LC1 Chronology
1957 May 15 - 16:01 GMT - Launch Vehicle: Soyuz. R-7 No. 5L FAILURE: Failure of Block D strap on, which tore away from the core 98 seconds after liftoff. The booster crashed 400 km from the pad. A fuel leak in the pump outlet led to a fire in the engine compartment from the time of liftoff. M1-5 (I-1) test Agency: MVS. Apogee: 100 km (60 mi). R-7 test flight. (M1-5 (I-1))
1957 June 11 - Launch Vehicle: Soyuz. R-7 8K71 M1-6 R-7 launch attempt After third attempt in three days to launch R-7 8K71 M1-6, the rocket is pulled from the pad. It is found that a nitrogen scavenging valve was installed backwards.
1957 July 12 - 12:53 GMT - Launch Vehicle: Soyuz. R-7 No. 7 FAILURE: Failure of the control system due to a short circuit of the battery. Rapid roll developed, resulting in all four strap-on boosters flying away from the core at 33 seconds in the flight. M1-7 (I-2) test Agency: MVS. Apogee: 20 km (12 mi). R-7 test flight. (M1-7 (I-2))
1957 August 21 - 12:25 GMT - Launch Vehicle: Soyuz. R-7 No. 8 M1-9 (I-3) test Agency: MVS. Apogee: 1,350 km (830 mi). First successful ICBM flight. Problems with the curing of the nose cone material, known before launch, led to the dummy warhead disintegrating over the Kamchatka Peninsula.
1957 September 7 - 11:39 GMT - Launch Vehicle: Soyuz. R-7 No. 9 M1-10 (I-4) test Agency: MVS. Apogee: 1,350 km (830 mi). Second successful ICBM flight.
1957 October 4 - 19:28 GMT - Launch Vehicle: Soyuz. Sputnik 8K71PS No. 1PS Sputnik 1 Mass: 84 kg (185 lb). Spacecraft: Sputnik 1. Agency: MVS. Perigee: 227 km (141 mi). Apogee: 945 km (587 mi). Inclination: 65.00 deg. Period: 96.10 min. First artificial satellite; transmitted signals for 21 days. Launching of first ever artificial satellite of the Earth; physical study of the atmosphere; remained in orbit until January 4, 1958. This event began the space race by galvanizing interest and action on the part of the American public to support an active role in space research, technology, and exploration.
1957 November 3 - 02:30 GMT - Launch Vehicle: Soyuz. Sputnik 8K71PS No. 2PS Sputnik 2 Mass: 508 kg (1,119 lb). Spacecraft: Sputnik 2. Agency: MVS. Perigee: 212 km (131 mi). Apogee: 1,660 km (1,030 mi). Inclination: 65.30 deg. Period: 103.70 min. Carried dog Laika. Study of the physical processes and conditions of life in outer space. After the surprise public impact of Sputnik 1, the satellite and launch teams were called back from vacation and in one month assembled the satellite (using equipment already developed for dog sounding rocket flights). After the launch, Soviet space officials said that the spacecraft would not return and that the dog had enough food and oxygen to live for up to 10 days. Only 45 years later was it revealed that Laika overheated, panicked and died within 5 to 7 hours of launch. What turned out to be the first space crypt remained in orbit a total of 162 days, then burned up in the atmosphere on April 14, 1958.
1958 January 29 - 21:15 GMT - Launch Vehicle: Soyuz. R-7 No. 11 FAILURE: The missile exploded a few seconds after liftoff. M1-12 (I-5) test Agency: MVS. Apogee: 1,350 km (830 mi). Last test of the original R-7 8K71 test series. Suborbital launch test.
1958 March 29 - 14:40 GMT - Launch Vehicle: Soyuz. R-7 No. 10 M1-6A (I-6) test Agency: MVS. Apogee: 1,350 km (830 mi). R-7 test flight. (M1-6A (I-6))
1958 April 4 - 15:30 GMT - Launch Vehicle: Soyuz. R-7 No. 12 B1-11 (I-7) test Agency: MVS. Apogee: 1,350 km (830 mi). R-7 test flight. (B1-11 (I-7))
1958 April 27 - Launch Vehicle: Soyuz. Sputnik 8A91 B1-2 FAILURE: Launch vehicle disintegrated 88 seconds after liftoff. Sputnik failure Spacecraft: Sputnik 3. Agency: MVS.
1958 May 15 - 07:00 GMT - Launch Vehicle: Soyuz. Sputnik 8A91 B1-1 Sputnik 3 Mass: 1,327 kg (2,925 lb). Spacecraft: Sputnik 3. Agency: MVS. Perigee: 217 km (134 mi). Apogee: 1,864 km (1,158 mi). Inclination: 65.20 deg. Period: 106.00 min. Variety of scientific data. Research in the upper atmosphere and outer space
1958 May 24 - 10:30 GMT - Launch Vehicle: Soyuz. R-7 No. 3 FAILURE: Failure. B1-3 (II-1) test Agency: MVS. Apogee: 1,350 km (830 mi). R-7 test flight. (B1-3 (II-1))
1958 July 10 - 07:42 GMT - Launch Vehicle: Soyuz. R-7-71/III No. 6 FAILURE: Failure. B1-14 (II-5)/Blok E test Agency: MVS. Apogee: 0 km ( mi).
1958 September 23 - Launch Vehicle: Soyuz. LV Model: Luna 8K72 . Vostok-L 8K72 B1-3 FAILURE: Launcher disintegrated 93 seconds after launch due to longitudinal resonance of strap-ons. Luna failure - booster disintegrated at T+92 seconds Spacecraft: Luna E-1. Agency: MVS. This was the start of an acrimonious debated between Glushko and Korolev design bureaux over the fault and fix for the problem.
1958 October 11 - 08:42 GMT - Launch Vehicle: Soyuz. LV Model: Luna 8K72 . Vostok-L 8K72 B1-4 FAILURE: Launcher disintegrated 104 seconds after launch due to longitudinal resonance of strap-ons. Luna failure - booster disintegrated at T+104 seconds Spacecraft: Luna E-1. Agency: MVS.
1958 December 4 - Launch Vehicle: Soyuz. LV Model: Luna 8K72 . Vostok-L 8K72 B1-5 FAILURE: Core engines shut off at 245 seconds into the flight. Cause was a loss of lubrication to the hydrogen peroxide pump. Luna failure - booster core shut down at T+245 seconds Spacecraft: Luna E-1. Agency: MVS.
1958 December 24 - 16:00 GMT - Launch Vehicle: Soyuz. FAILURE: Failure. III-1 test Agency: MVS. Apogee: 70 km (43 mi).
1959 January 2 - 16:41 GMT - Launch Vehicle: Soyuz. LV Model: Luna 8K72 . Vostok-L 8K72 B1-6 FAILURE: Failure of the launch vehicle control system. Luna 1 Mass: 361 kg (795 lb). Spacecraft: Luna E-1. Agency: MVS. Lunar probe; passed within 5,995 km of moon but did not hit it as planned due to a failure of the launch vehicle control system. Went into solar orbit. First manmade object to attain of escape velocity. Also known as Mechta ("Dream"), popularly called Lunik I. Because of its high velocity and its announced package of various metallic emblems with the Soviet coat of arms, it was concluded that Luna 1 was intended to impact the Moon. After reaching escape velocity, Luna 1 separated from its 1472 kg third stage. The third stage, 5.2 m long and 2.4 m in diameter, travelled along with Luna 1. On 3 January, at a distance of 113,000 km from Earth, a large (1 kg) cloud of sodium gas was released by the spacecraft. This glowing orange trail of gas, visible over the Indian Ocean with the brightness of a sixth-magnitude star, allowed astronomers to track the spacecraft. It also served as an experiment on the behavior of gas in outer space. Luna 1 passed within 5,995 km of the Moon's surface on 4 January after 34 hours of flight. It went into orbit around the Sun, between the orbits of Earth and Mars. The measurements obtained during this mission provided new data on the Earth's radiation belt and outer space, including the discovery that the Moon had no magnetic field and that a solar wind, a strong flow of ionized plasma emmanating from the Sun, streamed through interplanetary space.
1959 March 17 - 01:46 GMT - Launch Vehicle: Soyuz. R-7 No. 041081 GCh No. 13 (III-2) test Agency: MVS. Apogee: 1,350 km (830 mi). First test flight serial production model.
1959 March 25 - 05:25 GMT - Launch Vehicle: Soyuz. R-7 No. IZ-18 GCh No. 15 (III-3) test Agency: MVS. Apogee: 1,350 km (830 mi). R-7 development test flight. (GCh No. 15 (III-3))
1959 March 30 - 22:53 GMT - Launch Vehicle: Soyuz. R-7 No. IZ-20 FAILURE: Failure. GCh No. IZ-20 (III) test Agency: MVS. Apogee: 1,000 km (600 mi).
1959 May 9 - 18:59 GMT - Launch Vehicle: Soyuz. R-7 No. IZ-21 FAILURE: Failure. GCh No. 17 (III) test Agency: MVS. Apogee: 1,000 km (600 mi). R-7 development test flight. (GCh No. 17 (III))
1959 May 30 - 21:42 GMT - Launch Vehicle: Soyuz. R-7 No. IZ-22 FAILURE: Failure. GCh No. IZ-22 (III) test Agency: MVS. Apogee: 1,000 km (600 mi). Landed far from aim point.
1959 June 9 - 20:34 GMT - Launch Vehicle: Soyuz. FAILURE: Failure. GCh No. IZ-23 (III) test Agency: MVS. Apogee: 1,000 km (600 mi). Landed far from aim point.
1959 June 18 - Launch Vehicle: Soyuz. LV Model: Luna 8K72 . Vostok-L 8K72 I1-7 FAILURE: Inertial system failed at 153 seconds after launch. Vehicle destroyed by range safety. Luna failure - inertial system failed at T+153 seconds Spacecraft: Luna E-1A. Agency: MVS.
1959 July 18 - 18:15 GMT - Launch Vehicle: Soyuz. R-7 No. 24 GCh No. IZ-24 (III) test Agency: MVS. Apogee: 1,350 km (830 mi). R-7 development test flight. (GCh No. IZ-24 (III))
1959 July 30 - 04:00 GMT - Launch Vehicle: Soyuz. R-7 No. 041082 GCh (III) test Agency: MVS. Apogee: 1,350 km (830 mi). First successful flight of series production model.
1959 August 13 - 23:14 GMT - Launch Vehicle: Soyuz. GCh No. IZ-25 (III) test Agency: MVS. Apogee: 1,350 km (830 mi).
1959 September 12 - 06:39 GMT - Launch Vehicle: Soyuz. LV Model: Luna 8K72 . Vostok-L 8K72 I1-7B Luna 2 Mass: 387 kg (853 lb). Spacecraft: Luna E-1A. Agency: MVS. First probe to impact lunar surface. Delivered a pennant to the surface of the Moon and conducted research during flight to the Moon. Impacted Moon 13 Sep 1959 at 22:02:04 UT, Latitude 29.10 N, Longitude 0.00 - Palus Putredinis, east of Mare Serenitatis near the Aristides, Archimedes, and Autolycus craters. After launch and attainment of escape velocity, Luna 2 separated from its third stage, which travelled along with it towards the Moon. On 13 September the spacecraft released a bright orange cloud of sodium gas which aided in spacecraft tracking and acted as an experiment on the behavior of gas in space. On 14 September, after 33.5 hours of flight, radio signals from Luna 2 abruptly ceased, indicating it had impacted on the Moon. Some 30 minutes after Luna 2, the third stage of its rocket also impacted the Moon. The mission confirmed that the Moon had no appreciable magnetic field, and found no evidence of radiation belts at the Moon.
1959 September 18 - 16:02 GMT - Launch Vehicle: Soyuz. R-7 I1-1T Phase 3 test flight Agency: MVS. Apogee: 1,350 km (830 mi). R-7 development test flight.
1959 October 4 - 00:43 GMT - Launch Vehicle: Soyuz. LV Model: Luna 8K72 . Vostok-L 8K72 I1-8 Luna 3 Mass: 279 kg (615 lb). Spacecraft: Luna E-3. Agency: MVS. Luna 3 was the third spacecraft successfully launched to the Moon and the first to return images of the lunar far side. It was launched on a figure-eight trajectory which brought it over the Moon (closest approach to the Moon was 6200 km) and around the far side, which was sunlit at the time. It was stabilized while in optical view of the far side of the Moon. On October 7, 1959, the television system obtained a series of 29 photographs over 40 minutes, covering 70% of the surface, that were developed on-board the spacecraft. The photographs were scanned and 17 were radio transmitted to ground stations in facsimile form on October 18, 1959, as the spacecraft, in a barycentric orbit, returned near the Earth. The photographs were to be retransmitted at another point close to Earth but were not received. The spacecraft returned very indistinct pictures, but, through computer enhancement, a tentative atlas of the lunar farside was produced. These first views of the lunar far side showed mountainous terrain, very different from the near side, and two dark regions which were named Mare Moscovrae (Sea of Moscow) and Mare Desiderii (Sea of Dreams).
1959 October 22 - 17:30 GMT - Launch Vehicle: Soyuz. R-7 267432 Phase 3 test flight Agency: MVS. Apogee: 1,350 km (830 mi).
1959 October 25 - 17:32 GMT - Launch Vehicle: Soyuz. R-7 267434 Phase 3 test flight Agency: MVS. Apogee: 1,350 km (830 mi).
1959 November 1 - 21:23 GMT - Launch Vehicle: Soyuz. R-7 No. 267431 Phase 3 test flight Agency: MVS. Apogee: 1,350 km (830 mi). Flight over full missile design range.
1959 November 20 - 21:06 GMT - Launch Vehicle: Soyuz. R-7 I2-1T Phase 3 test flight Agency: MVS. Apogee: 1,350 km (830 mi). Flight over full missile design range.
1959 November 27 - 01:12 GMT - Launch Vehicle: Soyuz. R-7 267433 GCh No. IZ-33 (III) test Agency: MVS. Apogee: 1,350 km (830 mi). Sixteenth and last launch of the third production batch.
1959 December 23 - 19:05 GMT - Launch Vehicle: Soyuz. R-7A I1-1 R-7A I-1 test Agency: RVSN. Apogee: 1,350 km (830 mi).
1960 January 20 - 16:35 GMT - Launch Vehicle: Soyuz. R-7A I1-2 R-7A I-2/Dummy L test Agency: RVSN. Apogee: 1,000 km (600 mi). Suborbital aerodynamic test flight with R-7A 8K74 lower stages, dummy upper stages.
1960 January 24 - 16:15 GMT - Launch Vehicle: Soyuz. R-7A I1-3 FAILURE: Failure. R-7A I-3 test Agency: RVSN. Apogee: 20 km (12 mi).
1960 January 31 - 16:17 GMT - Launch Vehicle: Soyuz. R-7A I1-4 R-7A I-4/Dummy L test Agency: RVSN. Apogee: 1,000 km (600 mi). Suborbital aerodynamic test flight with R-7A 8K74 lower stages, dummy upper stages.
1960 March 17 - 23:55 GMT - Launch Vehicle: Soyuz. R-7A L1-5 R-7A I-4 test Agency: RVSN. Apogee: 1,350 km (830 mi).
1960 March 24 - 02:06 GMT - Launch Vehicle: Soyuz. R-7A I-5 test Agency: RVSN. Apogee: 1,350 km (830 mi).
1960 April 15 - Launch Vehicle: Soyuz. LV Model: Luna 8K72 . Vostok-L 8K72 L1-9 FAILURE: The third stage RO-5 engine either did not reach full thrust or shut down early. Luna failure - third stage insufficient delta V Spacecraft: Luna E-3. Agency: RVSN. Reached an altitude of 200,000 km before plunging back to earth.
1960 April 16 - 16:07 GMT - Launch Vehicle: Soyuz. LV Model: Luna 8K72 . Vostok-L 8K72 L1-9A FAILURE: Strap-on B reached only 75 percent of thrust at ignition. Four tenths of a second after liftoff it broke away from the core. Luna failure at lift-off Spacecraft: Luna E-3. Agency: RVSN. This dramatic failure resulted in a loss of thrust, and the lateral strap-on units separated and flew over the tracking stations and living areas. The core continued on its trajectory.
1960 May 15 - Launch Vehicle: Soyuz. Vostok 8K72 L1-11 Korabl-Sputnik 1 Mass: 2,500 kg (5,500 lb). Spacecraft: Vostok. Agency: RVSN. Perigee: 284 km (176 mi). Apogee: 514 km (319 mi). Inclination: 65.00 deg. Period: 92.50 min. The Soviet Union launched a Vostok 1KP prototype manned spacecraft (without heat shield; not recoverable) into near-earth orbit. Called Sputnik IV by the Western press. On May 19, at 15:52 Moscow time, the spacecraft was commanded to retrofire. However the guidance system had oriented the spacecraft incorrectly and the TDU engine instead put the spacecraft into a higher orbit. Soviet scientists said that conditions in the cabin, which had separated from the remainder of the spacecraft, were normal.
Officially: Development and checking of the main systems of the space ship satellite, which ensure its safe flight and control in flight, return to Earth and conditions needed for a man in flight.
1960 June 4 - 15:49 GMT - Launch Vehicle: Soyuz. R-7 L1-9 UBP (Readiness) operational test launch Agency: RVSN. Apogee: 1,350 km (830 mi). R-7 readiness verification test.
1960 July 5 - 15:56 GMT - Launch Vehicle: Soyuz. R-7A I-6 test Agency: RVSN. Apogee: 1,350 km (830 mi).
1960 July 7 - 15:27 GMT - Launch Vehicle: Soyuz. R-7A I-7 test Agency: RVSN. Apogee: 1,350 km (830 mi).
1960 July 28 - Launch Vehicle: Soyuz. Vostok 8K72 L1-10 FAILURE: At ignition one of the combustion chambers in strap on Block B or G burned through. The strap on separated from the core at 17 seconds into the flight and the launch vehicle exploded at 28.5 seconds. Korabl-Sputnik Spacecraft: Vostok. Agency: RVSN. First attempted flight of the Vostok 1K manned spacecraft prototype. Dogs Chaika and Lisichka perished in the explosion of the rocket.
1960 August 19 - 08:44 GMT - Launch Vehicle: Soyuz. Vostok 8K72 L1-12 Korabl-Sputnik 2 Mass: 1,440 kg (3,170 lb). Spacecraft: Vostok. Agency: RVSN. Perigee: 281 km (174 mi). Apogee: 340 km (210 mi). Inclination: 64.60 deg. Period: 90.70 min. The Soviet Union launched its second unmanned test of the Vostok spacecraft, the Korabl Sputnik II, or Sputnik V. The spacecraft carried two dogs, Strelka and Belka, in addition to a gray rabbit, rats, mice, flies, plants, fungi, microscopic water plants, and seeds. Electrodes attached to the dogs and linked with the spacecraft communications system, which included a television camera, enabled Soviet scientists to check the animals' hearts, blood pressure, breathing, and actions during the trip. After the spacecraft reentered and landed safely the next day, the animals and biological specimens were reported to be in good condition.
Officially: Development of systems ensuring man's life functions and safety in flight and his return to Earth.
1960 October 10 - 14:27 GMT - Launch Vehicle: Soyuz. Molniya 8K78 L1-4M FAILURE: At T+300.9 sec, the launcher went out of control and the destruct command was given at T+324.2 sec - the engine of Stage 3 cut off after 13.32 s of burning. Mars probe 1M s/n 1 failure. Mass: 640 kg (1,410 lb). Spacecraft: Mars 1M. Agency: RVSN. This was the Soviet Union's first attempt at a planetary probe. Mars probe intended to photograph Mars on a flyby trajectory. The possible cause lay in resonance vibrations of upper stages during Stage 2 burning, which led to break of contact in the command potentiometer of the gyrohorizon. As a result a pitch control malfunctioned and the launcher began to veer off the desired ascent profile. On exceeding 7 degrees of veering in pitch, the control system failed. The upper stage with the payload reached an altitude of 120 km before burning up on re-entry into the atmosphere above East Siberia.
1960 October 14 - 13:51 GMT - Launch Vehicle: Soyuz. Molniya 8K78 L1-5M FAILURE: At T+290 sec Stage 3's engine 8D715K failed to ignite because a LOX leak froze kerosene in the fuel inlet to the pump on the launch pad due to a faulty LOX valve seal. Mars probe 1M s/n 2 failure. Spacecraft: Mars 1M. Agency: RVSN. Mars probe intended to photograph Mars on a flyby trajectory. This was the Soviet Union's second attempt at a planetary probe. The upper stages and payload broke up on re-entry into the atmosphere.
1960 December 1 - 07:30 GMT - Launch Vehicle: Soyuz. Vostok 8K72 L1-13 Korabl-Sputnik 3 Mass: 4,563 kg (10,059 lb). Spacecraft: Vostok. Agency: RVSN. Perigee: 123 km (76 mi). Apogee: 269 km (167 mi). Inclination: 65.00 deg. Period: 88.40 min. The Soviet Union launched its third spaceship satellite, Korabl Sputnik III, or Sputnik VI. The spacecraft, similar to those launched on May 15 and August 19, carried the dogs Pcheka and Mushka in addition to other animals, insects, and plants. Deorbited December 2, 1960 7:15 GMT. Burned up on reentry due to steep entry angle (retrofire engine did not shut off on schedule and burned to fuel depletion).
Officially: Medical and biological research under space flight conditions.
Officially: Medical and biological research under space flight conditions.
1960 December 22 - Launch Vehicle: Soyuz. Vostok 8K72K L1-13A FAILURE: The third stage engine RO-7 failed just after ignition, 425 seconds in to flight. Korabl-Sputnik Spacecraft: Vostok. Agency: RVSN. Unable to reach orbital velocity, the Vostok prototype separated while the third stage was still firing. While the ejection seat failed to operate, the capsule did make a hard landing in severe winter conditons in Siberia. It was recovered after some time, and the dogs Kometa and Shutka were alive. As a result of this flight the ejection seat was developed with a heat shield designed to protect the pilot in the event of a launch vehicle failure up to shut down of the first stage. Additional Details: Korabl-Sputnik(5153).
1961 February 4 - 01:18 GMT - Launch Vehicle: Soyuz. Molniya 8K78 L1-7 FAILURE: At T+531 sec, the fourth vernier chamber of Stage 3's 8D715K engine exploded because the LOX cut-off valve had not closed as scheduled and LOX flowed into the hot chamber. Sputnik 7 Mass: 6,483 kg (14,292 lb). Spacecraft: Venera 1VA. Agency: RVSN. Perigee: 212 km (131 mi). Apogee: 318 km (197 mi). Inclination: 64.90 deg. Period: 89.80 min. The escape stage entered parking orbit but the main engine cut off just 0.8 s after ignition due to cavitation in the oxidiser pump and pump failure.. The payload attached together with escape stage remained in Earth orbit.
The booster launched into a beautiful clear sky, and it could be followed by the naked eye for four minutes after launch. The third stage reached earth parking orbit, but the fourth stage didn't ignite. It was at first believed a radio antenna did not deploy from the interior of the stage, and it did not receive the ignition commands. Therefore the Soviet Union has successfully orbited a record eight-tonne 'Big Zero' into orbit. The State Commission meets two hours after the launch, and argues whether to make the launch public or not, and how to announce it. Glushko proposes the following language for a public announcement: 'with the objective of developing larger spacecraft, a payload was successfully orbited which provided on the first revolution the necessary telemetry'. Korolev and the others want to minimize any statement, to prevent speculation that it was a reconnaissance satellite or a failed manned launch. Kamanin's conclusion - the rocket didn't reach Venus, but it did demonstrated a new rocket that could deliver an 8 tonne thermonuclear warhead anywhere on the planet. The commission heads back to Moscow.
1961 February 12 - 00:34 GMT - Launch Vehicle: Soyuz. Molniya 8K78 L1-6B Venera 1 Mass: 644 kg (1,419 lb). Spacecraft: Venera 1VA. Agency: RVSN. Venera 1 was the first spacecraft to fly by Venus. The 6424 kg assembly was launched first into a 229 x 282 km parking orbit, then boosted toward Venus by the restartable Molniya upper stage. On 19 February, 7 days after launch, at a distance of about two million km from Earth, contact with the spacecraft was lost. On May 19 and 20, 1961, Venera 1 passed within 100,000 km of Venus and entered a heliocentric orbit. This failure resulted in only the following objectives being met: checking of methods of setting space objects on an interplanetary course; checking of extra-long-range communications with and control of the space station; more accurate calculation of the dimension of the solar system; a number of physical investigations in space. Additional Details: Venera 1(64).
