| Baikonur LC31 |
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LC31 Chronology 1961 January 14 - 01:19 GMT - Launch Vehicle: Soyuz. R-7A II-1 operational test launch Agency: RVSN. Apogee: 1,350 km (830 mi). Some sources say first launch from LC31 was not until 27 February. 1961 February 13 - 04:39 GMT - Launch Vehicle: Soyuz. R-7A L1-3T R-7A II-2 operational test launch Agency: RVSN. Apogee: 1,350 km (830 mi). Some sources say first launch from LC31 was not until 27 February. 1961 February 27 - 00:52 GMT - Launch Vehicle: Soyuz. R-7 L2-1 Operational missile test Agency: RVSN. Apogee: 1,350 km (830 mi). 1961 April 14 - Launch Vehicle: Soyuz. FAILURE: Failure. R-7A II-3 test Agency: RVSN. Apogee: 0 km ( mi). Failure occurred only two days after Yuri Gagarin's flight. 1961 June 15 - 05:45 GMT - Launch Vehicle: Soyuz. R-7A E15001-06 R-7A II-4 test Agency: RVSN. Apogee: 1,350 km (830 mi). 1961 July 4 - 04:00 GMT - Launch Vehicle: Soyuz. R-7A L2-4 R-7A II-5 test Agency: RVSN. Apogee: 1,350 km (830 mi). 1961 July 4 - 20:20 GMT - Launch Vehicle: Soyuz. R-7A L2-2 R-7A II-6 test Agency: RVSN. Apogee: 1,350 km (830 mi). Two launches from one launch complex in the same day. 1961 September 21 - Launch Vehicle: Soyuz. R-7A E15003-03 R-7A II-7 test Agency: RVSN. Apogee: 1,350 km (830 mi). R-7A readiness verification test. 1961 November 29 - Launch Vehicle: Soyuz. Operational test Agency: RVSN. Apogee: 1,350 km (830 mi). 1962 July 2 - Launch Vehicle: Soyuz. Operational test Agency: RVSN. Apogee: 1,350 km (830 mi). 1963 April 22 - Launch Vehicle: Soyuz. Combat training launch Agency: RVSN. Apogee: 1,350 km (830 mi). 1963 May 18 - Launch Vehicle: Soyuz. Combat training launch Agency: RVSN. Apogee: 1,350 km (830 mi). 1963 October 14 - Launch Vehicle: Soyuz. Combat training launch Agency: RVSN. Apogee: 1,350 km (830 mi). 1963 November 1 - 08:56 GMT - Launch Vehicle: Soyuz. Sputnik 11A59 E15003-02A Polet 1; Polyot 1 Mass: 1,400 kg (3,000 lb). Spacecraft: Polyot. Agency: NII-88. Perigee: 331 km (205 mi). Apogee: 1,420 km (880 mi). Inclination: 58.90 deg. Period: 102.40 min. ASAT interceptor control and propulsion test. Launched by Korolev R-7 because Chelomei's own UR-200 was not yet available. Purpose - elaboration of system providing for the extensive manoeuvring of space apparatuses. Flight was considered a great success. Micro-engine fired 350 times and main stabilizing engine fired 300 times. Orbit given is final orbit after manoeuvres. 1964 April 4 - 09:36 GMT - Launch Vehicle: Soyuz. Vostok 8A92 G15001-04 Cosmos 28 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 213 km (132 mi). Apogee: 373 km (231 mi). Inclination: 65.00 deg. Period: 90.40 min. Area survey photo reconnaissance satellite. 1964 April 12 - 09:21 GMT - Launch Vehicle: Soyuz. Sputnik 11A59 T15001-01A Polet 2; Polyot 2 Mass: 1,400 kg (3,000 lb). Spacecraft: Polyot. Agency: NII-88. Perigee: 303 km (188 mi). Apogee: 479 km (297 mi). Inclination: 58.10 deg. Period: 92.30 min. ASAT interceptor control and propulsion test. Elaboration of systems providing for the extensive manouevring of space apparatuses. 1964 April 25 - 10:19 GMT - Launch Vehicle: Soyuz. Vostok 8A92 R15001-01 Cosmos 29 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 203 km (126 mi). Apogee: 292 km (181 mi). Inclination: 65.00 deg. Period: 89.50 min. Area survey photo reconnaissance satellite. 1964 June 3 - Launch Vehicle: Soyuz. Test? Agency: RVSN. Apogee: 1,350 km (830 mi). 1964 June 10 - 10:48 GMT - Launch Vehicle: Soyuz. Vostok 8A92 R15001-02 Cosmos 32 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 205 km (127 mi). Apogee: 322 km (200 mi). Inclination: 51.30 deg. Period: 89.80 min. Area survey photo reconnaissance satellite. 1964 June 23 - 10:19 GMT - Launch Vehicle: Soyuz. Vostok 8A92 G15001-05 Cosmos 33 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 205 km (127 mi). Apogee: 279 km (173 mi). Inclination: 64.90 deg. Period: 89.40 min. Area survey photo reconnaissance satellite. 1964 July 15 - 11:31 GMT - Launch Vehicle: Soyuz. Vostok 8A92 R15001-03 Cosmos 35 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 218 km (135 mi). Apogee: 258 km (160 mi). Inclination: 51.30 deg. Period: 89.20 min. Area survey photo reconnaissance satellite. 1964 July 27 - Launch Vehicle: Soyuz. Test? Agency: RVSN. Apogee: 1,350 km (830 mi). 1964 August 14 - 09:36 GMT - Launch Vehicle: Soyuz. Vostok 8A92 R15001-04 Cosmos 37 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 208 km (129 mi). Apogee: 240 km (140 mi). Inclination: 64.90 deg. Period: 88.90 min. Area survey photo reconnaissance satellite. Program partially completed. Break in the film fof the SA-10 camera. 1964 August 28 - 16:19 GMT - Launch Vehicle: Soyuz. Vostok 8A92M T15000-05 Cosmos 44 Mass: 4,730 kg (10,420 lb). Spacecraft: Meteor. Agency: NII-88. Perigee: 599 km (372 mi). Apogee: 778 km (483 mi). Inclination: 65.10 deg. Period: 98.50 min. Investigation of the upper atmosphere and outer space. 1964 September 24 - 12:00 GMT - Launch Vehicle: Soyuz. Vostok 8A92 R15001-05 Cosmos 46 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 211 km (131 mi). Apogee: 264 km (164 mi). Inclination: 51.30 deg. Period: 89.20 min. Area survey photo reconnaissance satellite. Demonstration launch witnessed by Khrushchev. 1964 October 14 - 09:50 GMT - Launch Vehicle: Soyuz. Vostok 8A92 R15002-01 Cosmos 48 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 204 km (126 mi). Apogee: 284 km (176 mi). Inclination: 65.10 deg. Period: 89.30 min. Area survey photo reconnaissance satellite. Program partially completed. Returned early due to failure of spacecraft thermoregulation system; internal temperature rose to 43 degrees C. 1964 October 28 - 10:48 GMT - Launch Vehicle: Soyuz. Vostok 8A92 R15002-02 Cosmos 50 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 190 km (110 mi). Apogee: 232 km (144 mi). Inclination: 51.20 deg. Period: 88.70 min. Area survey photo reconnaissance satellite. Unsuccessful mission. Failure of the braking engine system. Spacecraft ordered to self destruct. 1965 January 11 - 09:36 GMT - Launch Vehicle: Soyuz. Vostok 8A92 R15002-03 Cosmos 52 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 203 km (126 mi). Apogee: 298 km (185 mi). Inclination: 65.00 deg. Period: 89.50 min. Area survey photo reconnaissance satellite. 1965 February 22 - 07:40 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 R15000-03 Cosmos 57 Mass: 5,682 kg (12,526 lb). Spacecraft: Voskhod. Agency: NII-88. Perigee: 159 km (98 mi). Apogee: 708 km (439 mi). Inclination: 64.80 deg. Period: 93.20 min. Flight: Voskhod 2. Unsuccessful mission. Voskhod 2 test. Immediately after orbital insertion airlock and spacesuit inflated normally. Then two ground control stations sent commands to the spacecraft simultaneously. The combined signals accidentally set off the retrofire sequence, which some time later triggered the self destruct mechanism (designed to prevent the spacecraft from falling into enemy hands). 1965 February 26 - 05:02 GMT - Launch Vehicle: Soyuz. Vostok 8A92M R15000-09 Cosmos 58 Mass: 4,730 kg (10,420 lb). Spacecraft: Meteor. Agency: NII-88. Perigee: 333 km (206 mi). Apogee: 345 km (214 mi). Inclination: 65.00 deg. Period: 91.30 min. Probable weather satellite. Investigation of the upper atmosphere and outer space. 1965 March 7 - 09:07 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 R15001-05 Cosmos 59 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 321 km (199 mi). Inclination: 64.90 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule fitted with airlock mating ring planned for Voskhod-2 spacecraft. 1965 March 25 - 10:04 GMT - Launch Vehicle: Soyuz. Vostok 8A92 G15001-06 Cosmos 64 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 250 km (150 mi). Inclination: 65.00 deg. Period: 89.10 min. Area survey photo reconnaissance satellite. 1965 April 17 - 09:50 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 G15000-11 Cosmos 65 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 315 km (195 mi). Inclination: 65.00 deg. Period: 89.70 min. High resolution photo reconnaissance satellite; returned film capsule; also carried weather experiments. 1965 May 7 - 09:50 GMT - Launch Vehicle: Soyuz. Vostok 8A92 R15002-04 Cosmos 66 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 285 km (177 mi). Apogee: 397 km (246 mi). Inclination: 64.90 deg. Period: 91.30 min. Returned after 8 days. Unsuccessful mission. Parachute deployment failure. Spacecraft destroyed in crash. 1965 May 25 - 10:48 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 R15001-04 Cosmos 67 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 351 km (218 mi). Inclination: 51.80 deg. Period: 90.10 min. High resolution photo reconnaissance satellite; returned film capsule 1965 June 15 - 10:04 GMT - Launch Vehicle: Soyuz. Vostok 8A92 U15001-01 Cosmos 68 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 208 km (129 mi). Apogee: 306 km (190 mi). Inclination: 65.00 deg. Period: 89.70 min. Area survey photo reconnaissance satellite. 1965 July 13 - Launch Vehicle: Soyuz. Vostok 8A92 R15002-05 FAILURE: Second stage guidance failure. Zenit-2 11F61 s/n 28 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: RVSN. Area survey photo reconnaissance satellite. 1965 August 3 - 11:02 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 U15001-01 Cosmos 77 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 200 km (120 mi). Apogee: 281 km (174 mi). Inclination: 51.80 deg. Period: 89.30 min. High resolution photo reconnaissance satellite; returned film capsule 1965 August 14 - 11:16 GMT - Launch Vehicle: Soyuz. Vostok 8A92 U15001-02 Cosmos 78 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 330 km (200 mi). Apogee: 379 km (235 mi). Inclination: 69.00 deg. Period: 91.60 min. Area survey photo reconnaissance satellite. 1965 September 9 - 09:36 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 R15001-02 Cosmos 85 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 291 km (180 mi). Inclination: 64.90 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule 1965 September 23 - 09:07 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 R15001-03 Cosmos 91 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 324 km (201 mi). Inclination: 65.00 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule 1965 October 16 - 08:09 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 U15001-04 Cosmos 92 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 331 km (205 mi). Inclination: 64.90 deg. Period: 89.90 min. High resolution photo reconnaissance satellite; returned film capsule; also carried weather and biological experiments. 