65.0000 deg. Period: 89.20 min. Summary: High resolution photo reconnaissance satellite; returned film capsule; maneuverable..

1971 September 28 - . 10:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC81/24. LV Family: Proton. Launch Vehicle: Proton-K/D. LV Configuration: Proton-K/D 257-01.
  • Luna 19 - . Payload: Ye-8-LS s/n 202. Mass: 5,810 kg (12,800 lb). Nation: USSR. Agency: MOM. Program: Luna. Class: Moon. Type: Lunar probe. Spacecraft: Luna Ye-8-LS. USAF Sat Cat: 5488 . COSPAR: 1971-082A. Apogee: 140 km (80 mi). Perigee: 140 km (80 mi). Inclination: 40.6000 deg. Period: 121.75 min. Heavy lunar Orbiter; conducted lunar surface mapping. Luna 19 entered an intermediate earth parking orbit and was then put on a translunar trajectory by the Proton Block D stage. It entered lunar orbit on October 3, 1971. Luna 19 extended the systematic study of lunar gravitational fields and location of mascons (mass concentrations). It also studied the lunar radiation environment, the gamma-active lunar surface, and the solar wind. Photographic coverage via a television system was also obtained. Parameters are for lunar orbit.

1971 September 28 - . 11:48 GMT - . Launch Site: South Uist. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P49H.
  • Winter Anomaly / Stratosphere Ionosphere mission - . Nation: UK. Agency: SRC. Apogee: 142 km (88 mi).

1972 September 28 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 632. Launch Vehicle: Poseidon.
  • FOT-2 Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1972 September 28 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 632. Launch Vehicle: Poseidon.
  • FOT-2 Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1972 September 28 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 632. Launch Vehicle: Poseidon.
  • FOT-2 Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1972 September 28 - . Launch Site: ETR Launch Area. Launch Platform: SSBN 632. Launch Vehicle: Poseidon.
  • FOT-2 Follow-on operational missile test - . Nation: USA. Agency: USN. Apogee: 500 km (310 mi).

1973 September 28 - . 03:00 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: SHIR. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 91 km (56 mi).

1974 September 28 - . 11:32 GMT - . Launch Site: South Uist. LV Family: Petrel. Launch Vehicle: Petrel 1. LV Configuration: Petrel P161H.
  • Electron density Ionosphere mission - . Nation: UK. Agency: SRC. Apogee: 119 km (73 mi).

1974 September 28 - . 15:34 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF22. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • FOT GT46GB Follow-on Test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1976 September 28 - . 21:06 GMT - . Launch Site: Kheysa. LV Family: M-100. Launch Vehicle: M-100.
  • - . Nation: USSR. Apogee: 85 km (52 mi).

1977 September 28 - . LV Family: UR-100N. Launch Vehicle: UR-100NU.
  • First UR-100NU launch. - . Nation: USSR.

1977 September 28 - . 15:33 GMT - . Launch Site: Poker Flat. LV Family: Super Chief. Launch Vehicle: Talos Castor. LV Configuration: Talos Castor DNA IC733.03-1.
  • SPIRE I Infrared background mission - . Nation: USA. Agency: DNA. Apogee: 275 km (170 mi).

1978 September 28 - . 00:20 GMT - . Launch Site: Kwajalein. Launch Vehicle: Rocketsonde.
  • Arcasonde - . Nation: USA. Agency: MRN. Apogee: 68 km (42 mi).

1979 September 28 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF08. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • FOT GT70GM Follow-on Test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1979 September 28 - . 12:20 GMT - . Launch Site: Plesetsk. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Cosmos 1138 - . 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: 1979-10-12 . USAF Sat Cat: 11548 . COSPAR: 1979-085A. Apogee: 373 km (231 mi). Perigee: 199 km (123 mi). Inclination: 72.9000 deg. Period: 90.20 min. Summary: Photo surveillance; returned film capsule..