1961 March 9 - 06:29 GMT - Launch Vehicle: Soyuz. Vostok 8K72K E103-14 Korabl-Sputnik 4 Mass: 4,700 kg (10,300 lb). Spacecraft: Vostok. Agency: RVSN. Perigee: 173 km (107 mi). Apogee: 239 km (148 mi). Inclination: 64.90 deg. Period: 88.60 min. Flight: Vostok 1. Carried dog Chernushka, mannequin Ivan Ivanovich, and other biological specimens. Ivanovich was ejected from the capsule and recovered by parachute, and Chernsuhka was successfully recovered with the capsule on March 9, 1961 8:10 GMT.
Officially: Development of the design of the space ship satellite and of the systems on board, which ensure necessary conditions for man's flight.
Additional Details: Korabl-Sputnik 4(79).
1961 March 25 - 05:54 GMT - Launch Vehicle: Soyuz. Vostok 8K72K E103-15 Korabl-Sputnik 5 Mass: 4,695 kg (10,350 lb). Spacecraft: Vostok. Agency: RVSN. Perigee: 175 km (108 mi). Apogee: 175 km (108 mi). Inclination: 64.90 deg. Period: 88.00 min. Flight: Vostok 1. Carried dog Zvezdochka and mannequin Ivan Ivanovich. Ivanovich was again ejected from the capsule and recovered by parachute, and Zvezdochka was successfully recovered with the capsule on March 25, 1961 7:40 GMT.
Officially: Development of the design of the space ship satellite and of the systems on board, designed to ensure man's life functions during flight in outer space and return to Earth.
Additional Details: Korabl-Sputnik 5(65).
1961 April 12 - 06:07 GMT - Launch Vehicle: Soyuz. Vostok 8K72K E103-16 Vostok 1 Mass: 4,725 kg (10,416 lb). Spacecraft: Vostok. Agency: RVSN. Perigee: 169 km (105 mi). Apogee: 315 km (195 mi). Inclination: 65.00 deg. Period: 89.30 min. Crew: Gagarin. Flight: Vostok 1. First manned spaceflight, one orbit of the earth. Three press releases were prepared, one for success, two for failures. It was only known ten minutes after burnout, 25 minutes after launch, if a stable orbit had been achieved.
The payload included life-support equipment and radio and television to relay information on the condition of the pilot. The flight was automated; Gagarin's controls were locked to prevent him from taking control of the ship. The combination to unlock the controls was available in a sealed envelope in case it became necessary to take control in an emergency. After retrofire, the service module remained attached to the Sharik reentry sphere by a wire bundle. The joined craft went through wild gyrations at the beginning of re-entry, before the wires burned through. The Sharik, as it was designed to do, then naturally reached aerodynamic equilibrium with the heat shield positioned correctly.
Gagarin ejected after re-entry and descended under his own parachute, as was planned. However for many years the Soviet Union denied this, because the flight would not have been recognized for various FAI world records unless the pilot had accompanied his craft to a landing. Recovered April 12, 1961 8:05 GMT. Landed Southwest of Engels Smelovka, Saratov. Additional Details: Vostok 1(68).
1961 August 6 - 06:00 GMT - Launch Vehicle: Soyuz. Vostok 8K72K E103-17 Vostok 2 Mass: 4,730 kg (10,420 lb). Spacecraft: Vostok. Agency: RVSN. Perigee: 172 km (106 mi). Apogee: 221 km (137 mi). Inclination: 64.80 deg. Period: 88.40 min. Crew: Titov. Flight: Vostok 2. Second manned orbital flight. The Soviet Union successfully launched Vostok II into orbit with Gherman S. Titov as pilot. The spacecraft carried life-support equipment, radio and television for monitoring the condition of the cosmonaut, tape recorder, telemetry system, biological experiments, and automatic and manual control equipment. Flight objectives: Investigation of the effects on the human organism of a prolonged flight in orbit and subsequent return to the surface of the Earth; investigation of man's ability to work during a prolonged period of weightlessness. Titov took manual control of spacecraft but suffered from space sickness. He was equipped with a professional quality Konvas movie camera, with which ten minutes of film of the earth were taken through the porthole. Both television and film images were taken of the interior of the spacecraft. Like Gagarin, Titov experienced problems with separation of the service module after retrofire. Titov was never to fly again, after being assigned to the Spiral spaceplane, which turned out to be a dead-end project. A biography of him by Martin Caidin ('I Am Eagle') made him somewhat more accessible than Gagarin to the West.
1961 December 11 - 09:39 GMT - Launch Vehicle: Soyuz. FAILURE: RO-7 engine of block E upper stage cutoff prematurely. Spacecraft liquidated by self destruct system APO in 407th second of flight. Debris landed 100 km north of Vilyuisk. Zenit-2 11F61 s/n 1 Mass: 4,610 kg (10,160 lb). Spacecraft: Zenit-2. Agency: RVSN. First attempted launch of Zenit photo-reconnaisance satellite. According to Kamanin, there was a problem with the third stage, and the capsule landed between Novosibirsk and Yakutsk, but could not be located. There was no information on the nature of the problem. Korolev stayed at Tyuratam, preparing for the next launch attempt.
1962 April 26 - 10:02 GMT - Launch Vehicle: Soyuz. Cosmos 4 Mass: 4,610 kg (10,160 lb). Spacecraft: Zenit-2. Agency: RVSN. Perigee: 285 km (177 mi). Apogee: 317 km (196 mi). Inclination: 65.00 deg. Period: 90.50 min. Flight: Vostok 3, Vostok 4. Area survey photo reconnaissance satellite. Program partially completed. Failure of primary spacecraft orientation system. It was to spend four days in space, to be followed by another mission during 5-10 May. This meant that Vostok 3/4 could not be launched before 20-30 May. The cosmonaut prime crew returned from their in-suit parachute training at Fedosiya.
1962 June 1 - 09:38 GMT - Launch Vehicle: Soyuz. Vostok 8A92 E15000-01 FAILURE: Shutdown of Block B strap-on engine stage 1.8 seconds after liftoff. The booster crashed 300 m from the pad. Pad damaged. Zenit-2 11F61 s/n 3 Mass: 4,610 kg (10,160 lb). Spacecraft: Zenit-2. Agency: RVSN. Area survey photo reconnaissance satellite. Third attempted launch of Zenit photo-reconnaissance satellite. It blew up 300 m from the pad, and did enough damage to put the launch complex out of operation for a month. Therefore the Vostok 3/4 launches could not take place until the end of July at the earliest.
1962 July 28 - 09:18 GMT - Launch Vehicle: Soyuz. Vostok 8A92 T15000-07 Cosmos 7 Mass: 4,610 kg (10,160 lb). Spacecraft: Zenit-2. Agency: RVSN. Perigee: 197 km (122 mi). Apogee: 356 km (221 mi). Inclination: 64.90 deg. Period: 90.00 min. Area survey photo reconnaissance satellite. Also performed radiation measurements.
1962 August 11 - 08:30 GMT - Launch Vehicle: Soyuz. Vostok 3 Mass: 4,722 kg (10,410 lb). Spacecraft: Vostok. Agency: RVSN. Perigee: 166 km (103 mi). Apogee: 218 km (135 mi). Inclination: 65.00 deg. Period: 88.30 min. Crew: Nikolayev. Flight: Vostok 3. Joint flight with Vostok 4. The first such flight, where Vostok capsules were launched one day apart, coming within a few kilometers of each other at the orbital insertion of the second spacecraft. The flight was supposed to occur in March, but following various delays, one of the two Vostok pads was damaged in the explosion of the booster of the third Zenit-2 reconnsat in May. Repairs were not completed until August. Vostok 3 studied man's ability to function under conditions of weightlessness; conducted scientific observations; furthered improvement of space ship systems, communications, guidance and landing. Immediately at orbital insertion of Vostok 4, the spacecraft were less than 5 km apart. Popovich made radio contact with Cosmonaut Nikolayev. Nikolayev reported shortly thereafter that he had sighted Vostok 4. Since the Vostok had no maneuvering capability, they could not rendezvous or dock, and quickly drifted apart. The launches did allow Korolev to offer something new and different, and gave the launch and ground control crews practice in launching and handling more than one manned spacecraft at a time. The cosmonaut took colour motion pictures of the earth and the cabin interior. Additional Details: Vostok 3(93).
1962 August 12 - 08:02 GMT - Launch Vehicle: Soyuz. Vostok 4 Mass: 4,728 kg (10,423 lb). Spacecraft: Vostok. Agency: RVSN. Perigee: 159 km (98 mi). Apogee: 211 km (131 mi). Inclination: 65.00 deg. Period: 88.20 min. Crew: Popovich. Flight: Vostok 4. Joint flight with Vostok 3. Acquisition of experimental data on the possibility of establishing a direct link between two space ships; coordination of astronauts' operations; study of the effects of identical spaceflight conditions on the human organism. The launch of Popovich proceeds exactly on schedule, the spacecraft launching with 0.5 seconds of the planned time, entering orbit just a few kilometers away from Nikolayev in Vostok 3. Popovich had problems with his life support system, resulting in the cabin temperature dropping to 10 degrees Centigrade and the humidity to 35%. The cosmonaut still managed to conduct experiments, including taking colour motion pictures of the terminator between night and day and the cabin interior.
Despite the conditions, Popovich felt able to go for the full four days scheduled. But before the mission, Popovich had been briefed to tell ground control that he was 'observing thunderstorms' if he felt the motion sickness that had plagued Titov and needed to return on the next opportunity. Unfortunately he actually did report seeing thunderstorms over the Gulf of Mexico, and ground control took this as a request for an early return. He was ordered down a day early, landing within a few mintutes of Nikolayev. Only on the ground was it discovered that he was willing to go the full duration, and that ground control had thought he had given the code.
1962 August 25 - 02:18 GMT - Launch Vehicle: Soyuz. Molniya 8K78 T103-12 FAILURE: At T+60 min 50 sec one of the four solid motors of the escape stage's BOZ unit did not fire. The resulting asymmetric torque caused the stage to lose correct attitude and three seconds after ignition of the main engine S1.5400A1 it began to tumble. Sputnik 19 Mass: 890 kg (1,960 lb). Spacecraft: Mars 2MV-1. Agency: RVSN. Perigee: 173 km (107 mi). Apogee: 252 km (156 mi). Inclination: 64.90 deg. Period: 88.70 min. Attempt to launch a probe towards Mars. The launch went well, but the fourth stage motor burnt for only 45s of the planned 240s. The stage remained in Earth orbit. However Kamanin notes that it was good that the launch of the basic vehicle was a success - it gave the visiting female cosmonauts confidence in the rocket they will have to ride.
1962 September 1 - 02:12 GMT - Launch Vehicle: Soyuz. Molniya 8K78 T103-13 FAILURE: At T+ 61 min 30 sec the fuel valve did not open.; the ignition command was blocked from going to the main engine of Stage 4. Sputnik 20 Mass: 6,500 kg (14,300 lb). Spacecraft: Mars 2MV-1. Agency: RVSN. Perigee: 185 km (114 mi). Apogee: 246 km (152 mi). Inclination: 64.70 deg. Period: 88.80 min.
1962 September 12 - 00:59 GMT - Launch Vehicle: Soyuz. Molniya 8K78 T103-14 FAILURE: At T+531 sec, the fourth vernier chamber of Stage 3's 8D715K engine exploded because the LOX cut-off valve had not closed as scheduled and LOX flowed into the hot chamber. Sputnik 21 Mass: 6,500 kg (14,300 lb). Spacecraft: Mars 2MV-2. Agency: RVSN. Perigee: 179 km (111 mi). Apogee: 218 km (135 mi). Inclination: 64.90 deg. Period: 88.40 min. The escape stage entered parking orbit but the main engine cut off just 0.8 s after ignition due to cavitation in the oxidiser pump and pump failure.
1962 September 27 - 09:39 GMT - Launch Vehicle: Soyuz. Vostok 8A92 T15000-06 Cosmos 9 Mass: 4,700 kg (10,300 lb). Spacecraft: Zenit-2. Agency: RVSN. Perigee: 829 km (515 mi). Apogee: 981 km (609 mi). Inclination: 67.60 deg. Period: 103.10 min. Area survey photo reconnaissance satellite. Also performed radiation measurements.
1962 October 17 - 09:00 GMT - Launch Vehicle: Soyuz. Vostok 8A92 T15000-03 Cosmos 10 Mass: 4,700 kg (10,300 lb). Spacecraft: Zenit-2. Agency: RVSN. Perigee: 178 km (110 mi). Apogee: 376 km (233 mi). Inclination: 64.90 deg. Period: 90.00 min. Area survey photo reconnaissance satellite. Also performed radiation measurements.
1962 October 24 - 17:55 GMT - Launch Vehicle: Soyuz. Molniya 8K78 T103-15 FAILURE: 16 seconds after ignition of Stage 4, Block L's S1.5400A1 engine exploded. A lubricant leak resulted in the jamming of a shaft in the turbopump gearbox and break up of the turbine. Sputnik 22 Mass: 6,500 kg (14,300 lb). Spacecraft: Mars 2MV-4. Agency: RVSN. Perigee: 202 km (125 mi). Apogee: 260 km (160 mi). Inclination: 65.10 deg. Period: 89.10 min. Mars probe intended to photograph Mars on a flyby trajectory. The spacecraft broke into many pieces, some of which apparently remained in Earth orbit for a few days. This occurred during the Cuban missile crisis and was picked up by U.S. military radar installations, who originally feared it might by the start of a Soviet nuclear attack.
1962 November 1 - 16:14 GMT - Launch Vehicle: Soyuz. Molniya 8K78 T103-16 Mars 1 Mass: 894 kg (1,970 lb). Spacecraft: Mars 2MV-4. Agency: RVSN. Mars probe intended to photograph Mars on a flyby trajectory. Launched from Sputnik 23 in a 157 x 238 km, 65 degree parking orbit. Sixty-one radio transmissions were held in which a large amount of data was collected. On March 21, 1963, when the spacecraft was at a distance of 106 million km communications ceased, possibly due to a malfunction in the spacecraft orientation system. Mars 1 closest approach to Mars occurred on June 19, 1963 at a distance of approximately 193,000 km, after which the spacecraft entered a heliocentric orbit. Announced mission: Prolonged exploration of outer space during flight to the planet Mars; establishment of inter-planetary radio communications; photgraphing of the planet Mars and subsquent radio-transmission to Earth of the photographs of the surface of Mars thus obtained.
1962 November 4 - 15:35 GMT - Launch Vehicle: Soyuz. Molniya 8K78 T103-17 FAILURE: After T+260 sec, a malfunction of the pressurization system of the central sustainer led to cavitation in the oxidizer pipeline and LOX pump, followed at T+292s by the fuel pump. Sputnik 24 Mass: 890 kg (1,960 lb). Spacecraft: Mars 2MV-3. Agency: RVSN. Perigee: 170 km (100 mi). Apogee: 170 km (100 mi). Inclination: 64.80 deg. Period: 87.90 min. Mars probe intended to make a soft landing on Mars. Although the escape stage and payload reached orbit, the strong third stage vibrations shook a fuse loose from its mount in the main nozzle of the escape stage Block L's engine. The engine could not be ignited and remained in Earth orbit. It decayed about two months after insertion.
1962 December 22 - 09:23 GMT - Launch Vehicle: Soyuz. Vostok 8A92 T15000-10 Cosmos 12 Mass: 4,700 kg (10,300 lb). Spacecraft: Zenit-2. Agency: RVSN. Perigee: 202 km (125 mi). Apogee: 385 km (239 mi). Inclination: 64.80 deg. Period: 90.40 min. Area survey photo reconnaissance satellite. Also performed radiation measurements.
1963 January 4 - 08:49 GMT - Launch Vehicle: Soyuz. Molniya 8K78/E6 T103-09 FAILURE: The escape stage's BOZ unit failed to operate due to failure of a DC transformer of the power system. The stage with payload remained in Earth orbit. Sputnik 25 Spacecraft: Luna E-6. Agency: NII-88. Perigee: 165 km (102 mi). Apogee: 189 km (117 mi). Inclination: 64.60 deg. Period: 88.00 min.
1963 February 3 - 09:29 GMT - Launch Vehicle: Soyuz. Molniya 8K78/E6 G103-10 FAILURE: Upper stage gyro platform failure. E-6 s/n 2 failure. Spacecraft: Luna E-6. Agency: RVSN. Apparent causes were instabilities in the torque sensor circuit and the pitch-free floating gyro device. The upper stages and payload broke up on re-entry into the atmosphere over the Pacific.
1963 March 21 - 08:30 GMT - Launch Vehicle: Soyuz. Vostok 8A92 T15000-01 Cosmos 13 Mass: 4,700 kg (10,300 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 214 km (132 mi). Apogee: 303 km (188 mi). Inclination: 65.20 deg. Period: 89.60 min. Area survey photo reconnaissance satellite. Also performed radiation measurements.
1963 April 2 - 08:16 GMT - Launch Vehicle: Soyuz. Molniya 8K78/E6 G103-11 Luna 4 Mass: 1,422 kg (3,134 lb). Spacecraft: Luna E-6. Agency: RVSN. Perigee: 167 km (103 mi). Apogee: 182 km (113 mi). Inclination: 64.70 deg. Period: 87.98 min. Luna 4 was the second attempted Soviet unmanned lunar soft lander probe. The spacecraft, rather than being sent on a straight trajectory toward the Moon, was placed first in an earth parking orbit. The rocket stage then reignited and put the spaccecraft on a translunar trajectory. Failure of Luna 4 to make a required midcourse correction resulted in it missing the Moon by 8336.2 km on April 6, at 4:26 a.m. Moscow time. It thereafter entered a barycentric Earth orbit. The Soviet news agency, Tass, reported that data had been received from the spacecraft throughout its flight and that radio communication would continue for a few more days.
1963 April 22 - 08:30 GMT - Launch Vehicle: Soyuz. Vostok 8A92 T15000-08 Cosmos 15 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 194 km (120 mi). Apogee: 336 km (208 mi). Inclination: 65.00 deg. Period: 89.80 min. Area survey photo reconnaissance satellite. Also carried weather, radiation experiments.
1963 April 28 - 08:50 GMT - Launch Vehicle: Soyuz. Vostok 8A92 E15000-02 Cosmos 16 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 201 km (124 mi). Apogee: 379 km (235 mi). Inclination: 64.70 deg. Period: 90.30 min. Program partially completed. Part of the information lost due to failure of engine block stabilization system. Area survey photo reconnaissance satellite. Also performed radiation measurements.
1963 May 24 - 10:33 GMT - Launch Vehicle: Soyuz. Vostok 8A92 E15000-12 Cosmos 18 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 212 km (131 mi). Apogee: 269 km (167 mi). Inclination: 64.60 deg. Period: 89.30 min. Area survey photo reconnaissance satellite. Also performed radiation measurements.
1963 June 14 - 11:58 GMT - Launch Vehicle: Soyuz. Vostok 5 Mass: 4,720 kg (10,400 lb). Spacecraft: Vostok. Agency: NII-88. Perigee: 130 km (80 mi). Apogee: 131 km (81 mi). Inclination: 64.90 deg. Period: 87.10 min. Crew: Bykovsky. Flight: Vostok 5. Joint flight with Vostok 6. The Soviet Union launched Vostok 5, piloted by Lt. Col. Valery F. Bykovsky. Two days later Lt. Valentina V. Tereshkova, the first spacewoman, followed in Vostok 6. On its first orbit, Vostok 6 came within about five km of Vostok 5, the closest distance achieved during the flight, and established radio contact. Both cosmonauts landed safely on June 19. The space spectacular featured television coverage of Bykovsky that was viewed in the West as well as in Russia. Unlike earlier missions, only a black and white film camera was carried. Photometric measurements of the earth's horizon were made.
Mission objectives were officially: further study of the effect of various space-flight factors in the human organism; extensive medico-biological experiments under conditions of prolonged flight; further elaboration and improvement of spaceship systems.
Vostok 5 was originally planned to go for a record eight days. The launch was delayed repeatedly due to high solar activity and technical problems. Finally the spacecraft ended up in a lower than planned orbit. Combined with increased atmospheric activity due to solar levels, Vostok 5 quickly decayed temperatures in the service module reached very high levels.
Bykovsky also experienced an unspecified problem with his waste management system (a spill?) which made conditions in the cabin 'very uncomfortable'. He was finally ordered to return after only five days in space.
To top it all off, once again the Vostok service module failed to separate cleanly from the reentry sphere. Wild gyrations ensued until the heat of reentry burned through the non-separating retraining strap.
1963 June 16 - 09:29 GMT - Launch Vehicle: Soyuz. Vostok 6 Mass: 4,713 kg (10,390 lb). Spacecraft: Vostok. Agency: NII-88. Perigee: 165 km (102 mi). Apogee: 166 km (103 mi). Inclination: 64.90 deg. Period: 87.80 min. Crew: Tereshkova. Flight: Vostok 6. Joint flight with Vostok 5. First woman in space, and the only Russian woman to go into space until Svetlana Savitskaya 19 years later. On its first orbit, Vostok 6 came within about five km of Vostok 5, the closest distance achieved during the flight, and established radio contact. Flight objectives included: Comparative analysis of the effect of various space-flight factors on the male and female organisms; medico-biological research; further elaboration and improvement of spaceship systems under conditions of joint flight. It was Korolev's idea just after Gagarin's flight to put a woman into space as yet another novelty. Khrushchev made the final crew selection. Korolev was unhappy with Tereshkova's performance in orbit and she was not permitted to take manual control of the spacecraft as had been planned.
1963 July 10 - Launch Vehicle: Soyuz. Vostok 8A92 E15000-04 FAILURE: Shutdown of Block B strap-on engine stage 1.9 seconds after liftoff. Pad damaged. Zenit-2 11F61 s/n 12 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: RVSN. Area survey photo reconnaissance satellite.
1963 October 18 - 09:29 GMT - Launch Vehicle: Soyuz. Vostok 8A92 G15001-01 Cosmos 20 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 201 km (124 mi). Apogee: 296 km (183 mi). Inclination: 64.80 deg. Period: 89.40 min. Area survey photo reconnaissance satellite.
1963 November 11 - 06:23 GMT - Launch Vehicle: Soyuz. Molniya 8K78 G103-18 FAILURE: During unpowered coast in parking orbit the escape stage Block L lost stable attitude. Engine ignition occurred in an incorrect direction. Cosmos 21 Mass: 890 kg (1,960 lb). Spacecraft: Venera 3MV-1A. Agency: NII-88. Perigee: 192 km (119 mi). Apogee: 231 km (143 mi). Inclination: 64.80 deg. Period: 88.70 min. The stage with payload remained in Earth orbit as Cosmos-51 and burnt up on re-entry.
1963 November 16 - 10:34 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 G15000-06 Cosmos 22 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: NII-88. Perigee: 193 km (119 mi). Apogee: 376 km (233 mi). Inclination: 64.90 deg. Period: 90.20 min. High resolution photo reconnaissance satellite; returned film capsule
1963 November 28 - Launch Vehicle: Soyuz. Vostok 8A92 G15001-02 FAILURE: Failure of block E upper stage. Spacecraft liquidated by APO destruct system. Zenit-2 11F61 s/n 14 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: RVSN. Area survey photo reconnaissance satellite.
1963 December 19 - 09:28 GMT - Launch Vehicle: Soyuz. Vostok 8A92 G15001-03 Cosmos 24 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: NII-88. Perigee: 204 km (126 mi). Apogee: 391 km (242 mi). Inclination: 65.00 deg. Period: 90.50 min. Area survey photo reconnaissance satellite.
1964 January 30 - 09:45 GMT - Launch Vehicle: Soyuz. Elektron 1 Mass: 329 kg (725 lb). Spacecraft: Elektron-A. Agency: NII-88. Perigee: 413 km (256 mi). Apogee: 6,439 km (4,001 mi). Inclination: 60.90 deg. Period: 161.00 min. Studied inner Van Allen belt. Electron I and II launched by a single carrier rocket. Electron I: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and upper atmosphere. Electron II: simultaneous study of the Earth's inner and outer radiation belts, cosmic rays and outer space.