1965 October 28 - 08:24 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 U15001-03 Cosmos 94 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 271 km (168 mi). Inclination: 65.00 deg. Period: 89.20 min. High resolution photo reconnaissance satellite; returned film capsule; also carried biological experiments. 1965 November 12 - 05:02 GMT - Launch Vehicle: Soyuz. Venera 2 Mass: 962 kg (2,120 lb). Spacecraft: Venera 3MV-4. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 315 km (195 mi). Inclination: 51.80 deg. Period: 89.71 min. Venera 2 was launched towards the planet Venus and carried a TV system and scientific instruments. On February 27, 1966, the spacecraft passed Venus at a distance of 24,000 km and entered a heliocentric orbit. The spacecraft system had ceased to operate before the planet was reached and returned no data. 1965 November 16 - 04:19 GMT - Launch Vehicle: Soyuz. Venera 3 Mass: 958 kg (2,112 lb). Spacecraft: Venera 3MV-3. Agency: MOM. Venera 3 was launched towards the planet Venus. The mission was to land on the Venusian surface. The entry vehicle contained a radio communication system, scientific instruments, electrical power sources, and medallions bearing the coat of arms of the U.S.S.R. The station impacted Venus on March 1, 1966. However, the communications systems had failed before planetary data could be returned. 1965 November 23 - 03:21 GMT - Launch Vehicle: Soyuz. FAILURE: At T+528 sec, during the final thrust phase of the Block I's 8D715K engine, one of the combustion chambers blew up due to a tear in the fuel pipeline. This resulted in an abnormal separation of the upper stages. Cosmos 96 Mass: 960 kg (2,110 lb). Spacecraft: Venera 3MV-4. Agency: MOM. Perigee: 222 km (137 mi). Apogee: 296 km (183 mi). Inclination: 51.90 deg. Period: 89.70 min. The escape stage Block L entered parking orbit tumbling and was not able to operate properly. 1965 November 27 - 08:24 GMT - Launch Vehicle: Soyuz. Vostok 8A92 U15001-05 Cosmos 98 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 547 km (339 mi). Inclination: 65.00 deg. Period: 92.10 min. Area survey photo reconnaissance satellite. 1965 December 3 - 10:46 GMT - Launch Vehicle: Soyuz. Molniya 8K78 U103-28 Luna 8 Mass: 1,550 kg (3,410 lb). Spacecraft: Luna E-6. Agency: MOM. Lunar soft landing attempt failed. Luna 8's objectives were to test a soft lunar landing system and scientific research. Weighing 1,552 kg (3,422 lbs), the spacecraft was following a trajectory close to the calculated one and the equipment was functioning normally. However, the retrofire was late, and the spacecraft impacted the lunar surface in the Sea of Storms. Tass reported that "the systems were functioning normally at all stages of the landing except the final touchdown." The mission did complete the experimental development of the star-orientation system and ground control of radio equipment, flight trajectory, and other instrumentation. 1965 December 10 - 08:09 GMT - Launch Vehicle: Soyuz. Vostok 8A92 U15001-04 Cosmos 99 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 309 km (192 mi). Inclination: 65.00 deg. Period: 89.60 min. Area survey photo reconnaissance satellite. 1965 December 17 - 02:24 GMT - Launch Vehicle: Soyuz. Vostok 8A92M R15000-31 Cosmos 100 Mass: 4,730 kg (10,420 lb). Spacecraft: Meteor. Agency: MOM. Perigee: 485 km (301 mi). Apogee: 547 km (339 mi). Inclination: 65.00 deg. Period: 95.00 min. Probable weather satellite. Investigation of the upper atmosphere and outer space. 1965 December 27 - 22:19 GMT - Launch Vehicle: Soyuz. LV Model: Vostok 11A510 . Soyuz 11A510 G15000-01 Cosmos 102 Mass: 3,800 kg (8,300 lb). Spacecraft: US-A. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 267 km (165 mi). Inclination: 64.90 deg. Period: 89.20 min. Prototype RORSAT hardware using chemical batteries in place of nuclear reactor. 1966 January 7 - 08:24 GMT - Launch Vehicle: Soyuz. Cosmos 104 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 195 km (121 mi). Apogee: 379 km (235 mi). Inclination: 65.00 deg. Period: 90.20 min. Area survey photo reconnaissance satellite. Program not completely met. Spacecraft put into incorrect orbit by abnormal function of second and third stages of booster. 1966 January 22 - 08:38 GMT - Launch Vehicle: Soyuz. Cosmos 105 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 311 km (193 mi). Inclination: 65.00 deg. Period: 89.60 min. Area survey photo reconnaissance satellite. 1966 January 31 - 11:41 GMT - Launch Vehicle: Soyuz. Molniya 8K78M U103-32 Luna 9 Mass: 1,580 kg (3,480 lb). Spacecraft: Luna E-6. Agency: MOM. Soft landed on Moon; photographed surface for 3 days. Landed on Moon 3 February 1966 at 18:44:52 GMT, Latitude 7.08 N, Longitude 295.63 E - Oceanus Procellarum. The Luna 9 spacecraft was the first spacecraft to achieve a lunar soft landing and to transmit photographic data to Earth. Seven radio sessions, totaling 8 hours and 5 minutes, were transmitted as were three series of TV pictures. When assembled, the photographs provided a panoramic view of the nearby lunar surface. The pictures included views of nearby rocks and of the horizon 1.4 Km away from the spacecraft. 1966 February 10 - 08:52 GMT - Launch Vehicle: Soyuz. Cosmos 107 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 216 km (134 mi). Apogee: 313 km (194 mi). Inclination: 65.00 deg. Period: 89.70 min. Area survey photo reconnaissance satellite. 1966 February 19 - 08:52 GMT - Launch Vehicle: Soyuz. Cosmos 109 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 288 km (178 mi). Inclination: 64.90 deg. Period: 89.40 min. High resolution photo reconnaissance satellite; returned film capsule; also carried biological experiments. 1966 February 22 - 20:09 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 R15000-06 Cosmos 110 Mass: 5,700 kg (12,500 lb). Spacecraft: Voskhod. Agency: MOM. Perigee: 181 km (112 mi). Apogee: 887 km (551 mi). Inclination: 51.80 deg. Period: 95.30 min. Flight: Voskhod 3. Successfully recovered March 15, 1966 13:00 GMT. Precursor mission for Voskhod 3 hardware. Two dogs carried into lower Van Allen radiation belts. Voskhod s/n 5 launched at 23:10 Moscow time, with two dogs, Veterka and Ygolka, aboard. This will be a 25-day mission. Kamanin is disgusted, he had proposed this as a 25-day mission by a single cosmonaut, but Korolev had constantly held with the 'dog variant'. Preparations for Voskhod-3 are proceeding well. The prime and back-up crews have completed their training and will take their examinations on 28 February. Parallel trials of the oxygen regeneration system at IMBP and OKB-124 both went well (IMBP, 12 days so far, temperature 16-24 deg C, 70% humidity; OKB-124, 10 days so far, temperature 18-16 deg C, 65% humidity). 1966 March 1 - 11:03 GMT - Launch Vehicle: Soyuz. Molniya 8K78M N103-41 FAILURE: The escape stage Block L lost roll control during unpowered coast in parking orbit because the axis of the course regulator of the control system jammed in the zero position. The stage's engine was not fired. Cosmos 111 Mass: 6,540 kg (14,410 lb). Spacecraft: Luna E-6S. Agency: NII-88. Perigee: 168 km (104 mi). Apogee: 180 km (110 mi). Inclination: 51.80 deg. Period: 88.00 min. 1966 March 21 - 09:36 GMT - Launch Vehicle: Soyuz. Cosmos 113 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 314 km (195 mi). Inclination: 64.90 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule 1966 March 27 - Launch Vehicle: Soyuz. Molniya 8K78M N103-38 FAILURE: The booster failed during ascent. The launcher and payload broke up on impact with the ground. Molniya-1 s/n 5 Failure Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: RVSN. 1966 March 31 - 10:47 GMT - Launch Vehicle: Soyuz. Molniya 8K78M N103-42 Luna 10 Mass: 1,597 kg (3,520 lb). Spacecraft: Luna E-6S. Agency: NII-88. Lunar Orbit (Selenocentric). Development of system to permit the creation of an artificial lunar satellite for the investigation of circumlunar space; development of onboard systems for putting a station into a selenocentric (circumlunar) orbit. Orbit: Lunar Orbiter. The Luna 10 spacecraft was launched towards the Moon from an Earth orbiting platform. The spacecraft entered lunar orbit 3 50 x 1017 km, inclination 71.9 deg to plane of the lunar equator. on April 4, 1966. Scientific instruments included a gamma-ray spectrometer for energies between 0.3--3 MeV, a triaxial magnetometer, a meteorite detector, instruments for solar-plasma studies, and devices for measuring infrared emissions from the Moon and radiation conditions of the lunar environment. Gravitational studies were also conducted. The spacecraft played back to Earth the `Internationale' during the Twenty-third Congress of the Communist Party of the Soviet Union. Luna 10 was battery powered and operated for 460 lunar orbits and 219 active data transmissions before radio signals were discontinued on May 30, 1966. 1966 April 20 - 10:48 GMT - Launch Vehicle: Soyuz. Cosmos 115 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 189 km (117 mi). Apogee: 283 km (175 mi). Inclination: 65.00 deg. Period: 89.20 min. . Program partially completed. Abnormal operation of SA-10 camera. 1966 April 25 - 07:12 GMT - Launch Vehicle: Soyuz. Molniya 8K78M N103-39 Molniya 1-03 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 546 km (339 mi). Apogee: 39,414 km (24,490 mi). Inclination: 65.00 deg. Period: 709.80 min. Also transmitted cloud cover images. Television programme transmission and long-range two-way multi-channel telephone, phototelegraph and telegraph communicaitons. 1966 May 6 - 11:02 GMT - Launch Vehicle: Soyuz. Vostok 8A92 N15001-01 Cosmos 117 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 200 km (120 mi). Apogee: 314 km (195 mi). Inclination: 64.90 deg. Period: 89.60 min. Area survey photo reconnaissance satellite. 1966 May 11 - 14:09 GMT - Launch Vehicle: Soyuz. Cosmos 118 Mass: 4,730 kg (10,420 lb). Spacecraft: Meteor. Agency: MOM. Perigee: 316 km (196 mi). Apogee: 339 km (210 mi). Inclination: 65.00 deg. Period: 91.10 min. Probable weather satellite. Investigation of the upper atmosphere and outer space. 1966 June 8 - 11:02 GMT - Launch Vehicle: Soyuz. Cosmos 120 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 201 km (124 mi). Apogee: 331 km (205 mi). Inclination: 51.70 deg. Period: 89.80 min. Area survey photo reconnaissance satellite. 