1980 September 28 - . 15:09 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC1. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Progress 11 - . Payload: Progress s/n 111. Mass: 7,014 kg (15,463 lb). Nation: USSR. Agency: MOM. Program: Salyut 6. Class: Manned. Type: Manned logistics spacecraft. Flight: Salyut 6 EO-4. Spacecraft: Progress. Duration: 73.95 days. Completed Operations Date: 1980-12-11 14:00:05 . Decay Date: 1980-12-11 14:00:05 . USAF Sat Cat: 11993 . COSPAR: 1980-079A. Apogee: 241 km (149 mi). Perigee: 188 km (116 mi). Inclination: 51.6000 deg. Period: 88.70 min. Unmanned supply vessel for Salyut 6. Delivery of various cargoes to the Salyut-6 orbital station. Docked with Salyut 6 on 30 Sep 1980 17:03:00 GMT. Undocked on 9 Dec 1980 10:23:00 GMT. Destroyed in reentry on 11 Dec 1980 14:00:00 GMT. Total free-flight time 4.23 days. Total docked time 69.72 days.

1981 September 28 - . 21:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/2. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 53775-114.
  • Cosmos 1311 - . Nation: USSR. Agency: MO. Class: Military. Type: Radar calibration target. Spacecraft: Taifun-2. Decay Date: 1983-08-28 . USAF Sat Cat: 12871 . COSPAR: 1981-097A. Apogee: 513 km (318 mi). Perigee: 462 km (287 mi). Inclination: 82.9000 deg. Period: 94.30 min. Summary: Released 25 Romb radar calibration subsatellites..

1982 September 28 - . 23:17 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-60 / Centaur D-1AR 5040.
  • Intelsat 5 F-5 - . Mass: 2,000 kg (4,400 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 5. USAF Sat Cat: 13595 . COSPAR: 1982-097A. Apogee: 36,404 km (22,620 mi). Perigee: 36,228 km (22,510 mi). Inclination: 9.0000 deg. Period: 1,463.30 min. Positioned in geosynchronous orbit at 63 deg E in 1982-1990; 66 deg E in 1991-1996; 33 deg E in 1996; 72 deg E in 1997-on. As of 3 September 2001 located at 16.28 deg E drifting at 6.707 deg W per day. As of 2007 Mar 9 located at 163.88W drifting at 6.709W degrees per day.

1983 September 28 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF04. LV Family: Minuteman. Launch Vehicle: Minuteman 2.
  • FOT GT145MS Follow-on Test launch - . Nation: USA. Agency: USAF SAC. Apogee: 1,300 km (800 mi).

1983 September 28 - . 07:59 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32/1. LV Family: Tsiklon. Launch Vehicle: Tsiklon-3.
  • Cosmos 1500 - . Payload: Okean-OE no. 1. Mass: 1,950 kg (4,290 lb). Nation: USSR. Agency: MO. Program: Okean. Class: Earth. Type: Earth resources radar satellite. Spacecraft: Okean-OE. Completed Operations Date: 1986-07-16 . USAF Sat Cat: 14372 . COSPAR: 1983-099A. Apogee: 621 km (385 mi). Perigee: 596 km (370 mi). Inclination: 82.5000 deg. Period: 96.90 min. Summary: Elaboration of new kinds of information-measuring apparatus and methods of remote investigation of the Pacific Ocean in the interests of science and of various branches of the national economy of the USSR. .

1984 September 28 - . 06:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32/2. LV Family: Tsiklon. Launch Vehicle: Tsiklon-3.
  • Cosmos 1602 - . Payload: Okean-OE no. 2. Mass: 1,950 kg (4,290 lb). Nation: USSR. Agency: MO. Program: Okean. Class: Earth. Type: Earth resources radar satellite. Spacecraft: Okean-OE. Completed Operations Date: 1986-12-05 . USAF Sat Cat: 15331 . COSPAR: 1984-105A. Apogee: 628 km (390 mi). Perigee: 597 km (370 mi). Inclination: 82.5000 deg. Period: 97.00 min. Gathering of operational information and continued trials of new kinds of information and measurement apparatus and methods of remote investigation of the seas and oceans and the earth's surface in the interests of science and of various branches of the n ational economy of the USSR.