1964 February 19 - 05:47 GMT - Launch Vehicle: Soyuz. Molniya 8K78M T15000-19 FAILURE: Second stage failure. 3MV-1A Mass: 890 kg (1,960 lb). Spacecraft: Venera 3MV-1A. Agency: RVSN.
1964 March 21 - 08:15 GMT - Launch Vehicle: Soyuz. Molniya 8K78M T15000-20 FAILURE: Failure. Luna failure Spacecraft: Luna E-6. Agency: RVSN. The upper stages burnt on re-entry into the atmosphere.
1964 March 27 - 03:24 GMT - Launch Vehicle: Soyuz. Molniya 8K78M T15000-22 FAILURE: During unpowered coast in parking orbit the escape stage Block L lost stable attitude due to a loss of the power circuit of the pneumatic valves of the attitude control and stabilization system. Cosmos 27 Mass: 890 kg (1,960 lb). Spacecraft: Venera 3MV-1. Agency: NII-88. Perigee: 197 km (122 mi). Apogee: 209 km (129 mi). Inclination: 64.80 deg. Period: 88.50 min. The stage with payload remained in Earth orbit as Cosmos-27.
1964 April 2 - 02:42 GMT - Launch Vehicle: Soyuz. Molniya 8K78M T15000-23 Zond 1 Mass: 890 kg (1,960 lb). Spacecraft: Venera 3MV-1. Agency: NII-88. Failed Venus probe. Solar Orbit (Heliocentric). Elaboration of a long range space system and conduct of scientific research.
1964 April 20 - 08:08 GMT - Launch Vehicle: Soyuz. Molniya 8K78M T15000-21 FAILURE: Power failure caused upper stage shutdown at T+340 seconds. Luna failure Spacecraft: Luna E-6. Agency: RVSN. The upper stages broke up on re-entry into the atmosphere..
1964 May 18 - 09:50 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 G15000-12 Cosmos 30 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: NII-88. Perigee: 206 km (128 mi). Apogee: 366 km (227 mi). Inclination: 64.90 deg. Period: 90.30 min. High resolution photo reconnaissance satellite; returned film capsule
1964 June 4 - Launch Vehicle: Soyuz. Molniya 8K78 R103-34 FAILURE: At T+104 sec the tank draining of core Block A failed due to jamming of the servo-motored throttle and break down of the motor's circuit The launcher was destroyed on impact downrange from the pad. Molniya-1 s/n 2 Failure Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: RVSN. Unsuccessful first attempt to launch Molniya communications satellite.
1964 July 1 - 11:16 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 T15000-04 Cosmos 34 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: NII-88. Perigee: 201 km (124 mi). Apogee: 342 km (212 mi). Inclination: 64.90 deg. Period: 89.90 min. High resolution photo reconnaissance satellite; returned film capsule
1964 July 10 - 21:51 GMT - Launch Vehicle: Soyuz. Elektron 3 Mass: 350 kg (770 lb). Spacecraft: Elektron-A. Agency: NII-88. Perigee: 408 km (253 mi). Apogee: 6,302 km (3,915 mi). Inclination: 60.90 deg. Period: 159.30 min. Studied inner Van Allen belt. Electron 3 and 4 launched by a single carrier rocket. Simultaneous study of the inner and outer radiation belts of the earth, cosmic rays and the upper atmosphere.
1964 August 22 - 07:12 GMT - Launch Vehicle: Soyuz. Molniya 8K78 R103-36 Cosmos 41 Mass: 1,500 kg (3,300 lb). Spacecraft: Molniya-1. Agency: NII-88. Perigee: 1,023 km (635 mi). Apogee: 39,169 km (24,338 mi). Inclination: 68.40 deg. Period: 714.50 min. Successful launch of first Soviet communications satellite. This is the second Molniya launch attempt. (the first was a launch failure). The failure of the antennae to deploy means the spacecraft can only be tested in a limited manner and cannot be used for the planned relay of television.
1964 September 13 - 09:50 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 R15001-01 Cosmos 45 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: NII-88. Perigee: 203 km (126 mi). Apogee: 311 km (193 mi). Inclination: 64.90 deg. Period: 89.60 min. Flight: Voskhod 1. High resolution photo reconnaissance satellite; returned film capsule; also carried weather experiments. The Zenit-4 launches a day ahead of schedule. The booster rocket performs perfectly as Korolev and Kamanin watch from the veranda of the IP-1 tracking station. This confirms readiness of the same launch vehicle for the Voskhod launch.
1964 October 6 - 07:12 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 R15000-02 Cosmos 47 Mass: 5,320 kg (11,720 lb). Spacecraft: Voskhod. Agency: NII-88. Perigee: 174 km (108 mi). Apogee: 383 km (237 mi). Inclination: 64.60 deg. Period: 90.10 min. Flight: Voskhod 1. Unmanned test of Voskhod spacecraft. At 07:00 the State Commission meets at Area 2. All Chief Designers, Commanders, and Section report that all is ready for flight. The commission gives the order to proceed with the launch. Weather at the pad is 7 balls, 8-10 m/s wind with gusts to 15 m/s, temperature 9 to 12 deg C. Weather in the recovery zones is reported as winds up to 15 m/s. Weather in the recovery zone is not clear, but that is not considered an impediment, and in fact Kamanin would like to see how the landing system functions in bad conditions. Kamanin visits the pad at T-30 seconds; at T-20 seconds, the veranda at IP-1 has over 50 viewers of the launch, including 15 cosmonaut candidates and the 7 Voskhod cosmonauts. Kamanin is relegated to the IP-1 veranda this time, with Rudenko, Kirillov, and Tyulin the bunker adjacent to the pad. Korolev stays with the booster until T-5 minutes, then enters the bunker. The booster ignites precisely at 10:00; the strap-ons burn out and are jettisoned at T+120 seconds; the core burns out and the final stage ignites at T+290 seconds; and at T+523 seconds spacecraft 3KV number 2 is placed in orbit as the final stage shuts down. The spacecraft separates and all systems look normal.
Recovered October 7, 1964 7:28 GMT. Officially: Investigation of the upper atmosphere and outer space.
1964 October 12 - 07:30 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 R15000-04 Voskhod 1 Mass: 5,320 kg (11,720 lb). Spacecraft: Voskhod. Agency: NII-88. Perigee: 178 km (110 mi). Apogee: 336 km (208 mi). Inclination: 64.70 deg. Period: 89.60 min. Crew: Feoktistov, Komarov, Yegorov. Flight: Voskhod 1. The U.S.S.R. launched the world's first multi-manned spacecraft, Voskhod I, the first to carry a scientist and a physician into space. The crew were Col. Vladimir Komarov, pilot; Konstantin Feoktistov, scientist; and Boris Yegorov, physician. Potentially dangerous modification of Vostok to upstage American Gemini flights; no spacesuits, ejection seats, or escape tower. One concession was backup solid retrorocket package mounted on nose of spacecraft. Seats mounted perpendicular to Vostok ejection seat position, so crew had to crane their necks to read instruments, still mounted in their original orientation. Tested the new multi-seat space ship; investigated the in-flight work potential and co-operation of a group of cosmonauts consisting of specialists in different branches of science and technology; conducted scientific physico-technical and medico-biological research. The mission featured television pictures of the crew from space.
Coming before the two-man Gemini flights, Voskhod 1 had a significant worldwide impact. In the United States, the "space race" was again running under the green flag. NASA Administrator James E. Webb, commenting on the spectacular, called it a "significant space accomplishment." It was, he said, "a clear indication that the Russians are continuing a large space program for the achievement of national power and prestige." Additional Details: Voskhod 1(311).
1964 November 30 - 13:12 GMT - Launch Vehicle: Soyuz. Zond 2 Mass: 890 kg (1,960 lb). Spacecraft: Mars 3MV-4A. Agency: NII-88. Mars probe intended to photograph Mars on a flyby trajectory. Zond 2 was launched from an earth parking orbit towards Mars to test space-borne systems and to carry out scientific investigations. Zond 2 carried six electric rocket engines of plasma type that served as actuators of the attitude control system. The communications system failed during April 1965. The spacecraft flew by Mars on August 6, 1965, at a distance of 1500 km.
1965 March 12 - 09:30 GMT - Launch Vehicle: Soyuz. Molniya 8K78/E6 R103-25 FAILURE: The escape stage Block L's engine failed to ignite due to failure of a transformer in the power supply of the control system. Cosmos 60 Mass: 6,530 kg (14,390 lb). Spacecraft: Luna E-6. Agency: MOM. Perigee: 195 km (121 mi). Apogee: 248 km (154 mi). Inclination: 64.70 deg. Period: 88.90 min. The stage with the payload remained in Earth orbit as Kosmos-60.
1965 March 18 - 07:00 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 R15000-05 Voskhod 2 Mass: 5,682 kg (12,526 lb). Spacecraft: Voskhod. Agency: MOM. Perigee: 167 km (103 mi). Apogee: 475 km (295 mi). Inclination: 64.80 deg. Period: 90.90 min. Crew: Belyayev, Leonov. Flight: Voskhod 2. First spacewalk, with a two man crew of Colonel Pavel Belyayev and Lt. Colonel Aleksey Leonov. During Voskhod 2's second orbit, Leonov stepped from the vehicle and performed mankind's first "walk in space." After 10 min of extravehicular activity, he returned safely to the spacecraft through an inflatable airlock.
This mission was originally named 'Vykhod ('Exit/Advance'). It almost ended in disaster when Leonov was unable to reenter the airlock due to stiffness of the inflated spacesuit. He had to bleed air from the suit in order to get into the airlock. After Leonov finally managed to get back into the spacecraft cabin, the primary hatch would not seal completely. The environmental control system compensated by flooding the cabin with oxygen, creating a serious fire hazard in a craft only qualified for sea level nitrogen-oxygen gas mixes (Cosmonaut Bondarenko had burned to death in a ground accident in such circumstances, preceding the Apollo 204 disaster by many years). Additional Details: Voskhod 2(387).
1965 April 10 - Launch Vehicle: Soyuz. Molniya 8K78 R103-26 FAILURE: Stage 3's engine 8D715K failed due to depressurization of the nitrogen pipeline of the LOX tank pressurization system of Block I. Luna failure - stage 3 engine failure. Spacecraft: Luna E-6. Agency: RVSN. The upper stages fell apart on re-entry into the atmosphere..
1965 April 23 - 01:55 GMT - Launch Vehicle: Soyuz. Molniya 8K78 U103-35 Molniya 1-01 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 538 km (334 mi). Apogee: 39,300 km (24,400 mi). Inclination: 65.50 deg. Period: 707.30 min. First announced launch of Soviet communications satellite. Television programme transmission and long range two way multi channel telephone and telegraph communications. Orbital characteristics after correction of 2 May 1965.
1965 May 9 - 07:49 GMT - Launch Vehicle: Soyuz. Molniya 8K78M U103-30 Luna 5 Mass: 1,474 kg (3,249 lb). Spacecraft: Luna E-6. Agency: MOM. Perigee: 159 km (98 mi). Apogee: 219 km (136 mi). Inclination: 64.80 deg. Period: 88.27 min. Soft lunar landing attempt. The retrorocket system failed, and the spacecraft impacted the lunar surface at the Sea of Clouds. Western observers, among them England's Sir Bernard Lovell, correctly speculated that the craft's mission was a soft landing.
1965 June 8 - 07:40 GMT - Launch Vehicle: Soyuz. Molniya 8K78M U103-31 Luna 6 Mass: 1,440 kg (3,170 lb). Spacecraft: Luna E-6. Agency: MOM. Attempted unmanned lunar soft lander. Tass reported that all onboard equipment was functioning normally. Two days into the flight, however, the spacecraft's engine failed to shut down following a midcourse correction. This failure caused Luna 6 to miss its target by 159,612.8 Km.
1965 June 25 - 09:50 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 G15000-10 Cosmos 69 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 310 km (190 mi). Inclination: 64.90 deg. Period: 89.70 min. High resolution photo reconnaissance satellite; returned film capsule
1965 July 18 - 14:38 GMT - Launch Vehicle: Soyuz. Zond 3 Mass: 959 kg (2,114 lb). Spacecraft: Mars 3MV-4A. Agency: MOM. Zond 3 was towards the moon and interplanetary space. The spacecraft was equipped with a TV system that provided automatic inflight film processing. On July 20, during lunar flyby, 25 pictures of very good quality were taken of the lunar farside from distances of 11,570 to 9960 km. The photos covered 19,000,000 km square of the lunar surface. Photo transmissions by facsimile were returned to earth from a distance of 2,200,000 km on July 29 and were retransmitted later from a distance of 31,500,000 km, thus proving the ability of the communications system. After the lunar flyby, Zond 3 continued space exploration in a heliocentric orbit. Those pictures showed clearly the heavily cratered nature of the surface. This mission dramatized the advances in space photography that the U.S.S.R. had made since its first far-side effort six years earlier.
1965 August 25 - 10:19 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 R15001-06 Cosmos 79 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 338 km (210 mi). Inclination: 64.90 deg. Period: 89.90 min. High resolution photo reconnaissance satellite; returned film capsule
1965 October 4 - 07:56 GMT - Launch Vehicle: Soyuz. Molniya 8K78 U103-27 Luna 7 Mass: 1,504 kg (3,315 lb). Spacecraft: Luna E-6. Agency: MOM. Lunar soft landing attempt. The Luna 7 spacecraft was intended to achieve a soft landing on the Moon. However, due to premature retrofire and cutoff of the retrorockets, the spacecraft impacted the lunar surface in the Sea of Storms.
1965 October 14 - 19:40 GMT - Launch Vehicle: Soyuz. Molniya 8K78 U103-37 Molniya 1-02 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 487 km (302 mi). Apogee: 39,921 km (24,805 mi). Inclination: 65.20 deg. Period: 718.80 min. France - USSR communications link. Second communications satellite 'Molniya-1'. Television programme transmission and long-range, two-way multi-channel telephone, phototelegraph and telegraph communications.
1966 August 27 - 09:50 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 N15001-03 Cosmos 128 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 343 km (213 mi). Inclination: 64.90 deg. Period: 90.00 min. High resolution photo reconnaissance satellite; returned film capsule
1966 October 20 - 07:55 GMT - Launch Vehicle: Soyuz. Molniya 8K78M N103-40 Molniya 1-04 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 500 km (310 mi). Apogee: 39,689 km (24,661 mi). Inclination: 65.30 deg. Period: 714.40 min. Television programme transmission and long-range two-way multi-channel telephone, phototelegraph and telegraph communicaitons.
1966 December 21 - 10:17 GMT - Launch Vehicle: Soyuz. Molniya 8K78M N103-45 Luna 13 Mass: 1,700 kg (3,700 lb). Spacecraft: Luna E-6M. Agency: NII-88. Soft landed on Moon 24 December 1966 at 18:01:00 GMT, Latitude 18.87 N, 297.95 E - Oceanus Procellarum. The petal encasement of the spacecraft was opened, antennas were erected, and radio transmissions to Earth began four minutes after the landing. On December 25 and 26, 1966, the spacecraft television system transmitted panoramas of the nearby lunar landscape at different sun angles. Each panorama required approximately 100 minutes to transmit. The spacecraft was equipped with a mechanical soil-measuring penetrometer, a dynamograph, and a radiation densitometer for obtaining data on the mechanical and physical properties and the cosmic-ray reflectivity of the lunar surface. It is believed that transmissions from the spacecraft ceased before the end of December 1966.
1967 February 7 - 03:20 GMT - Launch Vehicle: Soyuz. Soyuz 11A511 U15000-03 Cosmos 140 Mass: 6,450 kg (14,210 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 169 km (105 mi). Apogee: 216 km (134 mi). Inclination: 51.60 deg. Period: 88.30 min. After the self-destruction of the first Soyuz 7K-OK on re-entry, and the loss of the second one on the pad fire in December, the state commission ruled that the third 7K-OK model would be flown unpiloted on a solo mission. If this was successful then the fourth and fifth Soyuz would be flown on a manned docking mission. Once in orbit Cosmos 140 experienced attitude control problems due to a faulty star sensor resulting in excessive fuel consumption. The spacecraft couldn't keep the required orientation towards the sun to keep the solar panels illuminated, and the batteries discharged. Despite all of these problems the spacecraft remained controllable. An attempted manoeuvre on the 22nd revolution still showed problems with the control system. It malfunctioned yet again during retrofire, leading to a steeper than planned uncontrolled ballistic re-entry. The re-entry capsule itself had depressurised on separation from the service module due to a fault in the base of the capsule. A 300 mm hole burned through in the heat shield during re-entry. Although such events would have been lethal to any human occupants, the capsule's recovery systems operated and the capsule crashed through the ice of the frozen Aral Sea, 3 km from shore and 500 kilometres short of the intended landing zone. The spacecraft finally sank in 10 meters of water and had to be retrieved by divers. Still, the mission was deemed 'good enough' for the next mission to be a manned two-craft docking and crew transfer space spectacular. Mishin and Kamanin felt that a human crew could have sorted out the problems. They were also under intense pressure to achieve a manned circumlunar flight before the 50th Anniversary of the Soviet Revolution in October.
1967 February 27 - 08:45 GMT - Launch Vehicle: Soyuz. Vostok 8A92 U15001-03 Cosmos 143 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 390 km (240 mi). Inclination: 64.90 deg. Period: 90.50 min. Placed into orbit with 22.8 second period different from that planned. Area survey photo reconnaissance satellite. Also carried science package.
1967 April 12 - 10:51 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 N15001-08 Cosmos 155 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 200 km (120 mi). Apogee: 267 km (165 mi). Inclination: 51.80 deg. Period: 89.20 min. High resolution photo reconnaissance satellite; returned film capsule
1967 April 23 - 00:35 GMT - Launch Vehicle: Soyuz. Soyuz 11A511 U15000-04 Soyuz 1 Mass: 6,450 kg (14,210 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 197 km (122 mi). Apogee: 223 km (138 mi). Inclination: 50.80 deg. Period: 88.70 min. Crew: Komarov. Flight: Soyuz 1, Soyuz 2A. Space disaster that put back Soviet lunar program 18 months. Soyuz 1 as active spacecraft was launched first. Soyuz 2, with a 3 man crew would launch the following day, with 2 cosmonauts spacewalking to Soyuz 1. However immediately after orbital insertion Komarov's problems started. One of the solar panels failed to deploy, staying wrapped around the service module. Although only receiving half of the planned solar power, an attempt was made to manoeuvre the spacecraft. This failed because of interference of the reaction control system exhaust with the ion flow sensors that were one of the Soyuz' main methods of orientation. Additional Details: Soyuz 1(712).
1967 May 12 - 10:30 GMT - Launch Vehicle: Soyuz. Cosmos 157 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 249 km (154 mi). Apogee: 262 km (162 mi). Inclination: 51.30 deg. Period: 89.60 min. Area survey photo reconnaissance satellite. Program partially completed. Bad quality film loaded into SA-20 camera.
1967 May 16 - 21:43 GMT - Launch Vehicle: Soyuz. Molniya 8K78M Ya716-56 Cosmos 159 Mass: 4,490 kg (9,890 lb). Spacecraft: Luna E-6LS. Agency: MOM. Perigee: 350 km (210 mi). Apogee: 60,637 km (37,678 mi). Inclination: 51.60 deg. Period: 1,174.20 min. Flight: Soyuz 7K-L1 mission 1. The E-6LS was a radio-equipped version of the E-6 used to test tracking and communications networks for the Soviet manned lunar program. The payload entered the desired orbit as Kosmos-159.
1967 May 24 - 22:50 GMT - Launch Vehicle: Soyuz. Molniya 1-05 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 90 km (55 mi). Apogee: 35,690 km (22,170 mi). Inclination: 64.60 deg. Period: 627.00 min. Further development and experimental operation of long-range two-way television and telephone-telegraph radio-communication.
1967 June 1 - 10:40 GMT - Launch Vehicle: Soyuz. Voskhod 11A57 Ya15001-11 Cosmos 162 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 196 km (121 mi). Apogee: 275 km (170 mi). Inclination: 51.80 deg. Period: 89.20 min. High resolution photo reconnaissance satellite; returned film capsule
1967 June 12 - 02:39 GMT - Launch Vehicle: Soyuz. Venera 4 Mass: 1,104 kg (2,433 lb). Spacecraft: Venera 1V (V-67). Agency: MOM. Venera 4 was successfully launched towards the planet Venus with the announced mission of direct atmospheric studies. On October 18, 1967, the descent vehicle entered the Venusian atmosphere. Signals were returned by the spacecraft, which deployed a parachute after braking to subsonic velocity in the Venusian atmosphere, until it reached an altitude of 24.96 km.
1967 June 17 - 02:36 GMT - Launch Vehicle: Soyuz. FAILURE: Stage 4's engine 11D33 failed to ignite because the turbopump had not been cooled before ignition. Cosmos 167 Mass: 1,106 kg (2,438 lb). Spacecraft: Venera 1V (V-67). Agency: MOM. Perigee: 211 km (131 mi). Apogee: 264 km (164 mi). Inclination: 51.80 deg. Period: 89.20 min. Suggestions for the cause of the failure included incorrect soldering of wires in multiple pin plugs, wrong attachments of the plugs to the pyrotechnic connectors, or a mix-up of the pyrotechnic connectors during assembly.. Investigation of the upper atmosphere and outer space.
1967 August 9 - 05:45 GMT - Launch Vehicle: Soyuz. Cosmos 172 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 277 km (172 mi). Inclination: 51.70 deg. Period: 89.30 min. High resolution photo reconnaissance satellite; returned film capsule
1967 August 31 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 174 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 430 km (260 mi). Apogee: 39,796 km (24,728 mi). Inclination: 64.90 deg. Period: 715.00 min. Probable commsat failure. Investigation of the upper atmosphere and outer space.
1967 September 16 - 06:06 GMT - Launch Vehicle: Soyuz. Cosmos 177 Mass: 4,720 kg (10,400 lb). Spacecraft: Zenit-2. Agency: MOM. Perigee: 201 km (124 mi). Apogee: 267 km (165 mi). Inclination: 51.70 deg. Period: 89.10 min. Area survey photo reconnaissance satellite.
1967 October 3 - 05:00 GMT - Launch Vehicle: Soyuz. Molniya 1-06 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 508 km (315 mi). Apogee: 39,709 km (24,673 mi). Inclination: 64.70 deg. Period: 714.90 min. Operation of a system of long range telephone-telegraph radiocommunication, and transmission of USSR Central Television programmes to the stations of the Orbita network.
1967 October 16 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 182 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 197 km (122 mi). Apogee: 374 km (232 mi). Inclination: 64.90 deg. Period: 90.20 min. High resolution photo reconnaissance satellite; returned film capsule
1967 October 22 - 08:40 GMT - Launch Vehicle: Soyuz. Molniya 1-07 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 508 km (315 mi). Apogee: 39,709 km (24,673 mi). Inclination: 64.80 deg. Period: 714.90 min. Operation of a system of long range telephone-telegraph radiocommunication, and transmission of USSR Central Television programmes to the stations of the Orbita network.
1967 October 30 - 08:12 GMT - Launch Vehicle: Soyuz. Cosmos 188 Mass: 6,530 kg (14,390 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 180 km (110 mi). Apogee: 247 km (153 mi). Inclination: 51.70 deg. Period: 88.70 min. Docking target craft for Cosmos 186, which achieved world's first automatic rendezvous on second attempt. Hard docking achieved but electric connections unsuccessful due to misallignment of spacecraft. Ion flow sensor failed and Cosmos 188 had to make a high-G uncontrolled re-entry. When it deviated too far off course, it was destroyed by the on-board self-destruct system,. However officially the Soviet Union reported that it landed succesfully on November 2, 1967 at 09:10 GMT, and that its mission was 'investigation of outer space, development of new systems and elements to be used in the construction of space devices'. Additional Details: Cosmos 188(662).