1966 June 25 - 10:30 GMT - Launch Vehicle: Soyuz. Vostok 8A92M N15000-21 Cosmos 122 Mass: 4,730 kg (10,420 lb). Spacecraft: Meteor. Agency: MOM. Perigee: 371 km (230 mi). Apogee: 388 km (241 mi). Inclination: 65.00 deg. Period: 92.10 min. Investigation of the upper atmosphere and outer space. 1966 July 14 - 10:33 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 N15001-14 Cosmos 124 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 282 km (175 mi). Inclination: 51.80 deg. Period: 89.40 min. Area survey photo reconnaissance satellite. 1966 July 20 - 09:07 GMT - Launch Vehicle: Soyuz. LV Model: Vostok 11A510 . Soyuz 11A510 G15000-02 Cosmos 125 Mass: 3,800 kg (8,300 lb). Spacecraft: US-A. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 260 km (160 mi). Inclination: 64.90 deg. Period: 89.10 min. Prototype RORSAT hardware using chemical batteries in place of nuclear reactor. Lost on the 52nd revolution as a result of a possible failure in the chemical power units placed on board instead of the nuclear BES-5. 1966 July 28 - 10:48 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 N15001-01 Cosmos 126 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 209 km (129 mi). Apogee: 343 km (213 mi). Inclination: 51.80 deg. Period: 90.10 min. High resolution photo reconnaissance satellite; returned film capsule 1966 August 8 - 11:16 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 N15001-13 Cosmos 127 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 201 km (124 mi). Apogee: 263 km (163 mi). Inclination: 51.80 deg. Period: 89.10 min. High resolution photo reconnaissance satellite; returned film capsule 1966 August 24 - 08:03 GMT - Launch Vehicle: Soyuz. Molniya 8K78M N103-43 Luna 11 Mass: 1,638 kg (3,611 lb). Spacecraft: Luna E-6LF. Agency: MOM. Automatic station Luna 11. Further development of artificial lunar satellite systems and conduct of scientific experiments in circumlunar space. Lunar orbit 160 km x 1200 km x 27 degrees. Luna 11 was launched towards the Moon from an earth-orbiting platform and entered lunar orbit on August 28, 1966. The objectives of the mission included the study of: (1) lunar gamma- and X-ray emissions in order to determine the Moon's chemical composition; (2) lunar gravitational anomalies; (3) the concentration of meteorite streams near the Moon; and, (4) the intensity of hard corpuscular radiation near the Moon. A total of 137 radio transmissions and 277 orbits of the Moon were completed before the batteries failed on October 1, 1966. 1966 September 16 - Launch Vehicle: Soyuz. FAILURE: Launch vehicle destroyed. Failure of Block D core stage. Zenit-2 11F61 s/n 40 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: RVSN. Area survey photo reconnaissance satellite. 1966 October 20 - 08:52 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 N15001-04 Cosmos 130 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 316 km (196 mi). Inclination: 64.90 deg. Period: 89.70 min. High resolution photo reconnaissance satellite; returned film capsule 1966 October 22 - 08:42 GMT - Launch Vehicle: Soyuz. Molniya 8K78M N103-44 Luna 12 Mass: 1,620 kg (3,570 lb). Spacecraft: Luna E-6LF. Agency: MOM. Lunar Orbiter, further development of artificial lunar satellite systems and conduct of scientific experiments in circumlunar space. Luna 12 was launched towards the Moon from an earth-orbiting platform and achieved a lunar orbit of of 100 km x 1740 km on October 25, 1966. The spacecraft was equipped with a television system that obtained and transmitted photographs of the lunar surface. The photographs contained 1100 scan lines with a maximum resolution of 14.9--19.8 m. Pictures of the lunar surface were returned on October 27, 1966. The number of photographs is not known. Radio transmissions from Luna 12 ceased on January 19, 1967, after 602 lunar orbits and 302 radio transmissions. 1966 November 19 - 08:09 GMT - Launch Vehicle: Soyuz. Vostok 8A92 N15001-08 Cosmos 132 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 257 km (159 mi). Inclination: 65.00 deg. Period: 89.10 min. Area survey photo reconnaissance satellite. 1966 November 28 - 11:00 GMT - Launch Vehicle: Soyuz. Soyuz 11A511 U15000-02 Cosmos 133 Mass: 6,450 kg (14,210 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 219 km (136 mi). Inclination: 51.80 deg. Period: 88.40 min. First test flight of Soyuz 7K-OK earth orbit spacecraft. A planned 'all up' test, with a second Soyuz to be launched the following day and automatically dock with Kosmos 133. This was to be followed by a manned link-up in December 1966. However Kosmos 133's attitude control system malfunctioned, resulting in rapid consumption of orientation fuel, leaving it spinning at 2 rpm. After heroic efforts by ground control and five attempts at retrofire over two days, the craft was finally brought down for a landing on its 33rd revolution. However due to the inaccuracy of the reentry burn, it was determined that the capsule would land in China. The APO self destruct system detected the course deviation and the destruct charge of several dozen kilogrammes of explosive was thought to have destroyed the ship on November 30, 1966 at 10:21 GMT. But stories persisted over the years of the Chinese having a Soyuz capsule in their possession.... 1966 December 3 - 08:09 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 N15001-06 Cosmos 134 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 286 km (177 mi). Inclination: 64.90 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule; also carried scientific experiments. 1966 December 14 - Launch Vehicle: Soyuz. Soyuz 11A511 U15000-01 FAILURE: Erroneous firing of launch escape tower ignited launch vehicle on the pad. Soyuz 7K-OK s/n 2 Spacecraft: Soyuz 7K-OK. Agency: RVSN. Second attempted flight of Soyuz 7K-OK (the spacecraft planned for the linkup with Ksomos 133). An analogue to Mercury Redstone's 'day we launched the tower' but with more disastorous consequences. The core stage ignited, but the strap-ons did not. A booster shutdown was commanded. The service towers were brought back around the booster, and ground crew began work to defuel the launch vehicle. At 27 minutes after the original launch attempt, the Soyuz launch escape system, having received the signal that liftoff had occurred, detected that the booster was not on course (either because a tower arm nudged the booster or because the earth's rotation as detected by the gyros had moved the spacecraft out of limits relative to its original inertial position). The launch escape system ignited, pulling the Soyuz away from the booster, igniting the third stage fuel tanks, leading to an explosion that severely damaged the pad and killed at least one person (the Soviet Rocket Forces major supervising the launch team) and injured many others. 1967 July 4 - 05:59 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 Ya15001-05 Cosmos 168 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 223 km (138 mi). Apogee: 230 km (140 mi). Inclination: 51.80 deg. Period: 89.10 min. Area survey photo reconnaissance satellite. 1967 July 21 - 06:00 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 Ya15001-14 FAILURE: Failure. Zenit-4 Spacecraft: Zenit-4. Agency: RVSN. High resolution photo reconnaissance mission. 1967 October 27 - 09:29 GMT - Launch Vehicle: Soyuz. Cosmos 186 Mass: 6,530 kg (14,390 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 179 km (111 mi). Apogee: 223 km (138 mi). Inclination: 51.60 deg. Period: 88.60 min. Docked with Cosmos 188; first automated rendezvous and docking of two spacecraft. The dockings were timed to celebrate the 50th Anniversary of the October Revolution (in lieu of a succession of manned space feats that all had to be cancelled due to schedule delays). Achieved automatic rendezvous on second attempt. Capture achieved but hard docking and electric connections unsuccessful due to misallignment of spacecraft. Star tracker failed and had to make a high-G ballistic re-entry. Recovered October 31, 1967 08:20 GMT. 1968 April 14 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 212 Mass: 6,500 kg (14,300 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 180 km (110 mi). Apogee: 200 km (120 mi). Inclination: 51.60 deg. Period: 88.30 min. Cosmos 212 docked with Cosmos 213 in the first completely successful test of the Soyuz 7K-OK attitude control, automatic rendezvous and docking systems. Cosmos 212 was successfully recovered on April 19, 1968 at 08:10 GMT. Additional Details: Cosmos 212(851). 1968 April 20 - 10:30 GMT - Launch Vehicle: Soyuz. Cosmos 216 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 198 km (123 mi). Apogee: 267 km (165 mi). Inclination: 51.00 deg. Period: 89.20 min. Area survey photo reconnaissance satellite. Unsuccessful mission. Spacecraft landed in River Volga 1 km from shore and sank after 42 minutes. 85% of the data was ruined. 1968 July 10 - 19:49 GMT - Launch Vehicle: Soyuz. Cosmos 231 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 311 km (193 mi). Inclination: 64.90 deg. Period: 89.60 min. Area survey photo reconnaissance satellite. 1968 August 9 - 07:00 GMT - Launch Vehicle: Soyuz. Cosmos 235 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 201 km (124 mi). Apogee: 281 km (174 mi). Inclination: 51.80 deg. Period: 89.30 min. Area survey photo reconnaissance satellite. Partially successful. Hard landing due to parachute sytem failure. 30% of the film damaged. 1968 August 28 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 238 Mass: 6,520 kg (14,370 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 210 km (130 mi). Inclination: 51.70 deg. Period: 88.60 min. Recovered September 1, 1968 9:03 GMT. Final test of redesigned Soyuz 7K-OK spacecraft for Soyuz 3 manned mission. 1968 September 14 - 06:50 GMT - Launch Vehicle: Soyuz. Cosmos 240 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 283 km (175 mi). Inclination: 51.80 deg. Period: 89.30 min. Area survey photo reconnaissance satellite. 1968 October 26 - 08:34 GMT - Launch Vehicle: Soyuz. Soyuz 3 Mass: 6,575 kg (14,495 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 183 km (113 mi). Apogee: 205 km (127 mi). Inclination: 51.70 deg. Period: 88.30 min. Crew: Beregovoi. Flight: Soyuz 3. Second manned Soyuz flight. Rendezvoused with the unmanned Soyuz 2 but failed to dock. Complex testing of spaceship systems; development, in joint flight with space ship Soyuz 2 of processes of space ship manoeuvring and docking in artificial earth satellite orbit; development of elements of celestial navigation; conduct of research under space flight conditions. The failed docking was blamed on manual control of the Soyuz by Beregovoi, who repeatedly put the spacecraft in an orientation that nulled the automatic docking system. Beregovoi used nearly all of his orientation fuel in his first attempt to dock - of 80 kg allocated, only 8 to 10 kg was remaining. Additional Details: Soyuz 3(930). 