1984 September 28 - . 14:00 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC200/39. LV Family: Proton. Launch Vehicle: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 327-02.
  • Cosmos 1603 - . Payload: Tselina-2 no. 1. Mass: 6,000 kg (13,200 lb). Nation: USSR. Agency: MOM. Program: Tselina. Class: Military. Type: Military naval signals reconnaisance satellite. Spacecraft: Tselina-2. USAF Sat Cat: 15333 . COSPAR: 1984-106A. Apogee: 863 km (536 mi). Perigee: 832 km (516 mi). Inclination: 71.0000 deg. Period: 101.90 min. Summary: First launch of new Tselina-2 ELINT satellite. .

1985 September 28 - . Launch Site: Yellow Sea Launch Area. Launch Pad: 35.0 N x 125.0 E. Launch Platform: XIA. Launch Vehicle: JL-1. FAILURE: Failure.
  • Test mission - . Nation: China. Agency: PRC. Apogee: 0 km ( mi).

1985 September 28 - . 23:36 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36B. LV Family: Atlas. Launch Vehicle: Atlas Centaur G. LV Configuration: Atlas G Centaur AC-65 / Centaur D-1AR 5045G.
  • Intelsat 5A F-12 - . Mass: 1,096 kg (2,416 lb). Nation: International. Agency: Intelsat. Program: Intelsat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Intelsat 5A. Completed Operations Date: 1998-06-23 . USAF Sat Cat: 16101 . COSPAR: 1985-087A. Apogee: 36,140 km (22,450 mi). Perigee: 36,086 km (22,422 mi). Inclination: 6.2000 deg. Period: 1,452.80 min. Telephone communications; 31 deg E. Launch vehicle put payload into geosynchronous transfer orbit Positioned in geosynchronous orbit at 60 deg E in 1985-1989; 1 deg W in 1989-1994; 21 deg W in 1994-1996; 56 deg W in 1996-1998 As of 28 August 2001 located at 145.57 deg E drifting at 4.159 deg W per day. As of 2007 Mar 10 located at 19.14E drifting at 4.163W degrees per day.

1986 September 28 - . 07:42 GMT - . Launch Site: Sea-launched. Launch Pad: UNKO. Launch Platform: USHAKOV. Launch Vehicle: MMR-06.
  • Aeronomy mission - . Nation: USSR. Agency: GMS. Apogee: 60 km (37 mi).

1988 September 28 - . 14:07 GMT - . Launch Site: Molodezhnaya. LV Family: M-100. Launch Vehicle: M-100B.
  • - . Nation: USSR. Apogee: 78 km (48 mi).

1989 September 28 - . 00:04 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32/2. LV Family: Tsiklon. Launch Vehicle: Tsiklon-3.
  • Intercosmos 24 - . Payload: AUOS-Z-AV-IK s/n 201. Mass: 1,000 kg (2,200 lb). Nation: USSR. Agency: MOM. Manufacturer: Yuzhnoye. Program: Intercosmos. Class: Technology. Type: Navigation technology satellite. Spacecraft: AUOS. Completed Operations Date: 1995-10-11 . USAF Sat Cat: 20261 . COSPAR: 1989-080A. Apogee: 2,414 km (1,499 mi). Perigee: 499 km (310 mi). Inclination: 82.6000 deg. Period: 115.00 min. US participation; particles and fields experiments; deployed Magion 2. Comprehensive study of the processes of propagation of low-frequency electromagnetic waves in the earth's magnetosphere and their interaction with charged particles of the radiation belts, in cooperation with Bulgaria, Czechoslovakia, the German Democrati c Republic, Hungary, Poland and Romania (the international scientific project entitled 'Aktivny'). Carrying the Czechoslovak Magion-2 satellite.
  • Magion 2 - . Payload: S2-AK. Mass: 50 kg (110 lb). Nation: Czech Republic. Agency: UNKS. Program: Intercosmos. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Magion. USAF Sat Cat: 20281 . COSPAR: 1989-080B. Apogee: 2,441 km (1,516 mi). Perigee: 498 km (309 mi). Inclination: 82.6000 deg. Period: 115.30 min. Deployed from Intercosmos 24 10/3/89; examined signal propogation from Intercosmos 24. Research of the magnetosphere and the ionosphere of the Earth. The Czechoslovak satellite Magion 2 was launched into orbit by the Soviet spacecraft Intercosmos 24. Magion 2 forms a part of the scientific programme of Intercosmos 24 (project Aktivnyj) Exe cution of the scientific programme of the 'Aktivny' project in conjunction with Intercosmos-24, permitting simultaneous spatially separating investigations of plasma processes in circumterrestrial space.