1968 February 6 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 201 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 334 km (207 mi). Inclination: 64.90 deg. Period: 89.90 min. High resolution photo reconnaissance satellite; returned film capsule
1968 February 7 - 10:43 GMT - Launch Vehicle: Soyuz. Molniya 8K78M Ya716-57 FAILURE: At T+524.6 sec Stage 3's engine 11D55 cut off prematurely because it ran out of fuel due to an excessive fuel consumption rate through the gas-generator. E-6LS s/n 112 Spacecraft: Luna E-6LS. Agency: RVSN. Flight: Soyuz 7K-L1 mission 1. Failed launch of an E-6LS radio-equipped version of the E-6 used to test tracking and communications networks for the Soviet manned lunar program. Suggestions for the abnormal consumption included the seizing up of a pintle valve for controlling fuel supply into the regulator or the seizing up of the fuel inlet control. The upper stages broke up in the atmosphere.
1968 March 21 - 09:50 GMT - Launch Vehicle: Soyuz. Cosmos 208 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 287 km (178 mi). Inclination: 64.90 deg. Period: 89.40 min. Area survey photo reconnaissance satellite; returned film capsule; deployed high energy gamma ray experiment capsule. First flight of modernised Zenit-2 area survey reconnaissance satellite.
1968 April 7 - 10:09 GMT - Launch Vehicle: Soyuz. Molniya 8K78M Ya716-58 Luna 14 Mass: 1,700 kg (3,700 lb). Spacecraft: Luna E-6LS. Agency: MOM. Lunar Orbiter; studied lunar gravitational field, Earth-Moon gravitational relationship, and conducted further scientific experiments in circumlunar space. Not revealed until years later was that the E-6LS was primarily intended to test tracking and communications networks for the Soviet manned lunar program. The Luna 14 spacecraft entered a 140 x 870 km x 42 degree lunar orbit on April 10, 1966. The spacecraft instrumentation was similar to that of Luna 10 and provided data for studies of the interaction of the earth and lunar masses, the lunar gravitational field, the propagation and stability of radio communications to the spacecraft at different orbital positions, solar charged particles and cosmic rays, and the motion of the Moon. This flight was the final flight of the second generation of the Luna series.
1968 April 15 - 09:34 GMT - Launch Vehicle: Soyuz. Cosmos 213 Mass: 6,500 kg (14,300 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 188 km (116 mi). Apogee: 254 km (157 mi). Inclination: 51.70 deg. Period: 88.90 min. Cosmos 213 was the target for Cosmos 212 in a successful test of Soyuz 7K-OK rendezvous and docking systems. The Cosmos 213 launch was the most accurate yet. The spacecraft was placed in orbit only 4 km from Cosmos 212, ready for a first-orbit docking. Both spacecraft were recovered, but Cosmos 213 was dragged by heavy wind across the steppes when the parachute lines didn't jettison at touchdown. This failure caused the upcoming Soyuz 2/3 manned docking mission to be scaled back.
Officially: Investigation of outer space, development of new systems and elements to be used in the construction of space devices.
Additional Details: Cosmos 213(852).
1968 April 21 - 04:20 GMT - Launch Vehicle: Soyuz. Molniya 1-08 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 405 km (251 mi). Apogee: 40,099 km (24,916 mi). Inclination: 64.00 deg. Period: 720.80 min. Operation of a system of long range telephone-telegraph radiocommunication, and transmission of USSR Central Television programmes to the stations of the Orbita network.
1968 June 4 - 06:45 GMT - Launch Vehicle: Soyuz. Cosmos 224 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 256 km (159 mi). Inclination: 51.80 deg. Period: 89.10 min. High resolution photo reconnaissance satellite; returned film capsule; also measured atmospheric composition.
1968 June 18 - 06:15 GMT - Launch Vehicle: Soyuz. Cosmos 227 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 271 km (168 mi). Inclination: 51.80 deg. Period: 89.20 min. High resolution photo reconnaissance satellite; returned film capsule
1968 June 21 - 12:00 GMT - Launch Vehicle: Soyuz. Cosmos 228 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 245 km (152 mi). Inclination: 51.60 deg. Period: 89.00 min. Area survey photo reconnaissance satellite; returned film capsule; deployed cosmic ray experiment capsule.
1968 July 5 - 15:25 GMT - Launch Vehicle: Soyuz. Molniya 1-09 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 396 km (246 mi). Apogee: 39,806 km (24,734 mi). Inclination: 65.10 deg. Period: 714.70 min. Operation of a system of long range telephone-telegraph radiocommunication, and transmission of USSR Central Television programmes to the stations of the Orbita network.
1968 July 30 - 07:00 GMT - Launch Vehicle: Soyuz. Cosmos 234 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 208 km (129 mi). Apogee: 288 km (178 mi). Inclination: 51.80 deg. Period: 89.40 min. High resolution photo reconnaissance satellite; returned film capsule
1968 September 5 - 07:00 GMT - Launch Vehicle: Soyuz. Cosmos 239 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 201 km (124 mi). Apogee: 274 km (170 mi). Inclination: 51.80 deg. Period: 89.20 min. High resolution photo reconnaissance satellite; returned film capsule
1968 September 23 - 07:39 GMT - Launch Vehicle: Soyuz. Cosmos 243 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 213 km (132 mi). Apogee: 293 km (182 mi). Inclination: 71.30 deg. Period: 89.50 min. Area survey photo reconnaissance satellite; returned film capsule; deployed passive microwave radio telescope capsule.
1968 October 5 - 00:32 GMT - Launch Vehicle: Soyuz. Molniya 1-10 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 498 km (309 mi). Apogee: 39,596 km (24,603 mi). Inclination: 64.90 deg. Period: 712.50 min. Operation of a system of long range telephone-telegraph radiocommunication, and transmission of USSR Central Television programmes to the stations of the Orbita network.
1968 October 25 - 09:00 GMT - Launch Vehicle: Soyuz. Soyuz 2 Mass: 6,450 kg (14,210 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 191 km (118 mi). Apogee: 229 km (142 mi). Inclination: 51.70 deg. Period: 88.60 min. Flight: Soyuz 3. Unmanned docking target for Soyuz 3. Soyuz 2 launched on time at 12:00 local time, in 0 deg C temperatures and 5 m/s winds. Launch was on time 'as in Korolev's time', notes Kamanin. Docking with Soyuz 3 a failure. Recovered October 28, 1968 7:51 GMT, 5 km from its aim point. Maneuver Summary:
177km X 196km orbit to 184km X 230km orbit. Delta V: 12 m/s.
Officially: Complex testing of spaceship systems in conditions of space flight.
1968 October 31 - Launch Vehicle: Soyuz. Cosmos 251 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 201 km (124 mi). Apogee: 255 km (158 mi). Inclination: 64.90 deg. Period: 89.00 min. High resolution photo reconnaissance satellite; returned film capsule; deployed radio astronony and gamma ray experiment capsule; maneuverable.
1968 December 16 - 09:15 GMT - Launch Vehicle: Soyuz. Cosmos 260 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 506 km (314 mi). Apogee: 39,573 km (24,589 mi). Inclination: 65.00 deg. Period: 712.20 min. Investigation of the upper atmosphere and outer space.
1969 January 5 - 06:28 GMT - Launch Vehicle: Soyuz. Venera 5 Mass: 1,128 kg (2,486 lb). Spacecraft: Venera 2V (V-69). Agency: MOM. Venera 5 is launched at 9:26 Moscow time from LC-31 in -23 deg C temperatures. All proceeds according to plan. Afterwards Kamanin meets Babakin. Venera 6 is planned for launch in 10 January. He also plans two moon landings in 1969 and two in 1970 of soil sample return spacecraft. Kamanin does not believe America can achieve a manned moon landing in 1969, and therefore that Babakin has a very good chance of stealing their thunder.
Meanwhile Venera 5 was launched from its parking orbit towards Venus to obtain atmospheric data. The spacecraft was very similar to Venera 4 although it was of a stronger design. When the atmosphere of Venus was approached, a capsule weighing 405 kg and containing scientific instruments was jettisoned from the main spacecraft. During satellite descent towards the surface of Venus, a parachute opened to slow the rate of descent. For 53 min on May 16, 1969, while the capsule was suspended from the parachute, data from the Venusian atmosphere were returned. The spacecraft also carried a medallion bearing the coat of arms of the U.S.S.R. and a bas-relief of V.I. Lenin to the night side of Venus.
1969 January 10 - 05:51 GMT - Launch Vehicle: Soyuz. Venera 6 Mass: 1,128 kg (2,486 lb). Spacecraft: Venera 2V (V-69). Agency: MOM. Venera 6 was launched towards Venus to obtain atmospheric data. When the atmosphere of Venus was approached, a capsule weighing 405 kg was jettisoned from the main spacecraft. This capsule contained scientific instruments. During descent towards the surface of Venus, a parachute opened to slow the rate of descent. For 51 min on May 17, 1969, while the capsule was suspended from the parachute, data from the Venusian atmosphere were returned. The spacecraft also carried a medallion bearing the coat of arms of the U.S.S.R. and a bas-relief of V.I. Lenin to the night side of Venus.
1969 January 15 - 07:04 GMT - Launch Vehicle: Soyuz. Soyuz 5 Mass: 6,585 kg (14,517 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 196 km (121 mi). Apogee: 212 km (131 mi). Inclination: 51.70 deg. Period: 88.60 min. Crew: Khrunov, Volynov, Yeliseyev. Flight: Soyuz 5, Soyuz 4/5. At 3 am an An-12 arrives from Moscow with ten newspapers, and letters for Shatalov, to be delivered by the Soyuz 5 crew to him as the first 'space mail'. At 05:15 the State Commission convened and approved launch at 10:04:30. The countdown proceeds normally; meanwhile communications sessions are held with Shatalov on Soyuz 4. The commission is taken by automobile convoy from Area 2, to Area 17, where the Soyuz 5 crew declares itself ready for flight. At T-25 minutes, with the crew already aboard the spacecraft, a piece of electrical equipment fails and needs to be replaced. Engineer-Captain Viktor Vasilyevich Alyeshin goes to the fuelled booster and replaces it. While doing this he notices that the access hatch has been secured with only three bolts, instead of the four required. Nevertheless the launch proceeds successfully. After Soyuz 5 is in orbit, it and Soyuz 4 begin their mutual series of manoeuvres for rendezvous and docking. Officially the flight conducted 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.
1969 January 23 - 09:15 GMT - Launch Vehicle: Soyuz. Cosmos 264 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 209 km (129 mi). Apogee: 295 km (183 mi). Inclination: 69.90 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule; carried radio astronony and gamma ray experiments; maneuverable.
1969 February 26 - 08:30 GMT - Launch Vehicle: Soyuz. Cosmos 267 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 331 km (205 mi). Inclination: 70.00 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule
1969 March 24 - 10:10 GMT - Launch Vehicle: Soyuz. Cosmos 274 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 300 km (180 mi). Inclination: 65.00 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule; also carried science package.
1969 April 11 - 02:30 GMT - Launch Vehicle: Soyuz. Molniya 1-11 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 483 km (300 mi). Apogee: 39,595 km (24,603 mi). Inclination: 64.90 deg. Period: 712.10 min. Operation of a system of long range telephone-telegraph radiocommunication, and transmission of USSR Central Television programmes to the stations of the Orbita network.
1969 April 15 - 08:14 GMT - Launch Vehicle: Soyuz. Cosmos 279 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 192 km (119 mi). Apogee: 267 km (165 mi). Inclination: 51.70 deg. Period: 89.00 min. High resolution photo reconnaissance satellite; returned film capsule
1969 April 23 - 09:55 GMT - Launch Vehicle: Soyuz. Cosmos 280 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 250 km (150 mi). Inclination: 51.60 deg. Period: 89.00 min. High resolution photo reconnaissance satellite; returned film capsule; carried weather experiments; maneuverable.
1969 May 29 - 06:59 GMT - Launch Vehicle: Soyuz. Cosmos 284 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 297 km (184 mi). Inclination: 51.70 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule
1969 June 27 - 06:59 GMT - Launch Vehicle: Soyuz. Cosmos 288 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 199 km (123 mi). Apogee: 273 km (169 mi). Inclination: 51.80 deg. Period: 89.20 min. High resolution photo reconnaissance satellite; returned film capsule
1969 July 22 - 12:55 GMT - Launch Vehicle: Soyuz. Molniya 1-12 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 496 km (308 mi). Apogee: 39,526 km (24,560 mi). Inclination: 64.90 deg. Period: 711.00 min. Operation of a system of long range telephone-telegraph radiocommunication, and transmission of USSR Central Television programmes to the stations of the Orbita network.
1969 August 29 - 09:05 GMT - Launch Vehicle: Soyuz. Cosmos 296 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 302 km (187 mi). Inclination: 65.00 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule
1969 September 18 - 08:40 GMT - Launch Vehicle: Soyuz. Cosmos 299 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 284 km (176 mi). Inclination: 65.00 deg. Period: 89.40 min. High resolution photo reconnaissance satellite; returned film capsule
1969 October 12 - 10:44 GMT - Launch Vehicle: Soyuz. Soyuz 7 Mass: 6,570 kg (14,480 lb). Spacecraft: Soyuz 7K-OK. Agency: MOM. Perigee: 210 km (130 mi). Apogee: 223 km (138 mi). Inclination: 51.70 deg. Period: 88.80 min. Crew: Filipchenko, Gorbatko, Volkov. 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 8 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. Additional Details: Soyuz 7(1057).
1969 October 24 - 09:40 GMT - Launch Vehicle: Soyuz. Cosmos 306 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 215 km (133 mi). Apogee: 299 km (185 mi). Inclination: 65.00 deg. Period: 89.60 min. Area survey photo reconnaissance satellite; returned film capsule.
1969 November 15 - 08:30 GMT - Launch Vehicle: Soyuz. Cosmos 310 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 336 km (208 mi). Inclination: 65.00 deg. Period: 89.90 min. High resolution photo reconnaissance satellite; returned film capsule
1970 January 9 - 09:20 GMT - Launch Vehicle: Soyuz. Cosmos 318 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 379 km (235 mi). Inclination: 65.00 deg. Period: 90.30 min. Area survey photo reconnaissance satellite; returned film capsule.
1970 April 8 - 10:15 GMT - Launch Vehicle: Soyuz. Cosmos 331 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 320 km (190 mi). Inclination: 65.00 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule
1970 May 20 - 09:20 GMT - Launch Vehicle: Soyuz. Cosmos 345 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 153 km (95 mi). Apogee: 296 km (183 mi). Inclination: 52.00 deg. Period: 89.00 min. High resolution photo reconnaissance satellite; returned film capsule
1970 June 10 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 346 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 351 km (218 mi). Inclination: 51.80 deg. Period: 90.00 min. High resolution photo reconnaissance satellite; returned film capsule
1970 June 26 - 12:00 GMT - Launch Vehicle: Soyuz. Cosmos 350 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 180 km (110 mi). Apogee: 274 km (170 mi). Inclination: 51.70 deg. Period: 89.00 min. Area survey photo reconnaissance satellite; returned film capsule.
1970 July 7 - 10:30 GMT - Launch Vehicle: Soyuz. Cosmos 352 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 340 km (210 mi). Inclination: 51.80 deg. Period: 89.90 min. High resolution photo reconnaissance satellite; returned film capsule
1970 August 17 - 05:38 GMT - Launch Vehicle: Soyuz. Venera 7 Mass: 1,180 kg (2,600 lb). Spacecraft: Venera 3V (V-70). Agency: MOM. Venera 7 was launched from an earth parking orbit towards Venus to study the Venusian atmosphere and other phenomena of the planet. Venera 7 entered the atmosphere of Venus on December 15, 1970, and a landing capsule was jettisoned. After aerodynamic braking, a parachute system was deployed. The capsule antenna was extended, and signals were returned for 35 min. Another 23 min of very weak signals were received after the spacecraft landed on Venus. The capsule was the first man-made object to return data after landing on another planet.
1970 September 17 - 08:10 GMT - Launch Vehicle: Soyuz. Cosmos 363 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 294 km (182 mi). Inclination: 65.00 deg. Period: 89.50 min. Area survey photo reconnaissance satellite; returned film capsule.
October 1970 - LC-1 at Baikonur refurbished In 1969 - 1970 LC-1 was refurbished. The refurbished complex could accommodate new versions of the Soyuz launch vehicle designed for Zenit reconnaisance satellites. The work was completed in October 1970. During the refurbishment a fire at the -32 m level in the flame pit killed four soldiers. The accident was apparently due to smoking of cigarettes in a corridor with an oxygen-rich atmosphere during liquid oxygen handling.
1970 October 1 - 08:20 GMT - Launch Vehicle: Soyuz. Cosmos 366 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 216 km (134 mi). Apogee: 284 km (176 mi). Inclination: 65.00 deg. Period: 89.50 min. Area survey photo reconnaissance satellite; returned film capsule.
1970 October 8 - 12:39 GMT - Launch Vehicle: Soyuz. Cosmos 368 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 383 km (237 mi). Inclination: 65.00 deg. Period: 90.40 min. Bion precursor mission. Conducted biological investigations and study of the physical characteristics of outer space.
1970 October 9 - 11:04 GMT - Launch Vehicle: Soyuz. Cosmos 370 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 280 km (170 mi). Inclination: 64.90 deg. Period: 89.30 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1970 November 11 - 09:20 GMT - Launch Vehicle: Soyuz. Cosmos 377 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 286 km (177 mi). Inclination: 65.00 deg. Period: 89.30 min. Area survey photo reconnaissance satellite; returned film capsule.
1970 December 15 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 386 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 222 km (137 mi). Apogee: 242 km (150 mi). Inclination: 65.00 deg. Period: 89.10 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1970 December 25 - 03:50 GMT - Launch Vehicle: Soyuz. Molniya 1-17 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 474 km (294 mi). Apogee: 39,881 km (24,780 mi). Inclination: 65.00 deg. Period: 717.80 min. Operation of a system of long range telephone-telegraph radiocommunication, and transmission of USSR Central Television programmes to the stations of the Orbita network.
1971 January 12 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 390 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 196 km (121 mi). Apogee: 276 km (171 mi). Inclination: 65.00 deg. Period: 89.20 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1971 January 21 - 08:40 GMT - Launch Vehicle: Soyuz. Cosmos 392 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 278 km (172 mi). Inclination: 65.00 deg. Period: 89.30 min. Area survey photo reconnaissance satellite; returned film capsule.
1971 March 3 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 399 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 200 km (120 mi). Apogee: 285 km (177 mi). Inclination: 64.90 deg. Period: 89.30 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1971 April 22 - 23:54 GMT - Launch Vehicle: Soyuz. Soyuz 11A511 25 Soyuz 10 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7KT-OK. Agency: MOM. Perigee: 209 km (129 mi). Apogee: 258 km (160 mi). Inclination: 51.60 deg. Period: 89.10 min. Crew: Rukavishnikov, Shatalov, Yeliseyev. Flight: Soyuz 10. Intended first space station mission; soft docked with Salyut 1. Launch nearly scrubbed due to poor weather. Soyuz 10 approached to 180 m from Salyut 1 automatically. It was hand docked after faillure of the automatic system, but hard docking could not be achieved because of the angle of approach. Post-flight analysis indicated that the cosmonauts had no instrument to proivde the angle and range rate data necessary for a successful manual docking. Soyuz 10 was connected to the station for 5 hours and 30 minutes. Despite the lack of hard dock, it is said that the crew were unable to enter the station due to a faulty hatch on their own spacecraft. When Shatalov tried to undock from the Salyut, the jammed hatch impeded the docking mechanism, preventing undocking. After several attempts he was unable to undock and land.
1971 May 6 - 06:20 GMT - Launch Vehicle: Soyuz. Cosmos 410 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 280 km (170 mi). Inclination: 65.00 deg. Period: 89.40 min. Area survey photo reconnaissance satellite; returned film capsule; deployed science capsule.
1971 May 18 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 420 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 199 km (123 mi). Apogee: 257 km (159 mi). Inclination: 51.80 deg. Period: 89.00 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1971 June 6 - 04:55 GMT - Launch Vehicle: Soyuz. Soyuz 11 Mass: 6,790 kg (14,960 lb). Spacecraft: Soyuz 7KT-OK. Agency: MOM. Perigee: 163 km (101 mi). Apogee: 237 km (147 mi). Inclination: 51.50 deg. Period: 88.40 min. Crew: Dobrovolsky, Patsayev, Volkov. Flight: Soyuz 11. First space station flight, two years before the American Skylab. The Soyuz 11 launch proceeds without any difficulties. The first orbital correction in the set of rendezvous manoeuvres to head for Salyut 1 is made on the fourth revolution. At 15:00 Kamanin and other critical staff board a plane for the mission control centre at Yevpatoriya. The aircraft takes 4 hours 30 minutes to get there.
Equipment aboard Salyut 1 included a telescope, spectrometer, electrophotometer, and television. The crew checked improved on-board spacecraft systems in different conditions of flight and conducted medico-biological research. The main instrument, a large solar telescope, was inoperative because its cover failed to jettison. A small fire and difficult working conditions will lead to a decision to return crew before planned full duration of 30 days.
1971 June 24 - 07:59 GMT - Launch Vehicle: Soyuz. Cosmos 428 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 257 km (159 mi). Inclination: 51.70 deg. Period: 89.10 min. Area survey photo reconnaissance satellite; returned film capsule; deployed electron and gamma ray science capsule.
1971 July 20 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 429 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 252 km (156 mi). Inclination: 51.80 deg. Period: 89.00 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1971 July 30 - 08:29 GMT - Launch Vehicle: Soyuz. Cosmos 431 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 165 km (102 mi). Apogee: 284 km (176 mi). Inclination: 51.70 deg. Period: 89.00 min. Area survey photo reconnaissance satellite; returned film capsule.
1971 August 5 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 432 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 200 km (120 mi). Apogee: 252 km (156 mi). Inclination: 51.70 deg. Period: 89.10 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1971 September 28 - 07:40 GMT - Launch Vehicle: Soyuz. Cosmos 441 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 266 km (165 mi). Inclination: 65.00 deg. Period: 89.20 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1971 October 14 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 452 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 193 km (119 mi). Apogee: 248 km (154 mi). Inclination: 64.90 deg. Period: 89.00 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1971 December 6 - 09:50 GMT - Launch Vehicle: Soyuz. Cosmos 463 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 272 km (169 mi). Inclination: 64.00 deg. Period: 89.20 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1971 December 16 - 09:39 GMT - Launch Vehicle: Soyuz. Cosmos 466 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 175 km (108 mi). Apogee: 375 km (233 mi). Inclination: 64.00 deg. Period: 90.00 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1972 January 12 - 09:59 GMT - Launch Vehicle: Soyuz. Cosmos 471 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 201 km (124 mi). Apogee: 316 km (196 mi). Inclination: 65.00 deg. Period: 89.70 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1972 February 3 - 08:40 GMT - Launch Vehicle: Soyuz. Cosmos 473 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. 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; returned film capsule.
1972 February 16 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 474 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 177 km (109 mi). Apogee: 325 km (201 mi). Inclination: 64.90 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1972 May 25 - 06:35 GMT - Launch Vehicle: Soyuz. Cosmos 491 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 177 km (109 mi). Apogee: 268 km (166 mi). Inclination: 64.90 deg. Period: 88.90 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1972 June 9 - 06:59 GMT - Launch Vehicle: Soyuz. Cosmos 492 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 323 km (200 mi). Inclination: 64.90 deg. Period: 89.70 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1972 June 21 - 06:25 GMT - Launch Vehicle: Soyuz. Cosmos 493 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 267 km (165 mi). Inclination: 64.90 deg. Period: 89.10 min. Area survey photo reconnaissance satellite; returned film capsule.
1972 June 26 - 14:53 GMT - Launch Vehicle: Soyuz. Cosmos 496 Mass: 6,675 kg (14,715 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 176 km (109 mi). Apogee: 253 km (157 mi). Inclination: 51.50 deg. Period: 88.70 min. Recovered July 6, 1972 13:54 GMT. Soyuz 7K-T redesign test.