1968 December 10 - 08:25 GMT - Launch Vehicle: Soyuz. Cosmos 258 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 298 km (185 mi). Inclination: 65.00 deg. Period: 89.60 min. Area survey photo reconnaissance satellite. 1969 January 14 - 07:30 GMT - Launch Vehicle: Soyuz. Soyuz 4 Mass: 6,625 kg (14,605 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 213 km (132 mi). Apogee: 224 km (139 mi). Inclination: 51.70 deg. Period: 88.80 min. Crew: Shatalov. Flight: Soyuz 4, Soyuz 4/5. Soyuz 4 is launched with Vladimir Shatalov aboard without further problems at 10:30. This time the rockets gyroscopes, the capsule communications, and the television camera all functioned perfectly. Volynov and his crew for Soyuz 5 watched the launch from Area 17. Later Soyuz 4 would dock with Soyuz 5, and following a transfer of two cosmonauts, return with Shatalov, Yevgeni Khrunov and Alexsei Yeliseyev from Soyuz 5. Official purpose: scientific, technical and medico-biological research, checking and testing of onboard systems and design elements of space craft, docking of piloted space craft and construction of an experimental space station, transfer of cosmonauts from one craft to another in orbit. This mission finally successfully completed the simulated lunar orbit docking and crew transfer mission attempted by Soyuz 1 in April 1967. In making the transfer Khrunov and Yeliseyev avoided the most spectacular survivable incident of the space age - the nose-first reentry of Soyuz 5, still attached to its service module. 1969 June 24 - 06:50 GMT - Launch Vehicle: Soyuz. Cosmos 287 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 189 km (117 mi). Apogee: 265 km (164 mi). Inclination: 51.80 deg. Period: 89.00 min. Area survey photo reconnaissance satellite. 1969 August 16 - 11:59 GMT - Launch Vehicle: Soyuz. Cosmos 293 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 215 km (133 mi). Apogee: 244 km (151 mi). Inclination: 51.70 deg. Period: 89.10 min. Area survey photo reconnaissance satellite; returned film capsule; carried science package. 1969 October 11 - 11:10 GMT - Launch Vehicle: Soyuz. Soyuz 6 Mass: 6,577 kg (14,499 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 212 km (131 mi). Apogee: 218 km (135 mi). Inclination: 51.60 deg. Period: 88.80 min. Crew: Kubasov, Shonin. Flight: Soyuz 6, Soyuz 7, Soyuz 8. Tested spacecraft systems and designs, manoeuvring of space craft with respect to each other in orbit, conducted scientific, technical and medico-biological experiments in group flight. Carried Vulkan welding furnace for vacuum welding experiments in depressurized orbital module. Was to have taken spectacular motion pictures of Soyuz 7 - Soyuz 8 docking but failure of rendezvous electronics in all three craft due to new helium pressurization integrity test prior to mission did not permit successful rendezvous and dockings. Additional Details: Soyuz 6(1056). 1969 October 13 - 10:19 GMT - Launch Vehicle: Soyuz. Soyuz 8 Mass: 6,646 kg (14,651 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 201 km (124 mi). Apogee: 227 km (141 mi). Inclination: 51.70 deg. Period: 88.70 min. Crew: Shatalov, Yeliseyev. Flight: Soyuz 6, Soyuz 7, Soyuz 8. Tested spacecraft systems and designs, manoeuvring of space craft with respect to each other in orbit, conducted scientific, technical and medico-biological experiments in group flight. Was to have docked with Soyuz 7 and transferred crew while Soyuz 6 took film from nearby. However failure of rendezvous electronics in all three craft due to a new helium pressurization integrity test prior to the mission did not permit successful rendezvous and dockings. Recovered October 18, 1969 10:19 GMT. Additional Details: Soyuz 8(1058). 1970 June 1 - 19:00 GMT - Launch Vehicle: Soyuz. Soyuz 9 Mass: 6,590 kg (14,520 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 176 km (109 mi). Apogee: 227 km (141 mi). Inclination: 51.60 deg. Period: 88.50 min. Crew: Nikolayev, Sevastyanov. Flight: Soyuz 9. Manned flight endurance test. Medico-biological, scientific and technical studies and experiments in prolonged orbital flight. Inconclusive results due to slow sun-oriented rotation of spacecraft to conserve fuel producing motion sickness in cosmonauts. Additional Details: Soyuz 9(1140). 1970 August 22 - 05:06 GMT - Launch Vehicle: Soyuz. FAILURE: The escape stage Block L's engine 11D33 was late igniting and cut off early at 25 seconds after firing due to abnormal operation of the sequencer and a DC transformer failure. Cosmos 359 Mass: 1,180 kg (2,600 lb). Spacecraft: Venera 3V (V-70). Agency: MOM. Perigee: 195 km (121 mi). Apogee: 908 km (564 mi). Inclination: 51.20 deg. Period: 95.70 min. Probable Venus probe failure. 1970 August 29 - 08:30 GMT - Launch Vehicle: Soyuz. Cosmos 360 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 287 km (178 mi). Inclination: 65.00 deg. Period: 89.40 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable; deployed capsule. 1970 November 24 - 05:15 GMT - Launch Vehicle: Soyuz. Cosmos 379 Mass: 5,500 kg (12,100 lb). Spacecraft: LK. Agency: MOM. Perigee: 198 km (123 mi). Apogee: 232 km (144 mi). Inclination: 51.60 deg. Period: 88.70 min. LK moon lander test using the T2K version. First use of the Soyuz 11A511L booster modified especially for this purpose. The spacecraft made a series of engine burns, simulating the lunar landing profile. After 3.5 days in orbit, the first burn was made in imitation of a descent to the lunar surface after separation of the Block D lunar crasher stage. The orbit changed from 192 km X 233 km to 196 km X 1206 km orbit; delta V: 263 m/s. After 4 days in orbit, a large manoeuvre was made simulating the ascent from the lunar surface. The orbit was changed from 188 km X 1198 km to 177 km X 14,041 km; delta V: 1518 m/s. These main manoeuvres were followed by a series of small adjustments simulating rendezvous and docking with the LOK. The LK tested out without major problems and decayed from orbit on September 21, 1983. 1971 February 26 - 05:06 GMT - Launch Vehicle: Soyuz. Cosmos 398 Mass: 5,500 kg (12,100 lb). Spacecraft: LK. Agency: MOM. Perigee: 186 km (115 mi). Apogee: 1,958 km (1,216 mi). Inclination: 51.50 deg. Period: 106.70 min. Second space test of the LK moon lander test using the T2K version. Followed the same programme as Cosmos 379. 1971 August 12 - 05:30 GMT - Launch Vehicle: Soyuz. Cosmos 434 Mass: 5,500 kg (12,100 lb). Spacecraft: LK. Agency: MOM. Perigee: 193 km (119 mi). Apogee: 1,253 km (778 mi). Inclination: 51.60 deg. Period: 99.30 min. Final LK moon lander test using the T2K version. 1971 August 19 - Launch Vehicle: Soyuz. FAILURE: Failure. Zenit-4M Spacecraft: Zenit-4M. Agency: RVSN. High resolution photo reconnaissance mission. 1972 March 27 - 04:15 GMT - Launch Vehicle: Soyuz. Venera 8 Mass: 1,180 kg (2,600 lb). Spacecraft: Venera 3V (V-72). Agency: MOM. Perigee: 194 km (120 mi). Apogee: 246 km (152 mi). Inclination: 51.70 deg. Period: 88.90 min. Venus atmospheric probe. The spacecraft took 117 days to reach Venus, entering the atmosphere on 22 July 1972. Descent speed was reduced from 41,696 km/hr to about 900 km/hr by aerobraking. The 2.5 meter diameter parachute opened at an altitude of 60 km, and a refrigeration system was used to cool the interior components. Venera 8 transmitted data during the descent and continued to send back data for 50 minutes after landing. The probe confirmed the earlier data on the high Venus surface temperature and pressure returned by Venera 7, and also measured the light level as being suitable for surface photography, finding it to be similar to the amount of light on Earth on an overcast day. 1972 March 31 - 04:02 GMT - Launch Vehicle: Soyuz. FAILURE: The escape stage Block L's engine cut off 125 seconds after ignition due to timer failure. Cosmos 482 Mass: 1,180 kg (2,600 lb). Spacecraft: Venera 3V (V-72). Agency: MOM. Perigee: 204 km (126 mi). Apogee: 9,806 km (6,093 mi). Inclination: 52.00 deg. Period: 201.40 min. 1972 April 7 - 10:00 GMT - Launch Vehicle: Soyuz. Intercosmos 6 Mass: 6,000 kg (13,200 lb). Spacecraft: Energia. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 326 km (202 mi). Inclination: 51.80 deg. Period: 89.80 min. Investigation of primary cosmic radiation and meteoritic particles in near-earth outer space. 1972 April 14 - 00:54 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-SOL Prognoz 1 Mass: 845 kg (1,862 lb). Spacecraft: Prognoz. Agency: MOM. Perigee: 1,005 km (624 mi). Apogee: 199,667 km (124,067 mi). Inclination: 65.00 deg. Period: 5,782.10 min. Study of the processes of solar activity and of their influence on interplanetary space and the Earth's magnetosphere. 1972 June 29 - 03:47 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-SOL Prognoz 2 Mass: 845 kg (1,862 lb). Spacecraft: Prognoz. Agency: MOM. Perigee: 517 km (321 mi). Apogee: 201,804 km (125,394 mi). Inclination: 65.30 deg. Period: 5,849.20 min. Study of the processes of solar activity and of their influence on interplanetary space and the Earth's magnetosphere. 1973 February 15 - 01:11 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-SOL Prognoz 3 Mass: 845 kg (1,862 lb). Spacecraft: Prognoz. Agency: MOM. Perigee: 896 km (556 mi). Apogee: 199,442 km (123,927 mi). Inclination: 65.00 deg. Period: 5,768.60 min. Solar flare monitor. Study of the processes of solar activity and of their influence on interplanetary space and the Earth's magnetosphere. 1974 April 3 - 07:30 GMT - Launch Vehicle: Soyuz. Cosmos 638 Mass: 6,570 kg (14,480 lb). Spacecraft: Soyuz 7K-TM. Agency: MOM. Perigee: 187 km (116 mi). Apogee: 309 km (192 mi). Inclination: 51.80 deg. Period: 89.40 min. Unmanned Soyuz test flight. Recovered April 13, 1974 5:05 GMT. Soyuz ASTP Test. 1974 April 12 - Launch Vehicle: Soyuz. FAILURE: Failure. Zenit-4MK Spacecraft: Zenit-4MK. Agency: RVSN. High resolution photo reconnaissance mission. 