1989 September 28 - . 17:05 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC200/40. LV Family: Proton. Launch Vehicle: Proton-K/DM-2. LV Configuration: Proton-K/DM-2 346-01.
  • Gorizont 19 - . Payload: Gorizont s/n 31L. Mass: 2,120 kg (4,670 lb). Nation: USSR. Agency: MOM. Class: Communications. Type: Civilian communications satellite. Spacecraft: Gorizont . Completed Operations Date: 1998-05-05 . USAF Sat Cat: 20263 . COSPAR: 1989-081A. Apogee: 35,827 km (22,261 mi). Perigee: 35,793 km (22,240 mi). Inclination: 7.9000 deg. Period: 1,437.30 min. Stationed at 97.5 deg E. Operation of the long-range telephone and telegraph radio-communications system and transmission of television programmes. Positioned in geosynchronous orbit at 97 deg E in 1989-1996; 34 deg E in 1996-1998 As of 4 September 2001 located at 105.39 deg E drifting at 0.168 deg E per day. As of 2007 Feb 28 located at 84.84E drifting at 0.295W degrees per day.

1990 September 28 - . 07:30 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32. Launch Pad: LC32/pad?. LV Family: Tsiklon. Launch Vehicle: Tsiklon-3.
  • Meteor 2-20 - . Payload: Meteor-2 s/n 25. Mass: 2,750 kg (6,060 lb). Nation: USSR. Agency: MO. Class: Earth. Type: Weather satellite. Spacecraft: Meteor-2. USAF Sat Cat: 20826 . COSPAR: 1990-086A. Apogee: 961 km (597 mi). Perigee: 939 km (583 mi). Inclination: 82.5000 deg. Period: 104.10 min. Summary: Gathering round-the-clock meteorological information..

1991 September 28 - . 07:05 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC32. Launch Pad: LC32/pad?. LV Family: Tsiklon. Launch Vehicle: Tsiklon-3.
  • Cosmos 2157 - . Payload: Strela-3 no. 59. 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: 21728 . COSPAR: 1991-068A. Apogee: 1,413 km (877 mi). Perigee: 1,408 km (874 mi). Inclination: 82.6000 deg. Period: 114.00 min. Summary: Eight satellites launched by a single carrier rocket..
  • Cosmos 2160 - . Payload: Strela-3 no. 62. 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: 21731 . COSPAR: 1991-068D. Apogee: 1,411 km (876 mi). Perigee: 1,398 km (868 mi). Inclination: 82.6000 deg. Period: 113.90 min.
  • Cosmos 2161 - . Payload: Strela-3 no. 63. 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: 21732 . COSPAR: 1991-068E. Apogee: 1,411 km (876 mi). Perigee: 1,394 km (866 mi). Inclination: 82.6000 deg. Period: 113.80 min.
  • Cosmos 2162 - . Payload: Strela-3 no. 64. 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: 21733 . COSPAR: 1991-068F. Apogee: 1,418 km (881 mi). Perigee: 1,409 km (875 mi). Inclination: 82.6000 deg. Period: 114.10 min.
  • Cosmos 2158 - . Payload: Strela-3 no. 60. 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: 21729 . COSPAR: 1991-068B. Apogee: 1,411 km (876 mi). Perigee: 1,404 km (872 mi). Inclination: 82.6000 deg. Period: 113.90 min.
  • Cosmos 2159 - . Payload: Strela-3 no. 61. 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: 21730 . COSPAR: 1991-068C. Apogee: 1,410 km (870 mi). Perigee: 1,388 km (862 mi). Inclination: 82.6000 deg. Period: 113.80 min.

1992 September 28 - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF26. Launch Pad: LF26?. LV Family: Minuteman. Launch Vehicle: Minuteman 3.
  • FOT GT149GB Follow-on Test launch - . Nation: USA. Agency: USAF ACC. Apogee: 1,300 km (800 mi).