1972 July 6 - 10:40 GMT - Launch Vehicle: Soyuz. Cosmos 499 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 283 km (175 mi). Inclination: 51.80 deg. Period: 89.30 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1972 August 2 - 08:15 GMT - Launch Vehicle: Soyuz. Cosmos 513 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 172 km (106 mi). Apogee: 307 km (190 mi). Inclination: 64.90 deg. Period: 89.30 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1972 August 30 - 08:19 GMT - Launch Vehicle: Soyuz. Cosmos 517 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 285 km (177 mi). Inclination: 64.90 deg. Period: 89.30 min. Area survey photo reconnaissance satellite; returned film capsule.
1972 September 16 - 08:20 GMT - Launch Vehicle: Soyuz. Cosmos 519 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 360 km (220 mi). Inclination: 71.30 deg. Period: 90.20 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1972 November 25 - 09:10 GMT - Launch Vehicle: Soyuz. Cosmos 537 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 303 km (188 mi). Inclination: 64.00 deg. Period: 89.60 min. Area survey photo reconnaissance satellite; returned film capsule.
1972 December 2 - 04:39 GMT - Launch Vehicle: Soyuz. Molniya 1-22 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 462 km (287 mi). Apogee: 39,608 km (24,611 mi). Inclination: 64.00 deg. Period: 712.00 min. Uncertain if Molniya-1T model was Molniya-1 or Molniya-1T. Operation of a system of long range telephone-telegraph radiocommunication, and transmission of USSR Central Television programmes to the stations of the Orbita network.
1973 January 11 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 543 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 191 km (118 mi). Apogee: 274 km (170 mi). Inclination: 64.90 deg. Period: 89.20 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1973 February 1 - 08:30 GMT - Launch Vehicle: Soyuz. Cosmos 547 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 309 km (192 mi). Inclination: 64.00 deg. Period: 89.60 min. Area survey photo reconnaissance satellite; returned film capsule.
1973 February 3 - 05:48 GMT - Launch Vehicle: Soyuz. Molniya 1-23 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 476 km (295 mi). Apogee: 39,602 km (24,607 mi). Inclination: 65.00 deg. Period: 712.20 min. Uncertain if Molniya-1T model was Molniya-1 or Molniya-1T. Operation of a system of long range telephone-telegraph radiocommunication, and transmission of USSR Central Television programmes to the stations of the Orbita network.
1973 March 6 - 09:20 GMT - Launch Vehicle: Soyuz. Cosmos 551 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 296 km (183 mi). Inclination: 65.00 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1973 June 10 - 10:10 GMT - Launch Vehicle: Soyuz. Cosmos 572 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 281 km (174 mi). Inclination: 51.70 deg. Period: 89.30 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1973 June 15 - 06:00 GMT - Launch Vehicle: Soyuz. Cosmos 573 Mass: 6,675 kg (14,715 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 191 km (118 mi). Apogee: 308 km (191 mi). Inclination: 51.60 deg. Period: 89.50 min. Soyuz test flight. Recovered June 17, 1973 6:01 GMT. Soyuz 7K-T redesign test, probably using one of the spacecraft allocated to the failed Salyut 2 or Cosmos 557 stations.
1973 August 24 - 10:59 GMT - Launch Vehicle: Soyuz. Cosmos 581 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 177 km (109 mi). Apogee: 276 km (171 mi). Inclination: 51.60 deg. Period: 89.00 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1973 August 30 - 10:30 GMT - Launch Vehicle: Soyuz. Cosmos 583 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 298 km (185 mi). Inclination: 64.90 deg. Period: 89.50 min. Area survey photo reconnaissance satellite; returned film capsule; separated capsule.
1973 September 27 - 12:18 GMT - Launch Vehicle: Soyuz. Soyuz 12 Mass: 6,720 kg (14,810 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 306 km (190 mi). Apogee: 348 km (216 mi). Inclination: 51.00 deg. Period: 91.00 min. Crew: Lazarev, Makarov. Flight: Soyuz 12. Experimental flight for the purpose of further development of manned space craft Soyuz 7K-T modifications. After the Soyuz 11 disaster, the Soyuz underwent redesign for increased reliability. Two solo test flights of the new design were planned. Crews for the first flight were those already planned for the deferred follow-on missions to the failed DOS 2 and DOS 3 space stations.
1973 October 15 - 08:45 GMT - Launch Vehicle: Soyuz. Cosmos 599 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 280 km (170 mi). Inclination: 64.90 deg. Period: 89.30 min. Area survey photo reconnaissance satellite; returned film capsule.
1973 November 14 - 20:40 GMT - Launch Vehicle: Soyuz. Molniya 1-25 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1. Agency: MOM. Perigee: 461 km (286 mi). Apogee: 39,607 km (24,610 mi). Inclination: 64.00 deg. Period: 712.00 min. Operation of a system of long range telephone-telegraph radiocommunication, and transmission of USSR Central Television programmes to the stations of the Orbita network.
1973 November 21 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 609 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 175 km (108 mi). Apogee: 335 km (208 mi). Inclination: 69.90 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1973 November 30 - 05:20 GMT - Launch Vehicle: Soyuz. Cosmos 613 Mass: 6,675 kg (14,715 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 199 km (123 mi). Apogee: 276 km (171 mi). Inclination: 51.60 deg. Period: 89.30 min. Unmanned Soyuz test flight. Recovered January 29, 1974 5:29 GMT. Soyuz 7K-T duration test.
1973 December 18 - 11:55 GMT - Launch Vehicle: Soyuz. Soyuz 13 Mass: 6,560 kg (14,460 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 188 km (116 mi). Apogee: 247 km (153 mi). Inclination: 51.60 deg. Period: 88.80 min. Crew: Klimuk, Lebedev. Flight: Soyuz 13. A unique flight of the 7K-T/AF modification of the Soyuz spacecraft. The orbital module was dominated by the large Orion 2 astrophysical camera. The crew conducted astrophysical observations of stars in the ultraviolet range. Additional experiments included spectrozonal photography of specific areas of the earth's surface, and continued testing of space craft's on-board systems.
1974 February 12 - 08:56 GMT - Launch Vehicle: Soyuz. Cosmos 632 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 176 km (109 mi). Apogee: 303 km (188 mi). Inclination: 65.00 deg. Period: 89.30 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1974 March 20 - 08:30 GMT - Launch Vehicle: Soyuz. Cosmos 636 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 169 km (105 mi). Apogee: 302 km (187 mi). Inclination: 65.00 deg. Period: 89.20 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1974 May 15 - 08:30 GMT - Launch Vehicle: Soyuz. Cosmos 652 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 343 km (213 mi). Inclination: 51.80 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1974 May 27 - 07:20 GMT - Launch Vehicle: Soyuz. Cosmos 656 Mass: 6,675 kg (14,715 lb). Spacecraft: Soyuz 7K-T/A9. Agency: MOM. Perigee: 195 km (121 mi). Apogee: 364 km (226 mi). Inclination: 51.60 deg. Period: 90.00 min. Unmanned test flight of the Soyuz 7K-T(A9) Soyuz variant designed for docking with the military Almaz space station. Recovered May 29, 1974 7:50 GMT.
1974 June 6 - 06:20 GMT - Launch Vehicle: Soyuz. Cosmos 658 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 286 km (177 mi). Inclination: 65.00 deg. Period: 89.40 min. Area survey photo reconnaissance satellite; returned film capsule.
1974 July 3 - 18:51 GMT - Launch Vehicle: Soyuz. Soyuz 14 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T/A9. Agency: MOM. Perigee: 195 km (121 mi). Apogee: 217 km (134 mi). Inclination: 51.60 deg. Period: 88.60 min. Crew: Artyukhin, Popovich. Flight: Soyuz 14. On 4 July Soyuz 14 docked with the Salyut 3 space station after 15 revolutions of the earth. The planned experimental program included manned military reconnaissance of the earth's surface, assessing the fundamental value of such observations, and some supplemental medico-biological research. After the crew's return research continued in the development of the on-board systems and the principles of remote control of such a station.
1974 July 25 - 07:00 GMT - Launch Vehicle: Soyuz. Cosmos 667 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4M. Agency: MOM. Perigee: 176 km (109 mi). Apogee: 320 km (190 mi). Inclination: 65.00 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1974 August 6 - 00:02 GMT - Launch Vehicle: Soyuz. Cosmos 670 Mass: 6,700 kg (14,700 lb). Spacecraft: Soyuz 7K-S. Agency: MOM. Perigee: 211 km (131 mi). Apogee: 294 km (182 mi). Inclination: 50.60 deg. Period: 89.50 min. Unmanned Soyuz 7K-S test flight. Recovered August 8, 1974 23:59 GMT.
1974 August 26 - 19:58 GMT - Launch Vehicle: Soyuz. Soyuz 15 Mass: 6,760 kg (14,900 lb). Spacecraft: Soyuz 7K-T/A9. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 236 km (146 mi). Inclination: 51.60 deg. Period: 88.50 min. Crew: Demin, Sarafanov. Flight: Soyuz 15. Soyuz 15 was to conduct the second phase of manned operations aboard the Salyut 3 military space station, but the Igla rendezvous system failed and no docking was made. The two day flight could only be characterised as '... research in manoeuvring and docking with the OPS in various modes, and development of methods for evacuation and landing from space complex in new conditions....'
As Chelomei had complained, Soyuz had no reserves or backup systems for repeated manual docking attempts and had to be recovered after a two-day flight. The state commission found that the Igla docking system of the Soyuz needed serious modification. This could not be completed before Salyut 3 decayed. Therefore the planned Soyuz 16 spacecraft became excess to the program (it was later flown as Soyuz 20 to a civilian Salyut station, even though over its two year rated storage life).
Officially: Conduct of joint experiments with the Salyut-3 orbital scientific station.
1974 August 29 - 07:39 GMT - Launch Vehicle: Soyuz. Cosmos 674 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 175 km (108 mi). Apogee: 323 km (200 mi). Inclination: 65.00 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1974 September 20 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 685 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 209 km (129 mi). Apogee: 281 km (174 mi). Inclination: 64.90 deg. Period: 89.30 min. Area survey photo reconnaissance satellite; returned film capsule.
1974 October 25 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 691 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 187 km (116 mi). Apogee: 317 km (196 mi). Inclination: 65.00 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1974 December 2 - 09:40 GMT - Launch Vehicle: Soyuz. Soyuz 16 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-TM. Agency: MOM. Perigee: 184 km (114 mi). Apogee: 291 km (180 mi). Inclination: 51.80 deg. Period: 89.20 min. Crew: Filipchenko, Rukavishnikov. Flight: Soyuz 16. ASTP Manned Test Flight. Check-out of the Soyuz space craft's on-board systems which had been modernized to meet the requirements of the 1975 joint flight in accordance with the programme of the Soviet-United States experiment; conduct of scientific and technical investigations.
1974 December 27 - 09:10 GMT - Launch Vehicle: Soyuz. Cosmos 701 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 319 km (198 mi). Inclination: 71.40 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1975 January 10 - 21:43 GMT - Launch Vehicle: Soyuz. Soyuz 17 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 185 km (114 mi). Apogee: 249 km (154 mi). Inclination: 51.60 deg. Period: 88.80 min. Crew: Grechko, Gubarev. Flight: Soyuz 17. Manned two crew. Docked with Salyut 4. Joint experiments with the Salyut scientific orbital station.
1975 January 17 - 09:07 GMT - Launch Vehicle: Soyuz. Cosmos 702 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 313 km (194 mi). Inclination: 71.30 deg. Period: 89.70 min. Area survey photo reconnaissance satellite; returned film capsule.
1975 February 26 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 710 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 176 km (109 mi). Apogee: 335 km (208 mi). Inclination: 65.00 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1975 March 12 - 08:55 GMT - Launch Vehicle: Soyuz. Cosmos 719 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 175 km (108 mi). Apogee: 307 km (190 mi). Inclination: 65.00 deg. Period: 89.30 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1975 March 27 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 722 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 337 km (209 mi). Inclination: 71.40 deg. Period: 89.90 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1975 April 5 - 11:04 GMT - Launch Vehicle: Soyuz. FAILURE: During second-third stage separation third stage failed to separate from second stage but still ignited. Soyuz 18-1 Mass: 6,830 kg (15,050 lb). Spacecraft: Soyuz 7K-T. Agency: RVSN. Apogee: 192 km (119 mi). Crew: Lazarev, Makarov. Flight: Soyuz 18-1. Carried Oleg Makarov, Vasili Lazarev for rendezvous with Salyut 4; but during second-third stage seperation third stage failed to separate from second stage but still ignited. The crew demanded that the abort procedures be implemented but ground control could not see the launch vehicle gyrations in their telemetry. Soyuz finally was separated from by ground control command at 192 km, and following a 20.6+ G reentry, the capsule landed in the Altai mountains, tumbled down a mountainside, and snagged in some bushes just short of a precipice. The crew was worried that they may have landed in China and would face internment, but after an hour sitting in the cold next to the capsule, they were discovered by locals speaking Russian. Total flight duration was 1574 km and flight time 21 minutes 27 seconds. Lazarev suffered internal injuries from the high-G reentry and tumble down the mountain side and never flew again. Both cosmonauts were denied their 3000 ruble spaceflight bonus pay and had to apeal all the way to Brezhnev before being paid.
1975 April 16 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 727 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 172 km (106 mi). Apogee: 334 km (207 mi). Inclination: 65.00 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1975 May 21 - 06:59 GMT - Launch Vehicle: Soyuz. Cosmos 731 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 296 km (183 mi). Inclination: 65.00 deg. Period: 89.50 min. Area survey photo reconnaissance satellite; returned film capsule; separated science capsule.
1975 May 24 - 14:58 GMT - Launch Vehicle: Soyuz. Soyuz 18 Mass: 6,825 kg (15,046 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 186 km (115 mi). Apogee: 230 km (140 mi). Inclination: 51.70 deg. Period: 88.60 min. Crew: Klimuk, Sevastyanov. Flight: Soyuz 18. Manned two crew. Docked with Salyut 4. Joint experiments with the Salyut scientific orbital station. The crew remained aloft aboard the station during the Apollo-Soyuz Test Project joint flight.
1975 May 28 - 07:29 GMT - Launch Vehicle: Soyuz. Cosmos 740 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 327 km (203 mi). Inclination: 65.00 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1975 July 15 - 12:20 GMT - Launch Vehicle: Soyuz. Soyuz 19 (ASTP) Mass: 6,790 kg (14,960 lb). Spacecraft: Soyuz 7K-TM. Agency: MOM. Perigee: 186 km (115 mi). Apogee: 220 km (130 mi). Inclination: 51.80 deg. Period: 88.50 min. Crew: Kubasov, Leonov. Flight: Soyuz 19 (ASTP), Apollo (ASTP). Soyuz 19 initial orbital parameters were 220.8 by 185.07 kilometres, at the desired inclination of 51.80�, while the period of the first orbit was 88.6 minutes. On 17 July the two spacecraft docked. The crew members rotated between the two spacecraft and conducted various mainly ceremonial activities. Leonov was on the American side for 5 hours, 43 minutes, while Kubasov spent 4:57 in the command and docking modules.
After being docked for nearly 44 hours, Apollo and Soyuz parted for the first time and were station-keeping at a range of 50 meters. The Apollo crew placed its craft between Soyuz and the sun so that the diameter of the service module formed a disk which blocked out the sun. After this experiment Apollo moved towards Soyuz for the second docking.
Three hours later Apollo and Soyuz undocked for the second and final time. The spacecraft moved to a 40 m station-keeping distance so that an ultraviolet absorption experiment could be performed. With all the joint flight activities completed, the ships went on their separate ways.
1975 August 13 - 07:21 GMT - Launch Vehicle: Soyuz. Cosmos 754 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 326 km (202 mi). Inclination: 71.40 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1975 September 16 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 760 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 174 km (108 mi). Apogee: 335 km (208 mi). Inclination: 65.00 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1975 September 29 - 04:15 GMT - Launch Vehicle: Soyuz. Cosmos 772 Mass: 6,750 kg (14,880 lb). Spacecraft: Soyuz 7K-S. Agency: MOM. Perigee: 154 km (95 mi). Apogee: 245 km (152 mi). Inclination: 51.80 deg. Period: 88.40 min. Unmanned military Soyuz 7K-S test flight. Recovered October 3, 1975 4:10 GMT. Unsuccessful mission. Transmitted only on 166 MHz frequency, at none of the other usual Soyuz wavelengths.
Maneuver Summary:
193 km X 270 km orbit to 195 km X 300 km orbit. Delta V: 8 m/s
196 km X 300 km orbit to 196 km X 328 km orbit. Delta V: 8 m/s
Total Delta V: 16 m/s
1975 October 1 - 08:30 GMT - Launch Vehicle: Soyuz. Cosmos 774 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 315 km (195 mi). Inclination: 71.40 deg. Period: 89.70 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1975 November 17 - 14:36 GMT - Launch Vehicle: Soyuz. Soyuz 20 Mass: 6,700 kg (14,700 lb). Spacecraft: Soyuz 7K-T/A9. Agency: MOM. Perigee: 184 km (114 mi). Apogee: 251 km (155 mi). Inclination: 51.60 deg. Period: 88.80 min. Unmanned long duration test of the Soyuz transport vehicle; docked with Salyut 4. Recovered February 16, 1976 2:24 GMT. Comprehensive checking of improved on-board systems of the space craft under various flight conditions. Carried a biological payload. Living organisms were exposed to three months in space.
1975 November 21 - 09:20 GMT - Launch Vehicle: Soyuz. Cosmos 780 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 201 km (124 mi). Apogee: 278 km (172 mi). Inclination: 65.00 deg. Period: 89.30 min. Area survey photo reconnaissance satellite; returned film capsule; separated science capsule.
1975 December 16 - 09:50 GMT - Launch Vehicle: Soyuz. Cosmos 786 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 184 km (114 mi). Apogee: 325 km (201 mi). Inclination: 65.00 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1976 January 22 - 11:38 GMT - Launch Vehicle: Soyuz. Molniya 1-32 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1T. Agency: MOM. Perigee: 2,247 km (1,396 mi). Apogee: 38,210 km (23,740 mi). Inclination: 63.60 deg. Period: 719.80 min. Continued operation of the long-range telephone and telegraph radio-communication system within the Soviet Union and transmission of USSR central television programmes to stations in the Orbita and participating international networks (international cooperation scheme).
1976 January 29 - 08:30 GMT - Launch Vehicle: Soyuz. Cosmos 799 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 306 km (190 mi). Inclination: 71.40 deg. Period: 89.60 min. Area survey photo reconnaissance satellite; returned film capsule.
1976 February 11 - 08:50 GMT - Launch Vehicle: Soyuz. Cosmos 802 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 172 km (106 mi). Apogee: 334 km (207 mi). Inclination: 65.00 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1976 March 10 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 806 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 188 km (116 mi). Apogee: 328 km (203 mi). Inclination: 71.40 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1976 March 18 - 09:15 GMT - Launch Vehicle: Soyuz. Cosmos 809 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 300 km (180 mi). Inclination: 65.00 deg. Period: 89.60 min. Area survey photo reconnaissance satellite; returned film capsule.
1976 March 19 - 19:31 GMT - Launch Vehicle: Soyuz. Molniya 1-34 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1T. Agency: MOM. Perigee: 617 km (383 mi). Apogee: 39,722 km (24,682 mi). Inclination: 62.70 deg. Period: 717.40 min. Continued operation of the long-range telephone and telegraph radio-communication system within the Soviet Union and transmission of USSR central television programmes to stations in the Orbita and participating international networks (international cooperation scheme).
1976 May 5 - 07:50 GMT - Launch Vehicle: Soyuz. Cosmos 817 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 324 km (201 mi). Inclination: 65.00 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1976 May 20 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 819 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 293 km (182 mi). Inclination: 64.90 deg. Period: 89.50 min. Area survey photo reconnaissance satellite; returned film capsule.
1976 June 8 - 07:00 GMT - Launch Vehicle: Soyuz. Cosmos 824 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 325 km (201 mi). Inclination: 71.40 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1976 June 29 - 07:20 GMT - Launch Vehicle: Soyuz. Cosmos 835 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 174 km (108 mi). Apogee: 317 km (196 mi). Inclination: 65.00 deg. Period: 89.40 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1976 July 6 - 12:08 GMT - Launch Vehicle: Soyuz. Soyuz 21 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T/A9. Agency: MOM. Perigee: 246 km (152 mi). Apogee: 274 km (170 mi). Inclination: 51.60 deg. Period: 89.70 min. Crew: Volynov, Zholobov. Flight: Soyuz 21. Soyuz 21 with Volynov and Zholobov aboard hard-docked with the station on 6 July 1976 after failure of the Igla system at the last stage of rendezvous. Towards the end of the two month mission an early return to earth was requested due to the poor condition of flight engineer Zholobov (who was suffering from space sickness and psychological problems).
1976 July 23 - 15:49 GMT - Launch Vehicle: Soyuz. Molniya 1-35 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1T. Agency: MOM. Perigee: 483 km (300 mi). Apogee: 38,911 km (24,178 mi). Inclination: 62.90 deg. Period: 698.40 min. Continued operation of the long-range telephone and telegraph radio-communication system within the Soviet Union and transmission of USSR central television programmes to stations in the Orbita and participating international networks (international cooperation scheme).
1976 August 28 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 852 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 332 km (206 mi). Inclination: 65.00 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1976 September 15 - 09:48 GMT - Launch Vehicle: Soyuz. Soyuz 22 Mass: 6,510 kg (14,350 lb). Spacecraft: Soyuz 7K-MF6. Agency: MOM. Perigee: 185 km (114 mi). Apogee: 296 km (183 mi). Inclination: 64.80 deg. Period: 89.30 min. Crew: Aksyonov, Bykovsky. Flight: Soyuz 22. Surplus Soyuz ASTP spacecraft modified with a multi-spectral camera manufactured by Carl Zeiss-Jena in place of the universal docking apparatus. Eight days were spent photographing the earth. Tested and perfected scientific-technical methods and devices for studying the geological characteristics of the earth's surface from outer space for economic purposes.
1976 September 22 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 856 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 300 km (180 mi). Inclination: 65.00 deg. Period: 89.50 min. Area survey photo reconnaissance satellite; returned film capsule; separated science capsule.
1976 October 10 - 09:35 GMT - Launch Vehicle: Soyuz. Cosmos 859 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 337 km (209 mi). Inclination: 65.00 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable; also performed earth resources tasks.
1976 October 14 - 17:39 GMT - Launch Vehicle: Soyuz. Soyuz 23 Mass: 6,760 kg (14,900 lb). Spacecraft: Soyuz 7K-T/A9. Agency: MOM. Perigee: 239 km (148 mi). Apogee: 269 km (167 mi). Inclination: 51.60 deg. Period: 89.50 min. Crew: Rozhdestvensky, Zudov. Flight: Soyuz 23. The Soyuz 23 ferry spacecraft suffered a docking system failure. Sensors indicated an incorrect lateral velocity, causing unnecessary firing of the thrusters during rendezvous. The automatic system was turned off, but no fuel remained for a manual docking by the crew.
1976 November 11 - 10:45 GMT - Launch Vehicle: Soyuz. Cosmos 866 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 180 km (110 mi). Apogee: 287 km (178 mi). Inclination: 65.00 deg. Period: 89.20 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1976 November 29 - 16:00 GMT - Launch Vehicle: Soyuz. Cosmos 869 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-S. Agency: MOM. Perigee: 209 km (129 mi). Apogee: 289 km (179 mi). Inclination: 51.70 deg. Period: 89.40 min. Unmanned military Soyuz 7K-S test flight. Recovered December 17, 1976 10:31 GMT. Transmitted only on 20.008 MHz and 166 MHz frequencies, at none of the other usual Soyuz wavelengths.
Maneuver Summary:
196 km X 290 km orbit to 187 km X 335 km orbit. Delta V: 15 m/s
187 km X 335 km orbit to 259 km X 335 km orbit. Delta V: 21 m/s
259 km X 335 km orbit to 260 km X 345 km orbit. Delta V: 2 m/s
260 km X 345 km orbit to 265 km X 368 km orbit. Delta V: 7 m/s
265 km X 368 km orbit to 267 km X 391 km orbit. Delta V: 6 m/s
267 km X 391 km orbit to 300 km X 310 km orbit. Delta V: 32 m/s
Total Delta V: 83 m/s
1976 December 17 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 884 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 169 km (105 mi). Apogee: 345 km (214 mi). Inclination: 65.10 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1977 January 6 - 09:40 GMT - Launch Vehicle: Soyuz. Cosmos 888 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 170 km (100 mi). Apogee: 325 km (201 mi). Inclination: 65.00 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1977 January 20 - 08:30 GMT - Launch Vehicle: Soyuz. Cosmos 889 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 329 km (204 mi). Inclination: 71.40 deg. Period: 89.80 min. Area survey photo reconnaissance satellite; returned film capsule.