1974 August 12 - 06:25 GMT - Launch Vehicle: Soyuz. Cosmos 672 Mass: 6,570 kg (14,480 lb). Spacecraft: Soyuz 7K-TM. Agency: MOM. Perigee: 222 km (137 mi). Apogee: 226 km (140 mi). Inclination: 51.70 deg. Period: 88.90 min. ASTP precursor. Recovered August 18, 1974 5:02 GMT. Soyuz ASTP test. 1975 December 22 - 02:08 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-SOL Prognoz 4 Mass: 905 kg (1,995 lb). Spacecraft: Prognoz. Agency: MOM. Perigee: 634 km (393 mi). Apogee: 199,000 km (123,000 mi). Inclination: 65.00 deg. Period: 5,740.00 min. Investigation of the corpuscular and electromagnetic radiation of the sun and of solar plasma fluxes, study of the magnetic fields in circumterrestrial space in order to determine the effects of solar activity on the interplanetary medium and in the magne tosphere of the earth. 1976 November 25 - 03:59 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-SOL Prognoz 5 Mass: 930 kg (2,050 lb). Spacecraft: Prognoz. Agency: MOM. Perigee: 777 km (482 mi). Apogee: 198,560 km (123,370 mi). Inclination: 65.20 deg. Period: 5,728.00 min. Investigation of the corpuscular and electromagnetic radiation of the sun and of solar plasma fluxes, study of the magnetic fields in circumterrestrial space in order to determine the effects of solar activity on the interplanetary medium and in the magne tosphere of the earth. 1977 February 22 - Launch Vehicle: Soyuz. FAILURE: Failure. Zenit-4MK Spacecraft: Zenit-4MK. Agency: RVSN. High resolution photo reconnaissance mission. 1977 June 29 - 18:34 GMT - Launch Vehicle: Soyuz. Meteor 1-28 Mass: 3,800 kg (8,300 lb). Spacecraft: Meteor-Priroda. Agency: MOM. Perigee: 332 km (206 mi). Apogee: 338 km (210 mi). Inclination: 97.40 deg. Period: 91.20 min. Continuation of experimental work in studying the natural resources of the earth. Acquisition of meteorological information required for use in the operational weather service. 1977 August 10 - Launch Vehicle: Soyuz. FAILURE: Failure. Zenit-4MKM Spacecraft: Zenit-4MKM. High resolution photo reconnaissance mission. 1977 September 22 - 00:51 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-SOL Prognoz 6 Mass: 910 kg (2,000 lb). Spacecraft: Prognoz. Agency: MOM. Perigee: 1,850 km (1,140 mi). Apogee: 196,379 km (122,024 mi). Inclination: 74.40 deg. Period: 5,683.20 min. Investigation of the corpuscular and electromagnetic radiation of the sun and of solar plasma fluxes, study of the magnetic fields in circumterrestrial space in order to determine the effects of solar activity on the interplanetary medium and in the magne tosphere of the earth. 1978 January 20 - 08:24 GMT - Launch Vehicle: Soyuz. Progress 1 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 256 km (159 mi). Inclination: 51.60 deg. Period: 88.70 min. Flight: Salyut 6 EO-1. Unmanned supply vessel to Salyut 6. Delivery of fuel, consumable materials and equipment to the Salyut 6 station. Docked with Salyut 6 on 22 Jan 1978 10:12:14 GMT. Undocked on 6 Feb 1978 05:54:00 GMT. Destroyed in reentry on 8 Feb 1978 02:00:00 GMT. Total free-flight time 3.91 days. Total docked time 14.82 days. 1978 July 2 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 1026 Mass: 6,000 kg (13,200 lb). Spacecraft: Energia. Agency: MOM. Perigee: 212 km (131 mi). Apogee: 247 km (153 mi). Inclination: 51.70 deg. Period: 89.00 min. Investigation of primary cosmic radiation and meteoritic particles in near-earth outer space. 1978 July 7 - 11:26 GMT - Launch Vehicle: Soyuz. Progress 2 Mass: 7,014 kg (15,463 lb). Spacecraft: Progress. Agency: MOM. Perigee: 248 km (154 mi). Apogee: 307 km (190 mi). Inclination: 51.60 deg. Period: 90.00 min. Flight: Salyut 6 EO-2. Unmanned supply vessel to Salyut 6. Delivery of fuel, consumable materials and equipment to the Salyut 6 station. Docked with Salyut 6 on 9 Jul 1978 12:58:59 GMT. Undocked on 2 Aug 1978 04:57:44 GMT. Destroyed in reentry on 4 Aug 1978 01:31:07 GMT. Total free-flight time 3.92 days. Total docked time 23.67 days. 1978 August 7 - 22:31 GMT - Launch Vehicle: Soyuz. Progress 3 Mass: 7,014 kg (15,463 lb). Spacecraft: Progress. Agency: MOM. Perigee: 190 km (110 mi). Apogee: 232 km (144 mi). Inclination: 51.60 deg. Period: 88.70 min. Flight: Salyut 6 EO-2. Unmanned supply vessel to Salyut 6. Delivery of fuel, consumable materials and equipment to the Salyut 6 station. Docked with Salyut 6 on 9 Aug 1978 23:59:30 GMT. Undocked on 21 Aug 1978 15:42:50 GMT. Destroyed in reentry on 23 Aug 1978 16:45:00 GMT. Total free-flight time 4.10 days. Total docked time 11.66 days. 1978 October 30 - 05:23 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-SOL Prognoz 7 Mass: 950 kg (2,090 lb). Spacecraft: Prognoz. Agency: MOM. Perigee: 472 km (293 mi). Apogee: 202,627 km (125,906 mi). Inclination: 64.90 deg. Period: 5,881.10 min. Magnetospheric investigations. Investigation of the corpuscular and electromagnetic radiation of the sun, of solar plasma fluxes and of the magnetic fields in circumterrestrial space in order to determine the effects of solar activity on the interplanetary medium and the magnetosphere of the earth; investigation of galactic ultraviolet rays, X-rays and gamma rays. In addition to Soviet apparatus, carried scientific apparatus produced in the USSR, the Czechoslovak Socialist Republic, France, the Hungarian People's Republic and Sweden. 1979 January 31 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 1074 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 195 km (121 mi). Apogee: 238 km (147 mi). Inclination: 51.60 deg. Period: 88.80 min. Manned precursor. Recovered April 1, 1979 10:09 GMT. Soyuz T Test. 1979 February 25 - 11:53 GMT - Launch Vehicle: Soyuz. Soyuz 32 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 193 km (119 mi). Apogee: 256 km (159 mi). Inclination: 51.60 deg. Period: 88.90 min. Crew: Lyakhov, Ryumin. Flight: Salyut 6 EO-3. Manned two crew. Docked with Salyut 6. Transported a team consisting of V A Lyakhov and V V Ryumin to the Salyut-6 space station to conduct scientific investigations and experiments and repair work. Recovered June 15, 1979 16:18 GMT. Returned unmanned. 1979 March 12 - 05:47 GMT - Launch Vehicle: Soyuz. Progress 5 Mass: 7,014 kg (15,463 lb). Spacecraft: Progress. Agency: MOM. Perigee: 183 km (113 mi). Apogee: 256 km (159 mi). Inclination: 51.70 deg. Period: 88.80 min. Flight: Salyut 6 EO-3. Unmanned supply vessel to Salyut 6. Delivery of fuel, consumable materials and equipment to the Salyut 6 station. Docked with Salyut 6 on 14 Mar 1979 07:19:21 GMT. Undocked on 3 Apr 1979 16:10:00 GMT. Destroyed in reentry on 5 Apr 1979 00:10:22 GMT. Total free-flight time 3.40 days. Total docked time 20.37 days. 1979 April 10 - 17:34 GMT - Launch Vehicle: Soyuz. Soyuz 33 Mass: 6,860 kg (15,120 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 194 km (120 mi). Apogee: 261 km (162 mi). Inclination: 51.60 deg. Period: 89.00 min. Crew: Ivanov Georgi, Rukavishnikov. Flight: Salyut 6 EP-5-1, Salyut 6 EO-3. Manned two crew. Flight under the Intercosmos programme of an international team consisting of N N Rukavishnikov (USSR) and G I Ivanov (Bulgaria). Unsuccessful mission. Failed to rendezvous with Salyut 6. 1979 May 13 - 04:17 GMT - Launch Vehicle: Soyuz. Progress 6 Mass: 7,014 kg (15,463 lb). Spacecraft: Progress. Agency: MOM. Perigee: 190 km (110 mi). Apogee: 247 km (153 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Salyut 6 EO-3. Unmanned supply vessel to Salyut 6. Delivery of fuel, consumable materials and equipment to the Salyut 6 station. Docked with Salyut 6 on 15 May 1979 06:19:22 GMT. Undocked on 8 Jun 1979 07:59:41 GMT. Destroyed in reentry on 9 Jun 1979 18:52:46 GMT. Total free-flight time 3.54 days. Total docked time 24.07 days. 1979 June 6 - 18:12 GMT - Launch Vehicle: Soyuz. Soyuz 34 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 192 km (119 mi). Apogee: 254 km (157 mi). Inclination: 51.60 deg. Period: 88.90 min. Flight: Salyut 6 EO-3. Docked with Salyut 6. Launched unmanned to provide return vehicle for Soyuz 32 crew of Lyakhov/Ryumin after Soyuz 33 primary propulsion system failure. Checked the operation of the spacecraft propulsion unit; transportated the crew of the Salyut-6 station back to earth. 1979 June 28 - 09:25 GMT - Launch Vehicle: Soyuz. Progress 7 Mass: 7,014 kg (15,463 lb). Spacecraft: Progress. Agency: MOM. Perigee: 186 km (115 mi). Apogee: 251 km (155 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Salyut 6 EO-3. Unmanned supply vessel to Salyut 6. Delivery of fuel, consumable materials and equipment to the Salyut 6 station. Docked with Salyut 6 on 30 Jun 1979 11:18:22 GMT. Undocked on 18 Jul 1979 03:49:55 GMT. Destroyed in reentry on 20 Jul 1979 01:57:30 GMT. Total free-flight time 4.0 days. Total docked time 17.69 days. 1979 December 16 - 12:29 GMT - Launch Vehicle: Soyuz. Soyuz T-1 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 213 km (132 mi). Apogee: 252 km (156 mi). Inclination: 51.60 deg. Period: 89.20 min. New generation Soyuz capsule; unmanned flight to Salyut 6. Docked with Salyut 6. Recovered March 25, 1980 21:47 GMT. Unmanned test of Soyuz T design. 1980 March 27 - 18:53 GMT - Launch Vehicle: Soyuz. Progress 8 Mass: 7,014 kg (15,463 lb). Spacecraft: Progress. Agency: MOM. Perigee: 185 km (114 mi). Apogee: 250 km (150 mi). Inclination: 51.60 deg. Period: 88.90 min. Unmanned supply vessel for Salyut 6. Delivery of various cargoes to the Salyut-6 orbital station. Docked with Salyut 6 on 29 Mar 1980 20:01:00 GMT. Undocked on 25 Apr 1980 08:04:00 GMT. Destroyed in reentry on 26 Apr 1980 06:54:00 GMT. Total free-flight time 3.0 days. Total docked time 26.50 days. 1980 April 9 - 13:38 GMT - Launch Vehicle: Soyuz. Soyuz 35 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 197 km (122 mi). Apogee: 247 km (153 mi). Inclination: 51.60 deg. Period: 88.90 min. Crew: Popov, Ryumin. Flight: Salyut 6 EO-4. Manned two crew. Docked with Salyut 6. Carried crew comprising L I Popov and V V Ryumin to the Salyut-6 station to carry out scientific and technical research and experiments. 1980 May 26 - 18:20 GMT - Launch Vehicle: Soyuz. Soyuz 36 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 190 km (110 mi). Apogee: 263 km (163 mi). Inclination: 51.60 deg. Period: 89.00 min. Crew: Farkas, Kubasov. Flight: Salyut 6 EP-5, Salyut 6 EO-4. Transported the fifth international crew under the INTERCOSMOS programme, comprising V N Kubasov (USSR) and B Farkas (Hungary) to the Salyut-6 station to carry out scientific research and experiments. 1980 October 30 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 1218 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 158 km (98 mi). Apogee: 285 km (177 mi). Inclination: 64.90 deg. Period: 88.90 min. Successful state acceptance test flight of Yantar-4K1 satellite. Led to Yantar-4K1 acceptance for Red Army service the following year. High resolution photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. 