1993 September 28 - . 00:57 GMT - .
  • EVA Mir EO-14-3 - . Crew: Tsibliyev; Serebrov. EVA Type: Extra-Vehicular Activity. EVA Duration: 0.0778 days. Nation: Russia. Related Persons: Tsibliyev; Serebrov. Program: Mir. Class: Manned. Type: Manned space station. Flight: Mir EO-14. Spacecraft: Mir. Summary: Installed material samples and retrieved experiment packages. Documented external condition of Mir..

1994 September 28 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R901.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1998 September 28 - . 15:11 GMT - . Launch Site: Sriharikota. LV Family: RH. Launch Vehicle: RH-560/300 Mk II.
  • DEOS F06 Ionosphere mission - . Nation: India. Agency: ISRO; DLR. Apogee: 422 km (262 mi).

1998 September 28 - . 23:41 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC43/3. LV Family: R-7. Launch Vehicle: Molniya 8K78M. LV Configuration: Molniya 8K78M-ML.
  • Molniya-1T - . Payload: Molniya-1T. Nation: Russia. Agency: MOM. Manufacturer: Reshetnev. Program: Molniya. Class: Communications. Type: Military communications satellite. Spacecraft: Molniya-1T. USAF Sat Cat: 25485 . COSPAR: 1998-054A. Apogee: 38,755 km (24,081 mi). Perigee: 1,599 km (993 mi). Inclination: 63.3000 deg. Period: 717.80 min.

1999 September 28 - . 11:00 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC43/4. LV Family: R-7. Launch Vehicle: Soyuz 11A511U.
  • Resurs F-1M - . Nation: Russia. Agency: RAKA. Manufacturer: Kozlov. Program: Resurs. Class: Earth. Type: Earth resources satellite. Spacecraft: Resurs F1M. Duration: 24.00 days. Decay Date: 1999-10-22 . USAF Sat Cat: 25929 . COSPAR: 1999-054A. Apogee: 240 km (140 mi). Perigee: 214 km (132 mi). Inclination: 82.3000 deg. Period: 89.00 min. Summary: Remote sensing film satellite. Recovered in Russia on October 22, 1999..

2000 September 28 - . 08:01 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF09. Launch Pad: LF09?. LV Family: Minuteman. Launch Vehicle: Minuteman 3. LV Configuration: Minuteman 3 GT174GM.
  • SHARP operational test launch - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,300 km (800 mi). Summary: RCT-2 FOT, 20 decoys.

2000 September 28 - . 10:01 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF04. LV Family: Minuteman. Launch Vehicle: Minuteman 3. LV Configuration: Minuteman 3 GT173GM.
  • RCT-2 FOT, 20 decoys/Target missile - . Nation: USA. Agency: USAF AFSPC. Apogee: 1,300 km (800 mi).

2002 September 28 - .
  • Black Armadillo test. - . Nation: USA. Program: X-Prize. Spacecraft: Black Armadillo. Summary: Armadillo Aerospace (Mesquite, Texas, USA) successfully flight tests manned lander vehicle..

2006 September 28 - .
2007 September 28 - . 20:16 GMT - . Launch Site: Vandenberg. Launch Complex: Vandenberg LF23. Launch Pad: LF23?. Launch Vehicle: OBV. LV Configuration: OBV 6.
  • FTG-03a - . Nation: USA. Agency: OSC; MDA. Apogee: 1,000 km (600 mi).

2009 September 28 - .
  • Death of Nikolai Stepanovich Porvatkin at Zvyozdny Gorodok, Russia - . Nation: Russia. Related Persons: Porvatkin. Summary: Russian engineer cosmonaut, 1967-1983. Graduated from Technical Air Force School, 1952. Graduated from Zhukovsky Air Force Engineering Academy, Monino, 1960. Cosmonaut training May 1967 - 18 August 1967. Worked at NPO Energia..

2009 September 28 - . LV Family: Shahab. Launch Vehicle: Shahab 3.
  • Shahab RV - . Mass: 500 kg (1,100 lb). Nation: Iran. Summary: Operational test.

2009 September 28 - . LV Family: Seijil. Launch Vehicle: Seijil.
  • Sejjil RV - . Mass: 800 kg (1,760 lb). Nation: Iran. Summary: Operational test.

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