1977 February 7 - 16:10 GMT - Launch Vehicle: Soyuz. Soyuz 24 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T/A9. Agency: MOM. Perigee: 226 km (140 mi). Apogee: 264 km (164 mi). Inclination: 51.60 deg. Period: 89.30 min. Crew: Glazkov, Gorbatko. Flight: Soyuz 24. Soyuz 24 docked with Salyut 5 and brought repair equipment and equipment for a change of cabin atmosphere. This special apparatus was designed to allow the entire station to be vented through the EVA airlock. Because of this the planned EVA was cancelled. However analysis after arrival showed no toxins in the air. The crew changed the cabin air anyway, then returned to earth. The mission, although a short 18 days, was characterised as a busy and successful mission, accomplishing nearly as much as the earlier Soyuz 21's 50 day mission.
1977 April 20 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 904 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 328 km (203 mi). Inclination: 71.40 deg. Period: 89.80 min. Area survey photo reconnaissance satellite; returned film capsule.
1977 May 17 - 10:10 GMT - Launch Vehicle: Soyuz. Cosmos 908 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 174 km (108 mi). Apogee: 288 km (178 mi). Inclination: 51.80 deg. Period: 89.10 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1977 May 31 - 07:30 GMT - Launch Vehicle: Soyuz. Cosmos 914 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 284 km (176 mi). Inclination: 65.00 deg. Period: 89.40 min. Area survey photo reconnaissance satellite; returned film capsule; separated science capsule.
1977 June 22 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 920 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MK. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 342 km (212 mi). Inclination: 65.00 deg. Period: 89.70 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1977 June 24 - 05:41 GMT - Launch Vehicle: Soyuz. Molniya 1-37 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1T. Agency: MOM. Perigee: 106 km (65 mi). Apogee: 4,564 km (2,835 mi). Inclination: 62.60 deg. Period: 134.90 min. Operation of a system of long range telephone-telegraph radiocommunication, and transmission of USSR Central Television programmes to the stations of the Orbita network.
1977 July 20 - 07:35 GMT - Launch Vehicle: Soyuz. Cosmos 932 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MKM. Agency: MOM. Perigee: 150 km (90 mi). Apogee: 358 km (222 mi). Inclination: 65.00 deg. Period: 89.60 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1977 September 30 - 09:46 GMT - Launch Vehicle: Soyuz. Cosmos 957 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-4MKM. Agency: MOM. Perigee: 171 km (106 mi). Apogee: 361 km (224 mi). Inclination: 65.00 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule
1977 October 9 - 02:40 GMT - Launch Vehicle: Soyuz. Soyuz 25 Mass: 6,860 kg (15,120 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 194 km (120 mi). Apogee: 240 km (140 mi). Inclination: 51.60 deg. Period: 88.80 min. Crew: Kovalyonok, Ryumin. Flight: Soyuz 25. Manned two crew. Unsuccessful mission. Failed to dock with Salyut 6.
1977 December 10 - 01:18 GMT - Launch Vehicle: Soyuz. Soyuz 26 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 235 km (146 mi). Inclination: 51.60 deg. Period: 88.80 min. Crew: Grechko, Romanenko. Flight: Salyut 6 EO-1. Manned two crew. Docked with Salyut 6. Carried Yuri Romanenko, Georgi Grechko to Salyut 6; returned crew of Soyuz 27 to Earth. Conduct of joint experiments with the Salyut-6 scientific station.
1977 December 12 - 09:40 GMT - Launch Vehicle: Soyuz. Cosmos 966 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 296 km (183 mi). Inclination: 65.00 deg. Period: 89.50 min. Area survey photo reconnaissance satellite; returned film capsule; separated science capsule.
1977 December 27 - 09:20 GMT - Launch Vehicle: Soyuz. Cosmos 973 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 325 km (201 mi). Inclination: 71.50 deg. Period: 89.80 min. Area survey photo reconnaissance satellite; returned film capsule; separated science capsule.
1978 January 10 - 12:26 GMT - Launch Vehicle: Soyuz. Soyuz 27 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 190 km (110 mi). Apogee: 237 km (147 mi). Inclination: 51.70 deg. Period: 88.70 min. Crew: Dzhanibekov, Makarov. Flight: Salyut 6 EP-1, Salyut 6 EO-1. Manned two crew. Carried Oleg Makarov, Vladimir Dzhanibekov to Salyut 6; returned crew of Soyuz 26 to Earth. Docked with Salyut 6.
1978 January 24 - 09:50 GMT - Launch Vehicle: Soyuz. Cosmos 986 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MKM. Agency: MOM. Perigee: 172 km (106 mi). Apogee: 318 km (197 mi). Inclination: 65.00 deg. Period: 89.40 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1978 February 14 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 989 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MKM. Agency: MOM. Perigee: 169 km (105 mi). Apogee: 318 km (197 mi). Inclination: 65.10 deg. Period: 89.40 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1978 March 2 - 15:28 GMT - Launch Vehicle: Soyuz. Soyuz 28 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 192 km (119 mi). Apogee: 246 km (152 mi). Inclination: 51.60 deg. Period: 88.80 min. Crew: Gubarev, Remek. Flight: Salyut 6 EP-2, Salyut 6 EO-1. Manned two crew. Docked with Salyut 6. Delivery to the Salyut-6 station of the first international 'Intercosmos' team consisting of A.A. Gubarev (USSR) and V. Remek (Czechoslovak Socialist Republic) to carry out scientific research and experiments jointly developed by Soviet a nd Czechoslovak specialists.
1978 March 4 - 07:40 GMT - Launch Vehicle: Soyuz. Cosmos 992 Mass: 6,000 kg (13,200 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 323 km (200 mi). Inclination: 71.30 deg. Period: 89.80 min. Area survey photo reconnaissance satellite; returned film capsule.
1978 March 30 - 07:50 GMT - Launch Vehicle: Soyuz. Cosmos 999 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MKM. Agency: MOM. Perigee: 174 km (108 mi). Apogee: 352 km (218 mi). Inclination: 71.40 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1978 April 4 - 15:00 GMT - Launch Vehicle: Soyuz. Cosmos 1001 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 199 km (123 mi). Apogee: 228 km (141 mi). Inclination: 51.60 deg. Period: 88.70 min. Manned precursor. Recovered April 15, 1978 12:02 GMT. Unsuccessful mission. Soyuz T test -failure.
Maneuver Summary:
202 km X 231 km orbit to 195 km X 291 km orbit. Delta V: 19 m/s
195 km X 291 km orbit to 306 km X 322 km orbit. Delta V: 40 m/s
306 km X 322 km orbit to 308 km X 318 km orbit. Delta V: 1 m/s
Total Delta V: 60 m/s.
Officially: Investigation of the upper atmosphere and outer space.
1978 April 6 - 09:10 GMT - Launch Vehicle: Soyuz. Cosmos 1002 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 283 km (175 mi). Inclination: 65.10 deg. Period: 89.40 min. Area survey photo reconnaissance satellite; returned film capsule.
1978 June 10 - 08:35 GMT - Launch Vehicle: Soyuz. Cosmos 1021 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MKM. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 313 km (194 mi). Inclination: 65.00 deg. Period: 89.40 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1978 June 15 - 20:16 GMT - Launch Vehicle: Soyuz. Soyuz 29 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 193 km (119 mi). Apogee: 248 km (154 mi). Inclination: 51.60 deg. Period: 88.90 min. Crew: Ivanchenkov, Kovalyonok. Flight: Salyut 6 EO-2. Manned two crew. Docked with Salyut 6. Placed on board the Salyut-6 station a crew consisting of V.V. Kovalenko and A.S. Ivanchenkov to conduct scientific and technological investigations and experiments.
1978 June 27 - 15:27 GMT - Launch Vehicle: Soyuz. Soyuz 30 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T/A9. Agency: MOM. Perigee: 194 km (120 mi). Apogee: 244 km (151 mi). Inclination: 51.60 deg. Period: 88.80 min. Crew: Hermaszewski, Klimuk. Flight: Salyut 6 EP-3, Salyut 6 EO-2. Manned two crew. Docked with Salyut 6. Placed on board the Salyut-6 station, under the Intercosmos programme, a second, international, crew consisting of P.I. Klimuk (USSR) and M. Hermaszewski (Poland) to conduct scientific investigations and experiments.
1978 August 26 - 14:51 GMT - Launch Vehicle: Soyuz. Soyuz 31 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 193 km (119 mi). Apogee: 243 km (150 mi). Inclination: 51.60 deg. Period: 88.80 min. Crew: Bykovsky, Jaehn. Flight: Salyut 6 EP-4, Salyut 6 EO-2. Manned two crew. Docked with Salyut 6. Delivered to the Salyut-6 station the third international 'Intercosmos' crew consisting of V F Bykovsky (USSR) and S Jaehn (German Democratic Republic) to carry out scientific research and experiments.
1978 October 3 - 23:09 GMT - Launch Vehicle: Soyuz. Progress 4 Mass: 7,014 kg (15,463 lb). Spacecraft: Progress. Agency: MOM. Perigee: 185 km (114 mi). Apogee: 247 km (153 mi). Inclination: 51.70 deg. Period: 88.80 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 6 Oct 1978 01:00:15 GMT. Undocked on 24 Oct 1978 13:01:52 GMT. Destroyed in reentry on 26 Oct 1978 16:28:13 GMT. Total free-flight time 4.22 days. Total docked time 18.50 days.
1978 December 8 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 1060 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-2M. Agency: MOM. Perigee: 216 km (134 mi). Apogee: 291 km (180 mi). Inclination: 65.00 deg. Period: 89.50 min. Area survey photo reconnaissance satellite; returned film capsule.
1979 January 25 - 05:43 GMT - Launch Vehicle: Soyuz. Meteor 1-29 Mass: 3,800 kg (8,300 lb). Spacecraft: Meteor-Priroda. Agency: MOM. Perigee: 546 km (339 mi). Apogee: 596 km (370 mi). Inclination: 97.80 deg. Period: 96.10 min. Obtaining information needed for research into the natural resources of the earth and the development of methods for remote sensing of the underlying surface, and obtaining meteorological information. In addition to Soviet apparatus, carried scientific ap paratus from the German Democratic Republic.
1979 July 10 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 1113 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MKM. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 330 km (200 mi). Inclination: 65.00 deg. Period: 89.50 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1979 August 11 - 09:15 GMT - Launch Vehicle: Soyuz. Cosmos 1120 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MKM. Agency: MOM. Perigee: 170 km (100 mi). Apogee: 362 km (224 mi). Inclination: 70.60 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1980 April 1 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 1170 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MKM. Agency: MOM. Perigee: 178 km (110 mi). Apogee: 379 km (235 mi). Inclination: 70.40 deg. Period: 90.10 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1980 April 17 - 08:30 GMT - Launch Vehicle: Soyuz. Cosmos 1173 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-4MKM. Agency: MOM. Perigee: 174 km (108 mi). Apogee: 352 km (218 mi). Inclination: 70.30 deg. Period: 89.80 min. High resolution photo reconnaissance satellite; returned film capsule; maneuverable.
1980 April 27 - 06:24 GMT - Launch Vehicle: Soyuz. Progress 9 Mass: 7,014 kg (15,463 lb). Spacecraft: Progress. Agency: MOM. Perigee: 185 km (114 mi). Apogee: 255 km (158 mi). Inclination: 51.70 deg. Period: 88.80 min. Flight: Salyut 6 EO-4. Unmanned supply vessel for Salyut 6. Delivery of various cargoes to the Salyut-6 orbital station. Docked with Salyut 6 on 29 Apr 1980 08:09:19 GMT. Undocked on 20 May 1980 18:51:00 GMT. Destroyed in reentry on 22 May 1980 00:44:00 GMT. Total free-flight time 3.32 days. Total docked time 21.45 days.
1980 June 5 - 14:19 GMT - Launch Vehicle: Soyuz. Soyuz T-2 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 195 km (121 mi). Apogee: 232 km (144 mi). Inclination: 51.60 deg. Period: 88.70 min. Crew: Aksyonov, Malyshev. Flight: Salyut 6 EP-6, Salyut 6 EO-4. Test flight of new Soyuz T; docked with Salyut 6. Conducted testing and development of on-board systems in the improved Soyuz T series transport vehicle under piloted conditions.
1980 June 18 - 06:14 GMT - Launch Vehicle: Soyuz. Meteor 1-30 Mass: 3,475 kg (7,661 lb). Spacecraft: Resurs-OE. Agency: MOM. Perigee: 428 km (265 mi). Apogee: 457 km (283 mi). Inclination: 97.70 deg. Period: 93.40 min. First flight of prototype for Resurs-O1 spacecraft. Also performed remote sensing tasks. Acquisition of information required for continued investigation of the natural resources of the earth; development of remote sensing methods for measuring the status of the earth's surface and the atmosphere beneath the satellite.
1980 June 29 - 04:40 GMT - Launch Vehicle: Soyuz. Progress 10 Mass: 7,014 kg (15,463 lb). Spacecraft: Progress. Agency: MOM. Perigee: 183 km (113 mi). Apogee: 264 km (164 mi). Inclination: 51.60 deg. Period: 89.00 min. Flight: Salyut 6 EO-4. Unmanned supply vessel for Salyut 6. Delivery of various cargoes to the Salyut-6 orbital station. Docked with Salyut 6 on 1 Jul 1980 05:53:00 GMT. Undocked on 17 Jul 1980 22:21:00 GMT. Destroyed in reentry on 19 Jul 1980 01:47:00 GMT. Total free-flight time 3.19 days. Total docked time 16.69 days.
1980 July 23 - 18:33 GMT - Launch Vehicle: Soyuz. Soyuz 37 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 190 km (110 mi). Apogee: 273 km (169 mi). Inclination: 51.50 deg. Period: 89.10 min. Crew: Gorbatko, Tuan. Flight: Salyut 6 EP-7, Salyut 6 EO-4. Manned two crew. Transported to the Salyut-6 station the sixth international crew under the Intercosmos programme, comprising V V Gorbatko (USSR) and Pham Tuan (Viet Nam), to conduct scientific research and experiments. Returned crew of Soyuz 35 to Earth. Recovered October 11, 1980 9:50 GMT.
1980 September 18 - 19:11 GMT - Launch Vehicle: Soyuz. Soyuz 38 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 195 km (121 mi). Apogee: 257 km (159 mi). Inclination: 51.60 deg. Period: 89.00 min. Crew: Romanenko, Tamayo-Mendez. Flight: Salyut 6 EP-8, Salyut 6 EO-4. Manned two crew. Docked with Salyut 6. Transported to the Salyut-6 station the seventh international crew under the INTERCOSMOS programme, comprising Y V Romanenko (USSR) and A. Tomaio Mendez (Cuba), to conduct scientific research and experiments.
1980 September 28 - 15:09 GMT - Launch Vehicle: Soyuz. Progress 11 Mass: 7,014 kg (15,463 lb). Spacecraft: Progress. Agency: MOM. Perigee: 188 km (116 mi). Apogee: 241 km (149 mi). Inclination: 51.60 deg. Period: 88.70 min. Flight: Salyut 6 EO-4. 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.
1980 November 27 - 14:18 GMT - Launch Vehicle: Soyuz. Soyuz T-3 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 256 km (159 mi). Apogee: 260 km (160 mi). Inclination: 51.60 deg. Period: 89.70 min. Crew: Kizim, Makarov, Strekalov. Flight: Salyut 6 EO-5. Manned three crew. Docked with Salyut 6. Tested the improved transport ship of the 'SOYUZ T' series; transported to the Salyut-6 orbital station a crew consisting of L D Kizim, O G Makarov and G M Strekalov to carry out repair and preventive work and scientific and technical investigation and experiments.
1981 January 24 - 14:18 GMT - Launch Vehicle: Soyuz. Progress 12 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 247 km (153 mi). Apogee: 308 km (191 mi). Inclination: 51.70 deg. Period: 90.00 min. Unmanned supply vessel to Salyut 6. Delivery of various cargoes to the Salyut-6 orbital station. Docked with Salyut 6 on 26 Jan 1981 15:56:00 GMT. Undocked on 19 Mar 1981 18:14:00 GMT. Destroyed in reentry on 20 Mar 1981 16:59:00 GMT. Total free-flight time 3.02 days. Total docked time 52.10 days.
1981 March 12 - 19:00 GMT - Launch Vehicle: Soyuz. Soyuz T-4 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 201 km (124 mi). Apogee: 237 km (147 mi). Inclination: 51.60 deg. Period: 88.90 min. Crew: Kovalyonok, Savinykh. Flight: Salyut 6 EO-6. Manned two crew. Docked with Salyut 6. Transported to the Salyut-6 orbital station cosmonauts V V Kovalenok and V P Savinykh to carry out repairs and preventive maintenance and scientific and technical investigations and experiments.
1981 April 15 - 10:30 GMT - Launch Vehicle: Soyuz. Cosmos 1264 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 382 km (237 mi). Inclination: 70.40 deg. Period: 90.40 min. Photo surveillance; returned film capsule.
1981 April 28 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 1268 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 366 km (227 mi). Inclination: 70.40 deg. Period: 90.30 min. Photo surveillance; returned film capsule; maneuverable.
1981 May 14 - 17:16 GMT - Launch Vehicle: Soyuz. Soyuz 40 Mass: 6,800 kg (14,900 lb). Spacecraft: Soyuz 7K-T. Agency: MOM. Perigee: 192 km (119 mi). Apogee: 270 km (160 mi). Inclination: 51.60 deg. Period: 89.10 min. Crew: Popov, Prunariu. Flight: Salyut 6 EP-10, Salyut 6 EO-6. Manned two crew. Docked with Salyut 6. Transported to the Salyut-6 orbital station the ninth international crew under the INTERCOSMOS programme, comprising L I Popov (USSR), and D. Prunariu (Romania), to conduct scientific research and experiments.
1981 May 21 - 09:10 GMT - Launch Vehicle: Soyuz. Cosmos 1272 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 376 km (233 mi). Inclination: 70.40 deg. Period: 90.30 min. Photo surveillance; returned film capsule.
1981 June 17 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 1277 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 373 km (231 mi). Inclination: 70.40 deg. Period: 90.30 min. Photo surveillance; returned film capsule.
1981 July 1 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 1279 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 364 km (226 mi). Inclination: 70.40 deg. Period: 90.20 min. Photo surveillance; returned film capsule; maneuverable.
1981 July 10 - 05:14 GMT - Launch Vehicle: Soyuz. Meteor 1-31 Mass: 3,800 kg (8,300 lb). Spacecraft: Meteor-Priroda. Agency: MOM. Perigee: 574 km (356 mi). Apogee: 612 km (380 mi). Inclination: 97.90 deg. Period: 96.50 min. Also performed earth resources tasks. Acquisition of information required for continued investigation of the natural resources of the earth; development of remote sensing methods for measuring the parameters of the atmosphere and the earth's surface beneath the satellite. Carried scientific i nstruments developed in the People's Republic of Bulgaria, as well as Soviet equipment. Objects 1595 and 1596 launched by a single rocket.
1981 August 21 - 10:20 GMT - Launch Vehicle: Soyuz. Cosmos 1298 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 170 km (100 mi). Apogee: 328 km (203 mi). Inclination: 64.80 deg. Period: 89.40 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.
1981 September 4 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 1303 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 208 km (129 mi). Apogee: 363 km (225 mi). Inclination: 70.40 deg. Period: 90.20 min. Photo surveillance; returned film capsule.
1981 October 1 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 1313 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 286 km (177 mi). Inclination: 70.40 deg. Period: 89.40 min. Photo surveillance; returned film capsule; maneuverable.
1981 October 15 - 09:15 GMT - Launch Vehicle: Soyuz. Cosmos 1316 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 381 km (236 mi). Inclination: 70.30 deg. Period: 90.40 min. Photo surveillance; returned film capsule; maneuverable.
1981 November 13 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 1319 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 374 km (232 mi). Inclination: 70.40 deg. Period: 90.30 min. Photo surveillance; returned film capsule.
1981 December 4 - 09:50 GMT - Launch Vehicle: Soyuz. Cosmos 1329 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 231 km (143 mi). Apogee: 273 km (169 mi). Inclination: 65.00 deg. Period: 89.50 min. Photo surveillance; returned film capsule; maneuverable.
1981 December 23 - 13:15 GMT - Launch Vehicle: Soyuz. Molniya 1-52 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1T. Agency: MOM. Perigee: 2,097 km (1,303 mi). Apogee: 38,267 km (23,777 mi). Inclination: 63.80 deg. Period: 718.00 min. Replaced Molniya 1-45. Uncertain if Molniya-1T model was Molniya-1 or Molniya-1T. Operation of the long-range telephone and telegraph radio communications system in the USSR; transmission of USSR Central Television programmes to stations in the Orbita network.
1982 April 2 - 10:15 GMT - Launch Vehicle: Soyuz. Cosmos 1347 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 172 km (106 mi). Apogee: 337 km (209 mi). Inclination: 70.40 deg. Period: 89.60 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 April 21 - 09:15 GMT - Launch Vehicle: Soyuz. Cosmos 1352 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 364 km (226 mi). Inclination: 70.40 deg. Period: 90.10 min. Photo surveillance; returned film capsule.
1982 May 13 - 09:58 GMT - Launch Vehicle: Soyuz. Soyuz T-5 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 190 km (110 mi). Apogee: 231 km (143 mi). Inclination: 51.60 deg. Period: 88.70 min. Crew: Berezovoi, Lebedev. Flight: Salyut 7 EO-1. Carried Anatoli Berezovoi, Valentin Lebedev to Salyut 7 to conduct scientific research and experiments; returned crew of Soyuz T-7 to Earth.
1982 May 21 - 12:40 GMT - Launch Vehicle: Soyuz. Cosmos 1368 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 338 km (210 mi). Inclination: 70.40 deg. Period: 89.90 min. Photo surveillance; returned film capsule; maneuverable.
1982 May 23 - 05:58 GMT - Launch Vehicle: Soyuz. Progress 13 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 186 km (115 mi). Apogee: 263 km (163 mi). Inclination: 51.60 deg. Period: 89.00 min. Flight: Salyut 7 EO-1. Unmanned supply vessel to Salyut 7. Transport of various cargoes to the Salyut-7 orbital station. Docked with Salyut 7 on 25 May 1982 07:56:36 GMT. Undocked on 4 Jun 1982 06:31:00 GMT. Destroyed in reentry on 6 Jun 1982 00:05:00 GMT. Total free-flight time 3.81 days. Total docked time 9.94 days.
1982 May 28 - 09:10 GMT - Launch Vehicle: Soyuz. Cosmos 1370 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 195 km (121 mi). Apogee: 273 km (169 mi). Inclination: 64.90 deg. Period: 89.20 min. Military topographic / cartographic satellite.
1982 June 2 - 12:50 GMT - Launch Vehicle: Soyuz. Cosmos 1373 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 210 km (130 mi). Apogee: 347 km (215 mi). Inclination: 70.40 deg. Period: 90.10 min. Photo surveillance; returned film capsule.
1982 June 12 - Launch Vehicle: Soyuz. FAILURE: Failure. Yantar-4K1 Spacecraft: Yantar-4K1. Agency: UNKS. 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 June 18 - 13:00 GMT - Launch Vehicle: Soyuz. Cosmos 1381 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 199 km (123 mi). Apogee: 374 km (232 mi). Inclination: 70.40 deg. Period: 90.30 min. Photo surveillance; returned film capsule.
1982 June 24 - 16:29 GMT - Launch Vehicle: Soyuz. Soyuz T-6 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 189 km (117 mi). Apogee: 233 km (144 mi). Inclination: 51.70 deg. Period: 88.70 min. Crew: Chretien, Dzhanibekov, Ivanchenkov. Flight: Salyut 7 EP-1, Salyut 7 EO-1. Manned three crew. Docked with Salyut 7. Transported to the Salyut-7 orbital station the Soviet-French international crew, comprising V A Dzhanibekov (USSR), A S Ivanchenkov (USSR) and Jean-Loup Chretien (France) to conduct scientific research and experiments.