1980 December 25 - 04:02 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-SOL Prognoz 8 Mass: 910 kg (2,000 lb). Spacecraft: Prognoz. Agency: MOM. Perigee: 978 km (607 mi). Apogee: 197,364 km (122,636 mi). Inclination: 65.80 deg. Period: 5,687.80 min. Examined solar wind interaction with magnetosphere. Investigation of the corpuscular and electromagnetic radiation of the sun and of solar plasma fluxes, study of the magnetic fields in circumterrestrial space in order to determine the effects of solar activity on the interplanetary medium and in the magne tosphere of the earth. In addition to Soviet apparatus, carried scientific apparatus produced in the USSR, the Czechoslovak Socialist Republic, the Polish People's Republic, and Sweden. 1981 January 20 - 11:00 GMT - Launch Vehicle: Soyuz. Cosmos 1240 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-2K. Agency: MOM. Perigee: 165 km (102 mi). Apogee: 359 km (223 mi). Inclination: 64.90 deg. Period: 89.80 min. Area survey photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. 1981 February 18 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 1246 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 193 km (119 mi). Apogee: 263 km (163 mi). Inclination: 64.90 deg. Period: 89.10 min. Military topographic / cartographic satellite. 1981 March 17 - 08:40 GMT - Launch Vehicle: Soyuz. Cosmos 1259 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 379 km (235 mi). Inclination: 70.30 deg. Period: 90.40 min. Photo surveillance; returned film capsule. 1981 March 22 - 14:58 GMT - Launch Vehicle: Soyuz. Soyuz 39 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 198 km (123 mi). Apogee: 249 km (154 mi). Inclination: 51.80 deg. Period: 88.90 min. Crew: Dzhanibekov, Gurragcha. Flight: Salyut 6 EP-9, Salyut 6 EO-6. Manned two crew. Docked with Salyut 6. Transported to the Salyut-6 orbital station the eighth international crew under the INTERCOSMOS programme, comprising V A Dzhanibekov (USSR) and Z. Gurragchi (Mongolian People's Republic) to conduct scientific investigations and experiments. 1981 March 28 - Launch Vehicle: Soyuz. FAILURE: Failure of launch vehicle. Yantar-2K s/n 979 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-2K. Agency: RVSN. Yantar Area survey photo reconnaissance spacecraft failed to achieve orbit. 1981 May 18 - 11:50 GMT - Launch Vehicle: Soyuz. Cosmos 1270 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-2K. Agency: MOM. Perigee: 171 km (106 mi). Apogee: 345 km (214 mi). Inclination: 64.90 deg. Period: 89.70 min. Area survey photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. 1981 July 15 - 13:00 GMT - Launch Vehicle: Soyuz. Cosmos 1282 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-2K. Agency: MOM. Perigee: 170 km (100 mi). Apogee: 332 km (206 mi). Inclination: 64.90 deg. Period: 89.50 min. Area survey photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. 1981 December 19 - 11:50 GMT - Launch Vehicle: Soyuz. Cosmos 1330 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-2K. Agency: MOM. Perigee: 164 km (101 mi). Apogee: 376 km (233 mi). Inclination: 70.40 deg. Period: 89.90 min. Area survey photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. 1982 January 30 - 11:30 GMT - Launch Vehicle: Soyuz. Cosmos 1336 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-2K. Agency: MOM. Perigee: 170 km (100 mi). Apogee: 352 km (218 mi). Inclination: 70.30 deg. Period: 89.70 min. Area survey photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. 1982 June 8 - 12:00 GMT - Launch Vehicle: Soyuz. Cosmos 1377 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 363 km (225 mi). Inclination: 64.90 deg. Period: 89.90 min. Photo surveillance; 2 small film capsules recovered in course of flight and main reentry capsule with remaining film, camera, and computer systems at end of flight. 1982 August 4 - 11:30 GMT - Launch Vehicle: Soyuz. Cosmos 1399 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 171 km (106 mi). Apogee: 344 km (213 mi). Inclination: 64.90 deg. Period: 89.70 min. High resolution photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. 1982 December 16 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 1424 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 171 km (106 mi). Apogee: 349 km (216 mi). Inclination: 64.90 deg. Period: 89.70 min. High resolution photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. 1982 December 28 - 12:00 GMT - Launch Vehicle: Soyuz. Cosmos 1426 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 200 km (120 mi). Apogee: 384 km (238 mi). Inclination: 50.60 deg. Period: 90.40 min. Photo/digital surveillance. 1983 February 6 - 11:31 GMT - Launch Vehicle: Soyuz. Cosmos 1439 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-2K. Agency: MOM. Perigee: 168 km (104 mi). Apogee: 344 km (213 mi). Inclination: 70.40 deg. Period: 89.60 min. Area survey photo reconnaissance; film capsule; also performed earth resources tasks. Returned in less than usual 30 day full duration. 1983 April 26 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 1457 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 164 km (101 mi). Apogee: 354 km (219 mi). Inclination: 70.40 deg. Period: 89.70 min. High resolution photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. 1983 May 26 - 12:00 GMT - Launch Vehicle: Soyuz. Cosmos 1466 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 166 km (103 mi). Apogee: 315 km (195 mi). Inclination: 64.90 deg. Period: 89.70 min. High resolution photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. 1983 July 1 - 12:17 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-SOL Prognoz 9 Mass: 1,060 kg (2,330 lb). Spacecraft: Prognoz. Agency: MOM. Perigee: 380 km (230 mi). Apogee: 720,000 km (440,000 mi). Inclination: 1.30 deg. Period: 38,448.00 min. Investigation of residual radiation from the Big Bang and gamma flares in deep space, and solar corpuscular and electromagnetic radiation plasma flows and magnetic fields in circumterrestrial space to determine the effects of solar activity on the interpl anetary medium and the earth's magnetosphere. In addition to Soviet scientific apparatus, carried instruments built in Czechoslovakia and France. 1983 July 24 - 05:30 GMT - Launch Vehicle: Soyuz. Cosmos 1484 Mass: 2,500 kg (5,500 lb). Spacecraft: Resurs-OE. Agency: MOM. Perigee: 543 km (337 mi). Apogee: 593 km (368 mi). Inclination: 97.50 deg. Period: 96.00 min. Follow-on to Meteor series. Second flight of prototype for Resurs-O1 spacecraft. Gathering regular information on the natural resources of the earth for use in various branches of the Soviet economy, and conducting further tests on new types of measuring apparatus and methods of remote sensing of the earth's surface and atmosphere. 1983 August 10 - 13:00 GMT - Launch Vehicle: Soyuz. Cosmos 1489 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 299 km (185 mi). Inclination: 64.70 deg. Period: 89.20 min. High resolution photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. 1983 October 14 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 1504 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 172 km (106 mi). Apogee: 304 km (188 mi). Inclination: 64.90 deg. Period: 89.30 min. High resolution photo reconnaissance; returned film in two small SpK capsules during the mission and with the main capsule at completion of the mission. 1983 October 20 - 09:59 GMT - Launch Vehicle: Soyuz. Progress 18 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 185 km (114 mi). Apogee: 242 km (150 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Salyut 7 EO-2. Transport of various cargoes to the Salyut-7 orbital station. Docked with Salyut 7 on 22 Oct 1983 11:34:00 GMT. Boosted Salyut to 326 X 356 orbit on 4 Nov 1983. Undocked on 13 Nov 1983 03:08:00 GMT. Destroyed in reentry on 16 Nov 1983 04:18:00 GMT. Total free-flight time 5.11 days. Total docked time 21.65 days. 1984 February 8 - 12:07 GMT - Launch Vehicle: Soyuz. Soyuz T-10 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 199 km (123 mi). Apogee: 219 km (136 mi). Inclination: 51.60 deg. Period: 88.70 min. Crew: Atkov, Kizim, Solovyov Vladimir. Flight: Salyut 7 EO-3. Manned three crew. Docked with Salyut 7. Transported a crew consisting of ship's commander L D Kizim, flight engineer V A Solovyov and cosmonaut-research O Y Atkov to the SALYUT-7 orbital station to conduct scientific and technical studies and experiments. 1984 February 21 - 06:46 GMT - Launch Vehicle: Soyuz. Progress 19 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 186 km (115 mi). Apogee: 245 km (152 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Salyut 7 EO-3. Transport of various cargoes to the Salyut-7 orbital station. Docked with Salyut 7 on 23 Feb 1984 08:21:00 GMT. Undocked on 31 Mar 1984 09:40:00 GMT. Destroyed in reentry on 1 Apr 1984 18:18:00 GMT. Total free-flight time 3.43 days. Total docked time 37.05 days. 1984 April 3 - 13:08 GMT - Launch Vehicle: Soyuz. Soyuz T-11 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 195 km (121 mi). Apogee: 224 km (139 mi). Inclination: 51.60 deg. Period: 88.70 min. Crew: Malyshev, Sharma, Strekalov. Flight: Salyut 7 EP-3, Salyut 7 EO-3. Manned three crew. Docked with Salyut 7.Transported a Soviet-Indian international crew comprising ship's commander Y V Malyshev, flight engineer G M Strekalov (USSR) and cosmonaut-researcher R Sharma (India) to the SALYUT-7 orbital station to conduct scientific and technical studies and experiments. 1984 April 15 - 08:12 GMT - Launch Vehicle: Soyuz. Progress 20 Mass: 7,200 kg (15,800 lb). Spacecraft: Progress. Agency: MOM. Perigee: 186 km (115 mi). Apogee: 260 km (160 mi). Inclination: 51.60 deg. Period: 89.00 min. Flight: Salyut 7 EO-3. Transport of various cargoes to the Salyut-7 orbital station. First launch of Progress by Soyuz-U2 launch vehicle. Docked with Salyut 7 on 17 Apr 1984 09:22:00 GMT. Undocked on 6 May 1984 17:46:00 GMT. Destroyed in reentry on 7 May 1984 00:32:51 GMT. Total free-flight time 2.33 days. Total docked time 19.35 days. 1984 May 7 - 22:47 GMT - Launch Vehicle: Soyuz. Progress 21 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 187 km (116 mi). Apogee: 246 km (152 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Salyut 7 EO-3. Transport of various cargoes to the Salyut-7 orbital station. Docked with Salyut 7 on 10 May 1984 00:10:00 GMT. Undocked on 26 May 1984 09:41:00 GMT. Destroyed in reentry on 26 May 1984 15:00:30 GMT. Total free-flight time 2.28 days. Total docked time 16.40 days. 1984 May 28 - 14:12 GMT - Launch Vehicle: Soyuz. Progress 22 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 188 km (116 mi). Apogee: 244 km (151 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Salyut 7 EO-3. Transport of various cargoes to the Salyut-7 orbital station. Docked with Salyut 7 on 30 May 1984 15:47:00 GMT. Undocked on 15 Jul 1984 13:36:00 GMT. Destroyed in reentry on 15 Jul 1984 18:52:00 GMT. Total free-flight time 2.28 days. Total docked time 45.91 days. 1984 July 17 - 17:40 GMT - Launch Vehicle: Soyuz. Soyuz T-12 Mass: 7,020 kg (15,470 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 192 km (119 mi). Apogee: 218 km (135 mi). Inclination: 51.60 deg. Period: 88.60 min. Crew: Dzhanibekov, Savitskaya, Volk. Flight: Salyut 7 EP-4, Salyut 7 EO-3. Docked with Salyut 7. Transported a crew comprising ship's commander V A Dzhanibekov, flight engineer S E Savitskaya and cosmonaut-research I P Volk to the Salyut-7 orbital station to conduct scientific and technical studies and experiments. 1985 April 26 - 05:48 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-SOL Intercosmos 23 Mass: 1,000 kg (2,200 lb). Spacecraft: Prognoz. Agency: MOM. Perigee: 5,975 km (3,712 mi). Apogee: 194,734 km (121,001 mi). Inclination: 76.80 deg. Period: 5,783.70 min. Magnetosphere and solar wind investigations. Prognoz-10-Intercosmos. Investigation of the structure of interplanetary and circumterrestrial shock waves generated by the interaction of the solar wind and the earth's magnetosphere. Carries scientific apparatus developed by scientists and specialists o f the USSR and the Czechoslovak Socialist Republic in the 'Intercosmos' programme of international cooperation in the exploration and peaceful uses of outer space. 1985 October 3 - 05:48 GMT - Launch Vehicle: Soyuz. Cosmos 1689 Mass: 1,500 kg (3,300 lb). Spacecraft: Resurs-O1. Agency: MOM. Perigee: 496 km (308 mi). Apogee: 545 km (338 mi). Inclination: 97.60 deg. Period: 95.10 min. First flight of Resurs-O1. Acquisition of operational information on the natural resources of the earth in the interests of various branches of the national economy of the USSR; continued trials of new types of informational and measurement apparatus and methods of remote sensing of the earth's surface and atmosphere. Operated for one year, two months. Re-entered January 14, 2001. 1988 March 17 - 06:43 GMT - Launch Vehicle: Soyuz. IRS-1A Mass: 975 kg (2,149 lb). Spacecraft: IRS. Agency: ISRO. Perigee: 897 km (557 mi). Apogee: 917 km (569 mi). Inclination: 99.00 deg. Period: 103.10 min. Indian remote sensing; 1st Soviet commercial launch. Indian Remote Sensing Satellite (IRS-1A). Operational remote sensing of the Earth for natural resources management applications. Also registered by the USSR as object no. 2387 in ST/SG/SER.E/182 and orbital parameters 102.7 min, 863 x 917 km x 99.01 deg. 1988 April 20 - 05:48 GMT - Launch Vehicle: Soyuz. Cosmos 1939 Mass: 2,000 kg (4,400 lb). Spacecraft: Resurs-O1. Agency: MOM. Perigee: 570 km (350 mi). Apogee: 602 km (374 mi). Inclination: 97.70 deg. Period: 96.40 min. Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation. Stayed in operation for six years, six months, far beyond its rated life of 3 to 5 years. 1991 July 10 - 14:00 GMT - Launch Vehicle: Soyuz. Cosmos 2153 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 182 km (113 mi). Apogee: 267 km (165 mi). Inclination: 64.90 deg. Period: 89.00 min. Photo/digital surveillance. 1991 August 29 - 06:48 GMT - Launch Vehicle: Soyuz. IRS-1B Mass: 980 kg (2,160 lb). Spacecraft: IRS. Agency: ISRO. Perigee: 892 km (554 mi). Apogee: 919 km (571 mi). Inclination: 99.00 deg. Period: 103.10 min. Remote sensing; launched commercially by USSR. Operational remote sensing satellite for natural resources management. 1991 December 17 - 11:00 GMT - Launch Vehicle: Soyuz. Cosmos 2174 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 193 km (119 mi). Apogee: 306 km (190 mi). Inclination: 64.90 deg. Period: 89.50 min. Topographic mapping for the Army General Staff. 1992 April 8 - 12:20 GMT - Launch Vehicle: Soyuz. Cosmos 2183 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 237 km (147 mi). Apogee: 289 km (179 mi). Inclination: 64.90 deg. Period: 89.80 min. Photo/digital surveillance. 1992 June 30 - 16:43 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 15000-062 Progress M-13 Mass: 7,320 kg (16,130 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 185 km (114 mi). Apogee: 226 km (140 mi). Inclination: 51.60 deg. Period: 88.60 min. Flight: Mir EO-11. Unmanned resupply vessel to Mir. An initial docking attempt on 2 Jul 1992 was a failure. Docked with Mir on 4 Jul 1992 16:55:13 GMT. Undocked on 24 Jul 1992 04:14:00 GMT. Destroyed in reentry on 24 Jul 1992 08:03:35 GMT. Total free-flight time 4.17 days. Total docked time 19.47 days. It was docked to Mir for only a few weeks, since on 26 Jul the Soyuz TM-15 was to be launched with a replacement crew and would need to use the same docking port. 1992 August 15 - 22:18 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 U15000-064 Progress M-14 Mass: 7,176 kg (15,820 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 187 km (116 mi). Apogee: 221 km (137 mi). Inclination: 51.50 deg. Period: 88.60 min. Flight: Mir EO-12. Unmanned resupply vessel to Mir. Progress M-38 was specially modified to carry the first VDU (Vynosnaya Dvigatel'naya Ustanovka, External Engine Unit) propulsion unit. The VDU was mounted externally on a special structure between the cargo module and the service module, replacing the OKD fuel section present on normal Progress vehicles. The crew spacewalked to extract the VDU from Progress and place it on the end of the Sofora boom extending from the Kvant module. The VDU was used to provide attitude control capability for the Mir station. Docked with Mir on 18 Aug 1992 00:20:48 GMT. Undocked on 21 Oct 1992 16:46:01 GMT. Destroyed in reentry on 21 Oct 1992 23:12:00 GMT. Total free-flight time 2.35 days. Total docked time 64.68 days. 1992 October 27 - 17:19 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 15000-061 Progress M-15 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 187 km (116 mi). Apogee: 205 km (127 mi). Inclination: 51.60 deg. Period: 88.40 min. Flight: Mir EO-12. Unmanned resupply vessel to Mir. Docked with Mir on 29 Oct 1992 19:05:51 GMT. Undocked on 4 Feb 1993 00:44:53 GMT. After completion of the Znamya and autonomous operation experiments, destroyed in reentry on 7 Feb 1993 06:43:20 GMT. Total free-flight time 5.32 days. Total docked time 97.24 days. 1992 December 22 - 12:00 GMT - Launch Vehicle: Soyuz. Cosmos 2225 Mass: 6,500 kg (14,300 lb). Spacecraft: Orlets-1. Agency: MOM. Perigee: 169 km (105 mi). Apogee: 313 km (194 mi). Inclination: 64.90 deg. Period: 89.30 min. Long duration film return military reconnaissance satellite. After returning multiple film capsules, the spacecraft was deorbited. 1993 April 27 - 10:35 GMT - Launch Vehicle: Soyuz. Cosmos 2243 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 189 km (117 mi). Apogee: 233 km (144 mi). Inclination: 70.40 deg. Period: 88.70 min. Topographic mapping for the Army General Staff. Mission normally would have run 44 days. 1993 September 7 - 13:25 GMT - Launch Vehicle: Soyuz. Cosmos 2262 Mass: 6,500 kg (14,300 lb). Spacecraft: Orlets-1. Agency: MOM. Perigee: 182 km (113 mi). Apogee: 261 km (162 mi). Inclination: 64.90 deg. Period: 88.90 min. Long duration film return military reconnaissance satellite. After returning multiple film capsules, the spacecraft was deorbited. First launch that demonstrated doubled operational life. 1994 April 28 - 17:14 GMT - Launch Vehicle: Soyuz. Cosmos 2280 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 233 km (144 mi). Apogee: 283 km (175 mi). Inclination: 70.40 deg. Period: 89.70 min. Photo/digital surveillance. 1994 July 29 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 2284 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 211 km (131 mi). Apogee: 274 km (170 mi). Inclination: 70.30 deg. Period: 89.35 min. Topographic mapping for the Army General Staff. Landed September 11 1994. 1994 December 29 - 11:30 GMT - Launch Vehicle: Soyuz. Cosmos 2305 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 231 km (143 mi). Apogee: 288 km (178 mi). Inclination: 64.90 deg. Period: 89.70 min. Photo/digital surveillance. 1995 September 29 - 04:25 GMT - Launch Vehicle: Soyuz. Cosmos 2320 Mass: 7,000 kg (15,400 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 235 km (146 mi). Apogee: 372 km (231 mi). Inclination: 64.90 deg. Period: 89.30 min. Photo/digital surveillance. 1995 December 28 - 06:45 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-2BL IRS-1C Mass: 1,250 kg (2,750 lb). Spacecraft: IRS. Agency: ISRO. Perigee: 819 km (508 mi). Apogee: 820 km (500 mi). Inclination: 98.60 deg. Period: 101.30 min. Indian Remote Sensing Satellite. 1996 May 14 - 08:55 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U PVB78051-368 FAILURE: Shroud broke up at T+49 seconds. Kometa Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: VKS. Topographic mapping satellite failed to reach orbit. 1997 May 15 - 12:10 GMT - Launch Vehicle: Soyuz. Cosmos 2343 Mass: 6,500 kg (14,300 lb). Spacecraft: Orlets-1. Agency: MO RF. Perigee: 179 km (111 mi). Apogee: 343 km (213 mi). Inclination: 64.90 deg. Period: 89.40 min. Long duration film return military reconnaissance satellite. After returning multiple film capsules, the spacecraft was deorbited. This satellite provided Russia with the photo reconnaisance capability after a break of 7 1/2 months. This launch came on the 40th anniversary of the first successful launch of the R-7 rocket, from which the Soyuz-U was derived. It was the 250th launch of the Soyuz-U from Baikonur, the 350th launch from Launch Complex 31, and the 666th launch of a Soyuz-U. 1998 February 17 - 10:35 GMT - Launch Vehicle: Soyuz. Cosmos 2349 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: RKA. Perigee: 212 km (131 mi). Apogee: 327 km (203 mi). Inclination: 70.40 deg. Period: 89.90 min. Topographic mapping for the Army General Staff. Landed in Kazakhstan April 2 1998. 1998 June 25 - 14:00 GMT - Launch Vehicle: Soyuz. Cosmos 2359 Spacecraft: Yantar-4KS1. Agency: MO RF. Perigee: 239 km (148 mi). Apogee: 300 km (180 mi). Inclination: 64.90 deg. Period: 89.90 min. Photo/digital surveillance. Entered an initial 170 x 290 km x 64.9 deg initial orbit. It manoeuvred to its operational orbit of 240 x 302 km x 64.9 deg on June 27. 