1982 July 10 - 09:57 GMT - Launch Vehicle: Soyuz. Progress 14 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 301 km (187 mi). Apogee: 325 km (201 mi). Inclination: 51.60 deg. Period: 90.70 min. Flight: Salyut 7 EO-1. Unmanned supply vessel to Salyut 7. Docked with Salyut 7 on 12 Jul 1982 11:41:00 GMT. Undocked on 10 Aug 1982 22:11:00 GMT. Destroyed in reentry on 13 Aug 1982 01:29:00 GMT. Total free-flight time 4.21 days. Total docked time 29.44 days.
1982 July 21 - 09:40 GMT - Launch Vehicle: Soyuz. Molniya 1-55 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1T. Agency: MOM. Perigee: 160 km (90 mi). Apogee: 39,618 km (24,617 mi). Inclination: 63.90 deg. Period: 706.20 min. Uncertain if Molniya-1T model was Molniya-1 or Molniya-1T. Operation of the long-range telephone and telegraph radio communications system in the USSR; transmission of USSR Central Television programmes to stations in the Orbita network.
1982 August 19 - 17:11 GMT - Launch Vehicle: Soyuz. Soyuz T-7 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 289 km (179 mi). Apogee: 299 km (185 mi). Inclination: 51.60 deg. Period: 90.30 min. Crew: Popov, Savitskaya, Serebrov. Flight: Salyut 7 EP-2, Salyut 7 EO-1. Docked with Salyut 7. Carried Svetlana Savitskaya, Leonid Popov, Alexander Serebrov to Salyut 7 to conduct scientific and technical research and experiments.
1982 September 1 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 1403 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 353 km (219 mi). Inclination: 70.40 deg. Period: 90.10 min. Photo surveillance; returned film capsule.
1982 September 18 - 04:58 GMT - Launch Vehicle: Soyuz. Progress 15 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 188 km (116 mi). Apogee: 241 km (149 mi). Inclination: 51.70 deg. Period: 88.80 min. Flight: Salyut 7 EO-1. Unmanned supply vessel to Salyut 7. Docked with Salyut 7 on 20 Sep 1982 06:12:00 GMT. Undocked on 14 Oct 1982 13:46:00 GMT. Destroyed in reentry on 16 Oct 1982 17:08:00 GMT. Total free-flight time 4.19 days. Total docked time 24.32 days.
1982 October 14 - 09:10 GMT - Launch Vehicle: Soyuz. Cosmos 1416 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 231 km (143 mi). Apogee: 278 km (172 mi). Inclination: 70.40 deg. Period: 89.60 min. Photo surveillance; returned film capsule; maneuverable.
1982 October 31 - 11:20 GMT - Launch Vehicle: Soyuz. Progress 16 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 186 km (115 mi). Apogee: 246 km (152 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Salyut 7 EO-1. Unmanned supply vessel to Salyut 7. Docked with Salyut 7 on 2 Nov 1982 13:22:00 GMT. Undocked on 13 Dec 1982 15:32:00 GMT. Destroyed in reentry on 14 Dec 1982 17:17:00 GMT. Total free-flight time 3.16 days. Total docked time 41.09 days.
1982 November 2 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 1419 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 264 km (164 mi). Inclination: 70.30 deg. Period: 89.20 min. Photo surveillance; returned film capsule; maneuverable.
1982 November 18 - 09:25 GMT - Launch Vehicle: Soyuz. Cosmos 1421 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 259 km (160 mi). Inclination: 70.30 deg. Period: 89.20 min. Photo surveillance; returned film capsule; maneuverable.
1982 December 8 - 13:46 GMT - Launch Vehicle: Soyuz. FAILURE: Fourth stage failure. Cosmos 1423 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1T. Agency: MOM. Perigee: 348 km (216 mi). Apogee: 571 km (354 mi). Inclination: 62.80 deg. Period: 93.80 min. Intended to replace Molniya 1-48; failed. Investigation of the upper atmosphere and outer space.
1982 December 23 - 09:10 GMT - Launch Vehicle: Soyuz. Cosmos 1425 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 220 km (130 mi). Apogee: 352 km (218 mi). Inclination: 70.00 deg. Period: 90.20 min. Photo surveillance; returned film capsule.
1983 January 27 - 08:30 GMT - Launch Vehicle: Soyuz. Cosmos 1438 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 226 km (140 mi). Inclination: 70.40 deg. Period: 88.80 min. Photo surveillance; returned film capsule; maneuverable.
1983 March 16 - 08:50 GMT - Launch Vehicle: Soyuz. Cosmos 1446 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 223 km (138 mi). Apogee: 343 km (213 mi). Inclination: 69.90 deg. Period: 90.20 min. Photo surveillance; returned film capsule; maneuverable.
1983 April 2 - 02:02 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-ML Molniya 1-57 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1T. Agency: MOM. Perigee: 802 km (498 mi). Apogee: 39,551 km (24,575 mi). Inclination: 63.90 deg. Period: 717.80 min. Replaced Molniya 1-52. Operation of the long-range telephone and telegraph radio communications system in the USSR; transmission of USSR Central Television programmes to stations in the Orbita network.
1983 April 20 - 13:10 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 372 Soyuz T-8 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 196 km (121 mi). Apogee: 213 km (132 mi). Inclination: 51.60 deg. Period: 88.60 min. Crew: Serebrov, Strekalov, Titov Vladimir. Flight: Soyuz T-8. Manned three crew. Unsuccessful mission. Failed to rendezvous with Salyut 7. Recovered April 22, 1983 13:29 GMT. Landed 113 km SE Arkalyk.
1983 May 6 - 09:10 GMT - Launch Vehicle: Soyuz. Cosmos 1460 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 344 km (213 mi). Inclination: 70.30 deg. Period: 90.00 min. Photo surveillance; returned film capsule.
1983 June 27 - 09:12 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 379 Soyuz T-9 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 197 km (122 mi). Apogee: 228 km (141 mi). Inclination: 51.60 deg. Period: 88.80 min. Crew: Aleksandrov, Lyakhov. Flight: Salyut 7 EO-2. Manned two crew. Docked with Salyut 7. Transported to the Salyut-7 orbital station a crew consisting of V A Lyakhov, commander of the spacecraft, and A P Aleksandrov, flight engineer, to conduct scientific and technical research and experiments.
1983 July 13 - 09:40 GMT - Launch Vehicle: Soyuz. Cosmos 1482 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 207 km (128 mi). Apogee: 350 km (210 mi). Inclination: 70.00 deg. Period: 90.10 min. Medium resolution photo surveillance; film capsule. Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation.
1983 July 19 - 15:14 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-ML Molniya 1-58 Mass: 1,600 kg (3,500 lb). Spacecraft: Molniya-1T. Agency: MOM. Perigee: 200 km (120 mi). Apogee: 25,838 km (16,054 mi). Inclination: 63.50 deg. Period: 448.10 min. Replaced Molniya 1-49. Operation of the long-range telephone and telegraph radio communications system in the USSR; transmission of USSR Central Television programmes to stations in the Orbita network.
1983 August 17 - 12:08 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U Ts15000-302 Progress 17 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 189 km (117 mi). Apogee: 242 km (150 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Salyut 7 EO-2. Unmanned supply vessel to Salyut 7. Docked with Salyut 7 on 19 Aug 1983 13:47:00 GMT. Undocked on 17 Sep 1983 11:44:00 GMT. Destroyed in reentry on 17 Sep 1983 23:43:00 GMT. Total free-flight time 2.57 days. Total docked time 28.91 days.
1983 September 26 - 19:37 GMT - Launch Vehicle: Soyuz. FAILURE: Launch vehicle blew up on pad. Soyuz T-10-1 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: UNKS. Apogee: 2.00 km (1.20 mi). Crew: Strekalov, Titov Vladimir. Flight: Soyuz T-10-1, Salyut 7 EO-2. Aborted September 27, 1983 19:38 GMT. Unsuccessful mission. Launch vehicle blew up on pad at Tyuratam; crew saved by abort system.
1983 December 27 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 1516 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 194 km (120 mi). Apogee: 274 km (170 mi). Inclination: 64.90 deg. Period: 89.20 min. Military topographic / cartographic satellite.
1984 January 26 - 08:50 GMT - Launch Vehicle: Soyuz. Cosmos 1533 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 222 km (137 mi). Apogee: 354 km (219 mi). Inclination: 70.40 deg. Period: 90.30 min. Photo surveillance; returned film capsule.
1984 March 7 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 1542 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-6U. Agency: MOM. Perigee: 223 km (138 mi). Apogee: 346 km (214 mi). Inclination: 70.30 deg. Period: 90.20 min. Photo surveillance; returned film capsule.
1984 May 14 - 14:00 GMT - Launch Vehicle: Soyuz. Cosmos 1552 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 180 km (110 mi). Apogee: 320 km (190 mi). Inclination: 64.90 deg. Period: 89.50 min. Photo/digital surveillance.
1984 June 11 - 08:40 GMT - Launch Vehicle: Soyuz. Cosmos 1571 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 213 km (132 mi). Apogee: 362 km (224 mi). Inclination: 69.90 deg. Period: 90.30 min. Military cartographic satellite; returned film capsule.
1984 July 31 - 12:29 GMT - Launch Vehicle: Soyuz. Cosmos 1585 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 172 km (106 mi). Apogee: 300 km (180 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.
1984 August 14 - 06:28 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 711 Progress 23 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 186 km (115 mi). Apogee: 250 km (150 mi). Inclination: 51.60 deg. Period: 88.90 min. Flight: Salyut 7 EO-3. Transport of various cargoes to the Salyut-7 orbital station. Docked with Salyut 7 on 16 Aug 1984 08:11:00 GMT. Undocked on 26 Aug 1984 16:13:00 GMT. Destroyed in reentry on 28 Aug 1984 01:28:00 GMT. Total free-flight time 3.46 days. Total docked time 10.33 days.
1984 September 27 - 08:10 GMT - Launch Vehicle: Soyuz. Cosmos 1600 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 201 km (124 mi). Apogee: 377 km (234 mi). Inclination: 70.00 deg. Period: 90.30 min. Military cartographic satellite; returned film capsule.
1984 November 14 - 07:40 GMT - Launch Vehicle: Soyuz. Cosmos 1608 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 195 km (121 mi). Apogee: 248 km (154 mi). Inclination: 70.00 deg. Period: 88.90 min. Military topographic / cartographic satellite.
1984 November 21 - 10:30 GMT - Launch Vehicle: Soyuz. Cosmos 1611 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 172 km (106 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.
1985 January 9 - 10:45 GMT - Launch Vehicle: Soyuz. Cosmos 1616 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 171 km (106 mi). Apogee: 356 km (221 mi). Inclination: 64.90 deg. Period: 89.80 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.
1985 January 16 - 08:19 GMT - Launch Vehicle: Soyuz. Cosmos 1623 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 198 km (123 mi). Apogee: 387 km (240 mi). Inclination: 70.00 deg. Period: 90.40 min. Military cartographic satellite; returned film capsule.
1985 February 27 - 11:10 GMT - Launch Vehicle: Soyuz. Cosmos 1630 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 173 km (107 mi). Apogee: 332 km (206 mi). Inclination: 64.90 deg. Period: 89.60 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.
1985 March 25 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 1643 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 182 km (113 mi). Apogee: 276 km (171 mi). Inclination: 64.80 deg. Period: 89.10 min. Photo/digital surveillance.
1985 April 3 - 08:40 GMT - Launch Vehicle: Soyuz. Cosmos 1644 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 335 km (208 mi). Inclination: 70.30 deg. Period: 90.30 min. Military cartographic satellite; returned film capsule.
1985 May 23 - 12:40 GMT - Launch Vehicle: Soyuz. Cosmos 1654 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 170 km (100 mi). Apogee: 341 km (211 mi). Inclination: 64.90 deg. Period: 89.60 min. High resolution photo reconnaissance. Spacecraft failed. Blown up in orbit on June 21.
1985 June 6 - 06:39 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 002 Soyuz T-13 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 198 km (123 mi). Apogee: 222 km (137 mi). Inclination: 51.60 deg. Period: 88.70 min. Crew: Dzhanibekov, Savinykh. Flight: Salyut 7 EO-4-1a, Salyut 7 EO-4-1b. Docked with Salyut 7. Delivered to the Salyut-7 orbital station a crew consisting of flight commander V A Dzhanibekov and flight engineer V P Savinykh to carry out emergency repairs to inert Salyut 7 station and to conduct scientific and technical research and experiments.
1985 June 21 - 00:39 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 417 Progress 24 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 189 km (117 mi). Apogee: 251 km (155 mi). Inclination: 51.60 deg. Period: 88.90 min. Flight: Salyut 7 EO-4-1a, Salyut 7 EO-4-1b. Delivery to the Salyut-7 orbital station of a mixed cargo with a total mass of 2,000 kg. Docked with Salyut 7 on 23 Jun 1985 02:54:00 GMT. Undocked on 15 Jul 1985 12:28:00 GMT. Destroyed in reentry on 15 Jul 1985 22:33:31 GMT. Total free-flight time 2.51 days. Total docked time 22.40 days.
1985 July 15 - 06:30 GMT - Launch Vehicle: Soyuz. Cosmos 1668 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 271 km (168 mi). Inclination: 70.40 deg. Period: 89.30 min. Military cartographic satellite; returned film capsule; maneuverable.
1985 July 19 - 13:05 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 446 Cosmos 1669 Mass: 7,020 kg (15,470 lb). Spacecraft: Progress. Agency: MOM. Perigee: 187 km (116 mi). Apogee: 247 km (153 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Salyut 7 EO-4-1a, Salyut 7 EO-4-1b. Progress vehicle, given Cosmos designation instead of Progress because control lost early in mission but regained later. Resupplied Salyut 7. On departure briefly undocked and redocked to verify reliability of docking system. Transported of various cargoes to the Salyut-7 orbital station. Docked with Salyut 7 on 21 Jul 1985 15:05:00 GMT. Undocked on 28 Aug 1985 21:50:00 GMT. Destroyed in reentry on 30 Aug 1985 01:20:00 GMT. Total free-flight time 3.23 days. Total docked time 38.28 days.
1985 August 8 - 10:19 GMT - Launch Vehicle: Soyuz. Cosmos 1673 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 195 km (121 mi). Apogee: 271 km (168 mi). Inclination: 64.80 deg. Period: 89.20 min. Military topographic / cartographic satellite.
1985 August 29 - 11:33 GMT - Launch Vehicle: Soyuz. Cosmos 1679 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 172 km (106 mi). Apogee: 341 km (211 mi). Inclination: 64.90 deg. Period: 89.60 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.
1985 September 17 - 12:38 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 007 Soyuz T-14 Mass: 6,850 kg (15,100 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 196 km (121 mi). Apogee: 223 km (138 mi). Inclination: 51.60 deg. Period: 88.70 min. Crew: Grechko, Vasyutin, Volkov Aleksandr. Flight: Salyut 7 EO-4-2, Salyut 7 EP-5, Salyut 7 EO-4-1a, Salyut 7 EO-4-1b. Docked with Salyut 7. Transported a crew comprising ship's commander V V Vasyutin, flight engineer G M Grechko and cosmonaut-researcher A A Volkov to the Salyut-7 orbital station to conduct scientific and technical studies and experiments. Grechko returned in Soyuz T-13 on 25 September 1985 - emergency return.
1985 October 16 - 09:25 GMT - Launch Vehicle: Soyuz. Cosmos 1696 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 270 km (160 mi). Inclination: 70.40 deg. Period: 89.30 min. Military cartographic satellite; returned film capsule; maneuverable.
1985 October 23 - 00:42 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-ML Molniya 1-65 Mass: 1,800 kg (3,900 lb). Spacecraft: Molniya-1T. Agency: MOM. Perigee: 1,104 km (685 mi). Apogee: 39,239 km (24,381 mi). Inclination: 64.50 deg. Period: 717.60 min. Replaced Molniya 1-58. Operation of the long-range telephone and telegraph radio communications system in the USSR; transmission of USSR Central Television programmes to stations in the Orbita network.
1986 January 28 - 08:35 GMT - Launch Vehicle: Soyuz. Cosmos 1728 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 278 km (172 mi). Inclination: 70.00 deg. Period: 89.30 min. Military cartographic satellite; returned film capsule.
1986 February 7 - 08:45 GMT - Launch Vehicle: Soyuz. Cosmos 1731 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 233 km (144 mi). Apogee: 263 km (163 mi). Inclination: 64.70 deg. Period: 89.50 min. Photo/digital surveillance.
1986 March 13 - 12:33 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 012 Soyuz T-15 Mass: 7,020 kg (15,470 lb). Spacecraft: Soyuz T. Agency: MOM. Perigee: 331 km (205 mi). Apogee: 366 km (227 mi). Inclination: 51.60 deg. Period: 91.50 min. Crew: Kizim, Solovyov Vladimir. Flight: Mir EO-1. Mir Main Expedition EO-01. Epic repair mission. The crew, consisting of ship's commander L D Kizim and flight engineer V A Solovyov first docked with the Mir orbital station to conduct scientific and technical studies and experiments. Mir then maneuvered 17 April to match Salyut 7's orbit at 4000 km separation, then again on 4 May to catch up. After six weeks aboard Mir, Soyuz T-15 undocked on 5 May, then rendezvoused and manually docked with the inoperative Salyut 7 station. This was the only flight in history by a single spacecraft between two space stations. The Salyut-7 station was found to be ice bound and without electrical power. The crew repaired the station, regaining power, heat, and environmental control. The also removed experimental results left behind by last crew. Soyuz T-15 undocked Salyut 7 on 25 June, and redocked with Mir on 26 June, delivering 400 kg of scientific material from Salyut 7, including a multichannel spectrometer. Following further work aboard Mir, the crew landed on July 16, 1986 at 12:34 GMT. No crew ever revisited Salyut 7; it made an uncontrolled reentry over Argentina.
1986 March 19 - 10:08 GMT - Launch Vehicle: Soyuz. Progress 25 Mass: 7,270 kg (16,020 lb). Spacecraft: Progress. Agency: MOM. Perigee: 183 km (113 mi). Apogee: 251 km (155 mi). Inclination: 51.70 deg. Period: 88.80 min. Flight: Mir EO-1. Unmanned supply vessel transporting sundry cargoes to the Mir orbital station. Docked with Mir on 21 Mar 1986 11:16:02 GMT. Undocked on 20 Apr 1986 19:24:08 GMT. Destroyed in reentry on 21 Apr 1986 00:48:30 GMT. Total free-flight time 2.27 days. Total docked time 30.34 days.
1986 March 26 - Launch Vehicle: Soyuz. FAILURE: Failure. Zenit-8 Spacecraft: Zenit-8. Agency: UNKS. Military cartographic mission.
1986 April 9 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 1739 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 171 km (106 mi). Apogee: 326 km (202 mi). Inclination: 64.90 deg. Period: 89.50 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.
1986 April 23 - 19:40 GMT - Launch Vehicle: Soyuz. Progress 26 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress. Agency: MOM. Perigee: 184 km (114 mi). Apogee: 257 km (159 mi). Inclination: 51.60 deg. Period: 88.90 min. Flight: Mir EO-1. Unmanned supply vessel to Mir. Rendezvoused with Mir on 25 April, but problem with Mir's radio communication system delays docking until the next day. Docked with Mir on 26 Apr 1986 21:26:06 GMT. Undocked on 22 Jun 1986 18:25:00 GMT. Destroyed in reentry on 23 Jun 1986 15:41:01 GMT. Total free-flight time 3.96 days. Total docked time 56.87 days.
1986 May 21 - 08:21 GMT - Launch Vehicle: Soyuz. Soyuz TM-1 Mass: 7,070 kg (15,580 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 192 km (119 mi). Apogee: 225 km (139 mi). Inclination: 51.60 deg. Period: 88.70 min. Flight: Mir EO-1. Test of new Soyuz vehicle. Recovered May 30, 1986 6:49 GMT. Unmanned test of Soyuz TM. Docked with Mir May 23 1987. Undocked 29 May.
Officially: Comprehensive experimental testing of spacecraft in independent flight and jointly with the Mir orbital station.
1986 May 29 - 09:20 GMT - Launch Vehicle: Soyuz. Cosmos 1747 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 389 km (241 mi). Inclination: 70.30 deg. Period: 90.50 min. Military cartographic satellite; returned film capsule.
1986 June 6 - 12:40 GMT - Launch Vehicle: Soyuz. Cosmos 1756 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 172 km (106 mi). Apogee: 268 km (166 mi). Inclination: 64.90 deg. Period: 88.90 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.
1986 June 19 - 10:30 GMT - Launch Vehicle: Soyuz. Cosmos 1760 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 348 km (216 mi). Apogee: 412 km (256 mi). Inclination: 70.00 deg. Period: 92.20 min. Military cartographic satellite; returned film capsule.
1986 July 17 - 12:30 GMT - Launch Vehicle: Soyuz. Cosmos 1764 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 171 km (106 mi). Apogee: 339 km (210 mi). Inclination: 64.90 deg. Period: 89.60 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.
1986 August 6 - 13:30 GMT - Launch Vehicle: Soyuz. Cosmos 1770 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 234 km (145 mi). Apogee: 292 km (181 mi). Inclination: 64.70 deg. Period: 89.80 min. Photo/digital surveillance.
1986 August 27 - 11:40 GMT - Launch Vehicle: Soyuz. Cosmos 1773 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 171 km (106 mi). Apogee: 339 km (210 mi). Inclination: 64.90 deg. Period: 89.60 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.
1986 September 3 - 07:59 GMT - Launch Vehicle: Soyuz. Cosmos 1775 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 345 km (214 mi). Apogee: 412 km (256 mi). Inclination: 70.40 deg. Period: 92.10 min. Military cartographic satellite; returned film capsule.
1986 September 17 - 07:59 GMT - Launch Vehicle: Soyuz. Cosmos 1781 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 203 km (126 mi). Apogee: 379 km (235 mi). Inclination: 70.40 deg. Period: 90.40 min. Military cartographic satellite; returned film capsule.
1986 October 6 - 07:40 GMT - Launch Vehicle: Soyuz. Cosmos 1784 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 190 km (110 mi). Apogee: 283 km (175 mi). Inclination: 64.80 deg. Period: 89.20 min. Military topographic / cartographic satellite.
1986 October 22 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 1787 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 211 km (131 mi). Apogee: 262 km (162 mi). Inclination: 70.00 deg. Period: 89.20 min. Military cartographic satellite; returned film capsule.
1986 November 13 - 10:59 GMT - Launch Vehicle: Soyuz. Cosmos 1792 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 184 km (114 mi). Apogee: 309 km (192 mi). Inclination: 64.90 deg. Period: 89.40 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.
1986 December 4 - 10:10 GMT - Launch Vehicle: Soyuz. Cosmos 1804 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 198 km (123 mi). Apogee: 421 km (261 mi). Inclination: 70.00 deg. Period: 90.70 min. Military cartographic satellite; returned film capsule.
1986 December 26 - 11:00 GMT - Launch Vehicle: Soyuz. Cosmos 1810 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 224 km (139 mi). Apogee: 275 km (170 mi). Inclination: 64.70 deg. Period: 89.50 min. Photo/digital surveillance.
1987 January 9 - 12:38 GMT - Launch Vehicle: Soyuz. Cosmos 1811 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 169 km (105 mi). Apogee: 345 km (214 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.
1987 January 16 - 06:06 GMT - Launch Vehicle: Soyuz. Progress 27 Mass: 7,230 kg (15,930 lb). Spacecraft: Progress. Agency: MOM. Perigee: 183 km (113 mi). Apogee: 263 km (163 mi). Inclination: 51.60 deg. Period: 89.00 min. Flight: Mir EO-2, Mir LD-1. Unmanned supply vessel to Mir; raised Mir's orbit. Transported sundry cargoes to the Mir orbital station. Docked with Salyut 7 on 18 Jan 1987 07:26:50 GMT. Undocked on 23 Feb 1987 11:29:01 GMT. Destroyed in reentry on 25 Feb 1987 16:05:00 GMT. Total free-flight time 4.25 days. Total docked time 36.17 days.