2000 February 8 - 23:20 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U/Fregat A15000-079 ST07 IRDT Mass: 110 kg (240 lb). Spacecraft: IRDT. Agency: ESA. Perigee: 580 km (361 mi). Apogee: 613 km (381 mi). Inclination: 64.85 deg. Period: 96.53 min. After four orbits around the Earth the test vehicle was powered by the launcher’s upper stage to re-enter the atmosphere for a landing about 1800 km northwest of the launch site. The heat shield was inflated and the IRDT separated from the upper stage. It then passed through the upper atmospheric layers that imposed the highest dynamic pressure, heat flux and acceleration loads onto the system. The IRDT landed inside the predicted area at 54 deg E and 51 deg N near the Kazakhstan border. Unfortunately, a tear occurred in the inflatable shield during descent resulting in a higher velocity and a heavier than expected impact on landing, resulting in some damage to the lower part of the IRDT. The IRDT was collected by helicopter so that the memory unit of the sensor package, with all recorded data, could be analysed. An initial data check confirmed that all experiments in the sensor package worked perfectly. 2000 March 20 - 18:28 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U/Fregat - ST08 Dumsat Mass: 2,382 kg (5,251 lb). Agency: Starsem. Perigee: 332 km (206 mi). Apogee: 17,687 km (10,990 mi). Inclination: 64.70 deg. Period: 316.60 min. Cluster 2 Composite Mock-Up validation flight. Mass model of a pair of Cluster II scientific satellites built by Aerospatiale Matra. Second test launch of the Soyuz-Fregat launch vehicle. 2000 July 16 - 12:39 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U/Fregat A15000-069 ST09 Samba Mass: 1,200 kg (2,600 lb). Spacecraft: Cluster 2. Agency: ESA. Perigee: 21,449 km (13,327 mi). Apogee: 116,279 km (72,252 mi). Inclination: 88.50 deg. Period: 3,423.40 min. The first two European Space Agency Cluster II satellites, Samba (FM7) and Salsa (FM6) were launched into an initial 200 km / 64.8 deg circular orbit. The Fregat upper stage then burned once before ejecting the satellites into a 250 x 18072 km x 64.7 deg transfer orbit. Both satellites then used their Astrium (former MBB) S400 liquid engines in a series of four additional burns before reaching their final 16869 x 121098 km x 90.6 deg orbits. Each magnetosphere research satellite deployed four 50-meter wire antennas. 2000 August 9 - 11:13 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U/Fregat A15000-070 ST10 Rumba Mass: 1,200 kg (2,600 lb). Spacecraft: Cluster 2. Agency: ESA. Perigee: 21,430 km (13,310 mi). Apogee: 116,297 km (72,263 mi). Inclination: 88.50 deg. Period: 3,423.30 min. 2000 September 29 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 2373 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MO RF. Perigee: 211 km (131 mi). Apogee: 285 km (177 mi). Inclination: 70.30 deg. Period: 89.46 min. Twentieth Kometa cartographic satellite, using the Yantar service module with a Vostok-type reentry vehicle. It was announced as a dual civil-military geodetic mission. After a day it raised its orbit to 211 x 285 km x 70.4 deg. Landed near Orenburg, Russia on November 14. Deorbit burn was probably around 2230 GMT; the Vostok-style sphere landed at 2253 GMT. 2003 June 2 - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG/Fregat E15000-005/ST11 Mars Express (F-1) / Mars Orbiter / Beagle 2 Mass: 1,120 kg (2,460 lb). Spacecraft: Mars Express. Agency: ESA. Perigee: 177 km (109 mi). Apogee: 177 km (109 mi). Inclination: 51.80 deg. Period: 88.00 min. Europe's first probe to Mars. Mars Express had a mass of 637 kg dry, including science payload and Beagle separation device, together with 480 kg of propellant and the 69 kg Beagle 2 lander, for a total of 1186 kg. In addition to this a 37 kg adapter remained attached to the Fregat upper stage. Mars Express was placed into a 1.014 x 1.531 AU x 0.2 deg orbit around the Sun, following a course correction on June 5. The launch was first moved forward from June 1 and May 31 to May 23. Then delayed to June 6, then moved forward to June 2. 2003 August 12 - 14:20 GMT - Launch Vehicle: Soyuz. Cosmos 2399 Mass: 6,750 kg (14,880 lb). Spacecraft: Orlets-1. Agency: VKS. Perigee: 180 km (110 mi). Apogee: 289 km (179 mi). Inclination: 64.90 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 December 27 - 21:30 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG/Fregat D15000-008 084/ST12 Amos-2 Spacecraft: AMOS. Perigee: 4,408 km (2,738 mi). Apogee: 35,784 km (22,235 mi). Inclination: 23.60 deg. Period: 714.50 min. Intermediate orbit shown. Fregat stage later placed Amos-2 in geostationary orbit. As of 2007 Mar 9 located at 4.00W drifting at 0.003W degrees per day. 2005 August 13 - 23:28 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG Zh15000-011 / Fregat ST-13 sn 007 Galaxy 14 Mass: 2,087 kg (4,601 lb). Spacecraft: Star bus. Agency: PanAmSat. Perigee: 35,782 km (22,233 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Payload swapped from Ariane 5. Launch delayed from December 2004; February 25, March 16 and 25, April 25, June 17, July 10 and 28, August 1, 6 and 12, 2005. As of 2007 Mar 9 located at 125.05W drifting at 0.008W degrees per day. 2005 September 2 - 09:50 GMT - Launch Vehicle: Soyuz. Cosmos 2415 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: VKS. Perigee: 205 km (127 mi). Apogee: 272 km (169 mi). Inclination: 64.90 deg. Period: 89.30 min. 1,700th launch of a vehicle derived from the R-7 ICBM put a Kometa-type cartographic satellite into orbit. The surveillance satellite's primary camera and film payload was recovered at 21:44 on 15 or 16 October. 2005 November 9 - 03:33 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG/Fregat Zh15000-010 Venus Express Mass: 1,270 kg (2,790 lb). Spacecraft: Venus Express. Agency: ESA. Launch delayed from October 26. The Soyuz placed the probe and Fregat upper stage into a 30 km x 190 km x 51.6 deg orbit around the earth. At apogee the Fregat stage made a 50 m/s maneuver to circularize the orbit. At the appropriate moment in this parking orbit, the Fregat fired again, then separated from the now Venus-bound probe at 05:11 GMT. Venus Express passed lunar orbit on November 10 at 10:10 GMT and went into a 0.702 AU x 0.993 AU x 0.26 deg inclination solar orbit. It was to brake itself into a 250 km x 326,550 km x 89.7 deg orbit around Venus on 11 April 2006 at 08:40 GMT. Two maneuvers would put in its final 24-hour Venus orbit of 282 x 66,911 km x 90.0 deg on 30 April. This was selected to synchronise the satellite with tracking stations on earth, while the planet slowly revolves below its perigee point over the following several months. 2005 December 28 - 05:19 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG/Fregat Zh15000-015 Giove-A Mass: 600 kg (1,320 lb). Spacecraft: MiniSat-400. Agency: ESA. Perigee: 23,616 km (14,674 mi). Apogee: 23,616 km (14,674 mi). Inclination: 56.00 deg. Delayed from September, October, December 26. Galileo In-Orbit Validation Element, a prototype for the Galileo European navigation satellite network. Giove carried carried two rubidium atomic clocks and a large L-band phased array antenna. 2006 September 14 - 13:41 GMT - Launch Vehicle: Soyuz. Cosmos 2423 Mass: 6,750 kg (14,880 lb). Spacecraft: Orlets-1. Agency: VKS. Perigee: 208 km (129 mi). Apogee: 306 km (190 mi). Inclination: 64.90 deg. Period: 89.70 min. 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. 2006 October 19 - 16:28 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz ST . Soyuz-2-1A/Fregat Zh15000-003/ST16 Metop-A Mass: 4,093 kg (9,023 lb). Spacecraft: Metop. Perigee: 817 km (507 mi). Apogee: 817 km (507 mi). Inclination: 98.70 deg. Period: 101.00 min. European polar weather satellite equipped with high-resolution visible and infrared cameras, a microwave sounder, ozone monitors, a GPS atmospheric sounding device, a wind scatterometer, and a search and rescue package. First launch of the Soyuz 2 version of the venerable Soyuz launch vehicle. The main change in this first version of the new booster was a digital control system. Problems with this system delayed the launch repeatedly. 2006 December 27 - 14:23 GMT - Launch Vehicle: Soyuz. Soyuz-2-1B/Fregat 001/ST17 Corot Mass: 640 kg (1,410 lb). Spacecraft: Corot. Agency: CNES. Perigee: 900 km (550 mi). Apogee: 902 km (560 mi). Inclination: 90.00 deg. European COnvection ROtation and planetary Transits satellite, designed to detect transits of planets down to earth size as they pass in front of their stars, and convection currents on stellar surfaces. The satellite was to use its 27-cm-diameter telescope to scan 120,000 stars during its 30-month mission. This was the first flight of the Soyuz-2 booster with the improved RD-0124 third stage engine. 2007 May 29 - 20:31 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG/Fregat Ts15000-021 Globalstar A Mass: 450 kg (990 lb). Spacecraft: Globalstar. Agency: Globalstar. Perigee: 914 km (567 mi). Apogee: 932 km (579 mi). Inclination: 52.00 deg. Period: 103.50 min. First replenishment launch of the resurgent Globalstar MEO communications satellite constellation after a five-year hiatus. 2007 October 20 - 20:12 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG/Fregat Ts15000-022 Globalstar FM66 Mass: 450 kg (990 lb). Spacecraft: Globalstar. Agency: Globalstar. Perigee: 914 km (567 mi). Apogee: 932 km (579 mi). Inclination: 52.00 deg. Period: 103.50 min. Last of the first generation Globalstar satellites, launched to replenish the constellation. The Fregat stage made three burns to deploy the satellites into circular orbit, and then deorbit itself to a reentry over the Pacific Ocean. 2007 December 14 - 13:17 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG/Fregat Ts15000-025 Radarsat-2 Mass: 2,200 kg (4,800 lb). Spacecraft: Radarsat. Perigee: 791 km (491 mi). Apogee: 793 km (492 mi). Inclination: 98.60 deg. Period: 100.70 min. Follow-on to Canadian Radarsat-1 launched in 1995. Designed to provide C-band synthetic aperture radar mapping with resolution of 3 m to Canadian government users. Compared to the earlier model had greater resolution, vastly increased on-board data storage capacity, and capability to scan left or right of ground track. Planned lifetime of seven years. Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2008 except where otherwise noted. |
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