1987 February 5 - 21:38 GMT - Launch Vehicle: Soyuz. Soyuz TM-2 Mass: 7,100 kg (15,600 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 341 km (211 mi). Apogee: 365 km (226 mi). Inclination: 51.60 deg. Period: 91.60 min. Crew: Laveykin, Romanenko. Flight: Mir EO-2, Mir LD-1. Mir Expedition EO-02. Docked with Mir 7 February 1987. Carried Yuri Romanenko, Aleksander Laveykin to Mir; returned Laveykin, crew of Soyuz TM-3 to Earth.
1987 March 3 - 11:14 GMT - Launch Vehicle: Soyuz. Progress 28 Mass: 7,246 kg (15,974 lb). Spacecraft: Progress. Agency: MOM. Perigee: 185 km (114 mi). Apogee: 254 km (157 mi). Inclination: 51.60 deg. Period: 88.90 min. Flight: Mir EO-2, Mir LD-1. Unmanned supply vessel to Mir. Orbit of station at time of rendezvous was 344 X 369 km, 51. 62 deg. Docked with Mir on 5 Mar 1987 12:42:36 GMT. Undocked on 26 Mar 1987 05:06:48 GMT. Destroyed in reentry on 28 Mar 1987 03:49:00 GMT. Total free-flight time 4.01 days. Total docked time 20.68 days.
1987 April 9 - 11:44 GMT - Launch Vehicle: Soyuz. Cosmos 1835 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 170 km (100 mi). Apogee: 343 km (213 mi). Inclination: 64.80 deg. Period: 89.60 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.
1987 April 16 - 06:18 GMT - Launch Vehicle: Soyuz. Cosmos 1836 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 236 km (146 mi). Apogee: 289 km (179 mi). Inclination: 64.80 deg. Period: 89.80 min. Photo/digital surveillance.
1987 April 21 - 15:14 GMT - Launch Vehicle: Soyuz. Progress 29 Mass: 7,100 kg (15,600 lb). Spacecraft: Progress. Agency: MOM. Perigee: 189 km (117 mi). Apogee: 237 km (147 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Mir EO-2, Mir LD-1. Unmanned supply vessel to Mir. Deorbited May 11, 1987. Docked with Mir at 343 X 363 1705 23 April at rear port of Kvant. Undocked May 11 03:10. Deorbited28 May 02:59 .
Officially: Transporting sundry cargoes to the Mir orbital station. Docked with Salyut 7 on 23 Apr 1987 17:04:51 GMT. Undocked on 11 May 1987 03:10:01 GMT. Destroyed in reentry on 11 May 1987 08:28:00 GMT. Total free-flight time 2.30 days. Total docked time 17.42 days.
1987 May 5 - 09:15 GMT - Launch Vehicle: Soyuz. Cosmos 1843 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 285 km (177 mi). Inclination: 70.40 deg. Period: 89.40 min. Military cartographic satellite; returned film capsule.
1987 May 13 - 06:00 GMT - Launch Vehicle: Soyuz. Cosmos 1845 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 373 km (231 mi). Inclination: 70.40 deg. Period: 90.30 min. Military cartographic satellite; returned film capsule.
1987 May 19 - 04:02 GMT - Launch Vehicle: Soyuz. Progress 30 Mass: 7,249 kg (15,981 lb). Spacecraft: Progress. Agency: MOM. Perigee: 341 km (211 mi). Apogee: 365 km (226 mi). Inclination: 51.60 deg. Period: 91.60 min. Flight: Mir EO-2, Mir LD-1. Unmanned supply vessel to Mir. Rendezvoused with Mir/Kvant in its orbit of 343 X 366 km, 51. 6 deg. Docked with the station on 21 May 1987 05:50:38 GMT. Undocked on 19 Jul 1987 00:19:51 GMT. Destroyed in reentry on 19 Jul 1987 05:42:00 GMT. Total free-flight time 2.30 days. Total docked time 58.77 days.
1987 July 8 - 10:59 GMT - Launch Vehicle: Soyuz. Cosmos 1865 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 192 km (119 mi). Apogee: 297 km (184 mi). Inclination: 64.80 deg. Period: 89.40 min. Military topographic / cartographic satellite.
1987 July 22 - 01:59 GMT - Launch Vehicle: Soyuz. Soyuz TM-3 Mass: 7,100 kg (15,600 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 297 km (184 mi). Apogee: 353 km (219 mi). Inclination: 51.60 deg. Period: 91.00 min. Crew: Aleksandrov, Faris, Viktorenko. Flight: Soyuz TM-3, Mir EP-1, Mir EO-2, Mir LD-1. Manned three crew. Transported to the Mir orbital space station a Soviet-Syrian crew comprising cosmonauts A S Viktorenko, A P Aleksandrov and M A Faris to conduct joint research and experiments with cosmonauts Y Romanenko and A Laveykin. Maneuvered from initial 231 X 217 km orbit to Mir's 311 X 359 km orbit. Docked with rear Mir port at 3:30 GMT 24 July. Undocked with rear port 30 July and docked to forward port.
1987 August 3 - 20:44 GMT - Launch Vehicle: Soyuz. Progress 31 Mass: 7,212 kg (15,899 lb). Spacecraft: Progress. Agency: MOM. Perigee: 187 km (116 mi). Apogee: 250 km (150 mi). Inclination: 51.60 deg. Period: 88.90 min. Flight: Soyuz TM-3, Mir LD-1. Unmanned resupply vessel to Mir. Rendezvous transfer orbits 187 X 250 km, 51. 64 deg; 266 X 314 km; 309 X 360 km. Docked with Mir on 5 Aug 1987 22:27:35 GMT. Refueled Mir propellants tanks on 15/16 Sept. Undocked on 21 Sep 1987 23:57:41 GMT. Destroyed in reentry on 23 Sep 1987 01:02:00 GMT. Total free-flight time 3.12 days. Total docked time 47.06 days.
1987 September 11 - 02:06 GMT - Launch Vehicle: Soyuz. Cosmos 1881 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 228 km (141 mi). Apogee: 294 km (182 mi). Inclination: 64.70 deg. Period: 89.70 min. Photo/digital surveillance.
1987 September 23 - 23:43 GMT - Launch Vehicle: Soyuz. Progress 32 Mass: 7,035 kg (15,509 lb). Spacecraft: Progress. Agency: MOM. Perigee: 295 km (183 mi). Apogee: 355 km (220 mi). Inclination: 51.60 deg. Period: 91.00 min. Flight: Soyuz TM-3, Mir LD-1. Unmanned resupply vessel to Mir. Delivered 850 kg propellants, 315 kg food, 2,000 kg total. Docked with Mir on 26 Sep 1987 01:08:15 GMT. Undocked on 10 Nov 1987 04:09:10 GMT. Redocked from 2,500 m on 10 Nov 1987 05:47 GMT. Undocked again 17 Nov 1998 19:25 GMT. Destroyed in reentry on 19 Nov 1987 00:58:00 GMT. Total free-flight time 3.17 days. Total docked time 52.82 days.
1987 October 9 - 08:30 GMT - Launch Vehicle: Soyuz. Cosmos 1889 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 371 km (230 mi). Inclination: 70.00 deg. Period: 90.30 min. Military cartographic satellite; returned film capsule.
1987 November 11 - 09:04 GMT - Launch Vehicle: Soyuz. Cosmos 1895 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 224 km (139 mi). Apogee: 283 km (175 mi). Inclination: 70.40 deg. Period: 89.60 min. Military cartographic satellite; returned film capsule.
1987 November 14 - 09:29 GMT - Launch Vehicle: Soyuz. Cosmos 1896 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 263 km (163 mi). Inclination: 64.80 deg. Period: 89.20 min. Military topographic / cartographic satellite.
1987 November 20 - 23:47 GMT - Launch Vehicle: Soyuz. Progress 33 Mass: 6,895 kg (15,200 lb). Spacecraft: Progress. Agency: MOM. Perigee: 326 km (202 mi). Apogee: 343 km (213 mi). Inclination: 51.60 deg. Period: 91.20 min. Flight: Soyuz TM-3, Mir LD-1. Unmanned resupply vessel to Mir. Space station orbit at rendezvous was 326 km x 343 km. Docked on 23 Nov 1987 01:39:13 GMT. Undocked on 19 Dec 1987 08:15:46 GMT. Destroyed in reentry on 19 Dec 1987 13:37:00 GMT. Total free-flight time 2.30 days. Total docked time 26.28 days.
1987 December 7 - 08:50 GMT - Launch Vehicle: Soyuz. Cosmos 1899 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 225 km (139 mi). Apogee: 277 km (172 mi). Inclination: 70.40 deg. Period: 89.50 min. Military cartographic satellite; returned film capsule.
1987 December 14 - 11:29 GMT - Launch Vehicle: Soyuz. Cosmos 1901 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 172 km (106 mi). Apogee: 343 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.
1987 December 21 - 11:18 GMT - Launch Vehicle: Soyuz. Soyuz TM-4 Mass: 7,070 kg (15,580 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 337 km (209 mi). Apogee: 357 km (221 mi). Inclination: 51.60 deg. Period: 91.50 min. Crew: Levchenko, Manarov, Titov Vladimir. Flight: Mir EO-3, Mir LII-1, Soyuz TM-3, Mir LD-1. Mir Expedition EO-03. Carried Musa Manarov, Anatoly Levchenko, Vladimir Titov to Mir; returned crew of Soyuz TM-5 to Earth. Orbits 168 x 243 km, 255 x 296 km, 333 x 359 km. Docked with Mir 12:51 GMT 23 December. 30 December moved to forward port.
1987 December 25 - 08:45 GMT - Launch Vehicle: Soyuz. Cosmos 1905 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 226 km (140 mi). Apogee: 277 km (172 mi). Inclination: 70.40 deg. Period: 89.50 min. Military cartographic satellite; returned film capsule.
1988 January 20 - 22:51 GMT - Launch Vehicle: Soyuz. Progress 34 Mass: 7,078 kg (15,604 lb). Spacecraft: Progress. Agency: MOM. Perigee: 329 km (204 mi). Apogee: 347 km (215 mi). Inclination: 51.60 deg. Period: 91.30 min. Flight: Mir EO-3. Unmanned resupply vessel to Mir. Docked on 23 Jan 1988 00:09:09 GMT. Undocked on 4 Mar 1988 03:40:09 GMT. Destroyed in reentry on 4 Mar 1988 07:29:30 GMT. Total free-flight time 2.21 days. Total docked time 41.15 days.
1988 February 3 - 12:15 GMT - Launch Vehicle: Soyuz. Cosmos 1916 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 168 km (104 mi). Apogee: 352 km (218 mi). Inclination: 64.90 deg. Period: 89.70 min. High resolution photo reconnaissance. Spacecraft failed. Blown up in orbit on February 27.
1988 February 19 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 1921 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 202 km (125 mi). Apogee: 375 km (233 mi). Inclination: 70.00 deg. Period: 90.30 min. Military cartographic satellite; returned film capsule.
1988 March 11 - 06:38 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-ML Molniya 1-71 Mass: 1,800 kg (3,900 lb). Spacecraft: Molniya-1T. Agency: MOM. Perigee: 1,199 km (745 mi). Apogee: 39,149 km (24,326 mi). Inclination: 63.80 deg. Period: 717.70 min. Operation of the long-range telephone and telegraph radio communications system in the USSR; transmission of USSR Central Television programmes to stations in the Orbita network.
1988 March 23 - 21:05 GMT - Launch Vehicle: Soyuz. Progress 35 Mass: 7,037 kg (15,513 lb). Spacecraft: Progress. Agency: MOM. Perigee: 185 km (114 mi). Apogee: 262 km (162 mi). Inclination: 51.60 deg. Period: 89.00 min. Flight: Mir EO-3. Unmanned resupply vessel to Mir. Docked on 25 Mar 1988 22:21:35 GMT. Undocked on 5 May 1988 01:36:03 GMT. Destroyed in reentry on 5 May 1988 06:56:19 GMT. Total free-flight time 2.28 days. Total docked time 40.14 days.
1988 March 30 - 12:00 GMT - Launch Vehicle: Soyuz. Cosmos 1936 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 182 km (113 mi). Apogee: 266 km (165 mi). Inclination: 64.80 deg. Period: 89.00 min. Photo/digital surveillance.
1988 April 27 - 09:10 GMT - Launch Vehicle: Soyuz. Cosmos 1941 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 266 km (165 mi). Inclination: 70.30 deg. Period: 89.20 min. Military cartographic satellite; returned film capsule.
1988 May 13 - 00:30 GMT - Launch Vehicle: Soyuz. Progress 36 Mass: 7,077 kg (15,602 lb). Spacecraft: Progress. Agency: MOM. Perigee: 185 km (114 mi). Apogee: 246 km (152 mi). Inclination: 51.70 deg. Period: 88.80 min. Flight: Mir EO-3. Unmanned resupply vessel to Mir. Rendezvous transfer orbits 185x246 km, 51. 66 deg; 223x334 km; 331x357 km. Docked with Mir on 15 May 1988 02:13:26 GMT. Undocked on 5 Jun 1988 11:11:55 GMT. Destroyed in reentry on 5 Jun 1988 21:18:40 GMT. Total free-flight time 2.49 days. Total docked time 21.37 days.
1988 May 18 - 10:30 GMT - Launch Vehicle: Soyuz. Cosmos 1944 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 196 km (121 mi). Apogee: 288 km (178 mi). Inclination: 64.80 deg. Period: 89.30 min. Military topographic / cartographic satellite.
1988 May 19 - 09:15 GMT - Launch Vehicle: Soyuz. Cosmos 1945 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 364 km (226 mi). Inclination: 70.40 deg. Period: 90.20 min. Military cartographic satellite; returned film capsule.
1988 June 7 - 14:03 GMT - Launch Vehicle: Soyuz. Soyuz TM-5 Mass: 7,000 kg (15,400 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 196 km (121 mi). Apogee: 216 km (134 mi). Inclination: 51.60 deg. Period: 88.60 min. Crew: Aleksandrov Aleksandr, Savinykh, Solovyov. Flight: Mir EP-2, Mir EO-3. Transported to the Mir orbital station a Soviet/Bulgarian crew comprising cosmonauts A Y Solovyev, V P Savinykh and A P Aleksandrov (Bulgaria) to conduct joint research and experiments with cosmonauts V G Titov and M K Manarov. Interim orbit 343 x 282 km. Maneuvered to Mir's 355 x 349 km orbit. Docked 15:57 GMT 9 June to Mir's aft port. Moved to forward port 18 June.
1988 June 11 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 1952 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 269 km (167 mi). Inclination: 70.00 deg. Period: 89.20 min. Military cartographic satellite; returned film capsule.
1988 June 22 - 13:00 GMT - Launch Vehicle: Soyuz. Cosmos 1955 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 171 km (106 mi). Apogee: 357 km (221 mi). Inclination: 64.80 deg. Period: 89.80 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.
1988 July 9 - Launch Vehicle: Soyuz. FAILURE: Failure. Yantar-4KS1 Spacecraft: Yantar-4KS1. Agency: UNKS.
1988 July 18 - 21:13 GMT - Launch Vehicle: Soyuz. Progress 37 Mass: 7,065 kg (15,575 lb). Spacecraft: Progress. Agency: MOM. Perigee: 189 km (117 mi). Apogee: 256 km (159 mi). Inclination: 51.60 deg. Period: 89.00 min. Flight: Mir EO-3. Unmanned resupply vessel to Mir. Rendezvous transfer orbits 187x256 km, 51. 62 deg; 235 x 319 km; 343 x 347 km. Docked with Mir on 20 Jul 1988 22:33:40 GMT. Refuelling operations on 7,8, and 9 August 1998. Undocked on 12 Aug 1988 08:31:54 GMT. Destroyed in reentry on 12 Aug 1988 13:45:40 GMT. Total free-flight time 2.27 days. Total docked time 22.42 days.
1988 August 8 - 09:25 GMT - Launch Vehicle: Soyuz. Cosmos 1962 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 265 km (164 mi). Inclination: 70.00 deg. Period: 89.20 min. Military cartographic satellite; returned film capsule.
1988 August 16 - 13:00 GMT - Launch Vehicle: Soyuz. Cosmos 1963 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 176 km (109 mi). Apogee: 350 km (210 mi). Inclination: 64.80 deg. Period: 89.80 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.
1988 August 23 - 09:20 GMT - Launch Vehicle: Soyuz. Cosmos 1964 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 206 km (128 mi). Apogee: 271 km (168 mi). Inclination: 70.00 deg. Period: 89.30 min. Military cartographic satellite; returned film capsule.
1988 August 29 - 04:23 GMT - Launch Vehicle: Soyuz. Soyuz TM-6 Mass: 7,070 kg (15,580 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 195 km (121 mi). Apogee: 228 km (141 mi). Inclination: 51.60 deg. Period: 88.70 min. Crew: Lyakhov, Mohmand, Polyakov. Flight: Mir EP-3, Mir LD-2, Mir EO-3. Transported to the Mir orbital station a Soviet-Afghan crew comprising the cosmonauts V A Lyakhov, V V Polyakov and A A Momand (Afghanistan) to conduct joint research and experiments with the cosmonauts V G Titov and M K Manarov. Returned Manarov, Titov (Soyuz TM-4), Chretien (Soyuz TM-7) to Earth. Initial orbit 195 X 228 km at 51. 57 deg. Maneuvered to a 235 x 259 km orbit, then docked with Mir at 05:41 GMT on 31 August at its 339 x 366 km orbit. Moved from aft to forward port 8 Sept 88.
1988 September 9 - 23:33 GMT - Launch Vehicle: Soyuz. Progress 38 Mass: 7,027 kg (15,491 lb). Spacecraft: Progress. Agency: MOM. Perigee: 187 km (116 mi). Apogee: 248 km (154 mi). Inclination: 51.60 deg. Period: 88.90 min. Flight: Mir LD-2, Mir EO-3. Unmanned resupply vessel to Mir. During launch first test of Buran ejection seat was made during ascent to orbit. The K-36M.11F35 seat was installed in an 'experimental droppable compartment' installed in place of the Launch Escape Tower engine on top of the shroud. Rendezvous orbits 186 X 246 km, 51. 63 deg; 234 X 332 km, 337 X 363 km. Docked with Mir on 12 Sep 1988 01:22:28 GMT. Delivered 2,000 kg supplies including 300 kg of food. Refuelled Mir. Undocked on 23 Nov 1988 12:12:46 GMT. Destroyed in reentry on 23 Nov 1988 19:06:58 GMT. Total free-flight time 2.36 days. Total docked time 72.45 days.
1988 November 11 - Launch Vehicle: Soyuz. FAILURE: Failure. Yantar-4KS1 Spacecraft: Yantar-4KS1. Agency: UNKS.
1988 November 26 - 15:49 GMT - Launch Vehicle: Soyuz. Soyuz TM-7 Mass: 7,000 kg (15,400 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 194 km (120 mi). Apogee: 235 km (146 mi). Inclination: 51.60 deg. Period: 88.80 min. Crew: Chretien, Krikalyov, Volkov Aleksandr. Flight: Mir EO-4, Mir Aragatz, Mir LD-2, Mir EO-3. Mir Expedition EO-04. Carried Alexander Volkov, Sergei Krikalev, Jean-Loup Chretien to Mir; returned Volkov, Krikalev to Earth. Initial Orbit: 194 X 235 km. Thereafter maneuvered to rendezvous orbit 256 X 291 km before docking with Mir in 337 X 369 km at 17:16 GMT 28 November.
1988 November 30 - 09:00 GMT - Launch Vehicle: Soyuz. Cosmos 1982 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 377 km (234 mi). Inclination: 70.00 deg. Period: 90.30 min. Military cartographic satellite; returned film capsule.
1988 December 25 - 04:11 GMT - Launch Vehicle: Soyuz. Progress 39 Mass: 7,015 kg (15,465 lb). Spacecraft: Progress. Agency: MOM. Perigee: 187 km (116 mi). Apogee: 238 km (147 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Mir EO-4, Mir LD-2. Unmanned resupply vessel to Mir. Made second test of Buran ejection seat during ascent to orbit. The K-36M.11F35 seat was installed in an 'experimental droppable compartment' installed in place of the Launch Escape Tower engine on top of the shroud. Rendezvous orbits 187 X 237 km, 51.63 deg; 236 X 338 km; 325 X 353 km at Mir. Delivered 1,300 kg cargo. Docked with Mir on 27 Dec 1988 05:35:10 GMT. Undocked on 7 Feb 1989 06:45:34 GMT. Destroyed in reentry on 7 Feb 1989 13:49:00 GMT. Total free-flight time 2.35 days. Total docked time 42.05 days.
1988 December 29 - 10:00 GMT - Launch Vehicle: Soyuz. Cosmos 1986 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 193 km (119 mi). Apogee: 289 km (179 mi). Inclination: 64.80 deg. Period: 89.30 min. Topographic mapping for the Army General Staff.
1989 January 18 - 08:20 GMT - Launch Vehicle: Soyuz. Cosmos 1991 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 375 km (233 mi). Inclination: 70.00 deg. Period: 90.30 min. Military cartographic satellite; returned film capsule.
1989 January 28 - 12:30 GMT - Launch Vehicle: Soyuz. Cosmos 1993 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 171 km (106 mi). Apogee: 347 km (215 mi). Inclination: 64.80 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.
1989 February 10 - 08:53 GMT - Launch Vehicle: Soyuz. Progress 40 Mass: 7,022 kg (15,480 lb). Spacecraft: Progress. Agency: MOM. Perigee: 187 km (116 mi). Apogee: 244 km (151 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Mir EO-4, Mir LD-2. Unmanned resupply vessel to Mir. Conducted third test of Buran ejection seat during ascent to orbit. The K-36M.11F35 seat was installed in an 'experimental droppable compartment' installed in place of the Launch Escape Tower engine on top of the shroud. Docked with Mir on 12 Feb 1989 10:29:38 GMT. Undocked on 3 Mar 1989 01:45:52 GMT. Unfurled experimental space mirror petal structure on undocking. Destroyed in reentry on 5 Mar 1989 01:59:00 GMT. Total free-flight time 4.08 days. Total docked time 18.64 days.
1989 February 15 - 11:00 GMT - Launch Vehicle: Soyuz. Molniya 8K78M-ML Molniya 1-75 Mass: 1,800 kg (3,900 lb). Spacecraft: Molniya-1T. Agency: MOM. Perigee: 2,111 km (1,311 mi). Apogee: 38,249 km (23,766 mi). Inclination: 63.50 deg. Period: 717.90 min. Operation of the long-range telephone and telegraph radio communications system in the USSR; transmission of USSR Central Television programmes to stations in the Orbita network and within the framework of international cooperation.
1989 March 16 - 18:54 GMT - Launch Vehicle: Soyuz. Progress 41 Mass: 6,995 kg (15,421 lb). Spacecraft: Progress. Agency: MOM. Perigee: 187 km (116 mi). Apogee: 243 km (150 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Mir EO-4, Mir LD-2. Unmanned resupply vessel to Mir. Conducted fourth test of Buran ejection seat during ascent to orbit. The K-36M.11F35 seat was installed in an 'experimental droppable compartment' installed in place of the Launch Escape Tower engine on top of the shroud. Delivered Bulgarian Spektr 256 spectrometer, power supplies for failed equipment. Docked with Mir on 18 Mar 1989 20:50:46 GMT. Between April 9 and 17 boosted Mir into a 373 X 416 km storage orbit after the decision was made to delay remanning the station. However these maneuvers resulted in the spacecraft running out of fuel. Undocked on 21 Apr 1989 01:46:15 GMT. Destroyed in uncontrolled decay of orbit on 25 Apr 1989 12:12:00 GMT. Total free-flight time 6.52 days. Total docked time 33.21 days.
1989 March 23 - 12:25 GMT - Launch Vehicle: Soyuz. Cosmos 2007 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 224 km (139 mi). Apogee: 262 km (162 mi). Inclination: 64.70 deg. Period: 89.40 min. Photo/digital surveillance.
1989 May 17 - 13:00 GMT - Launch Vehicle: Soyuz. Cosmos 2020 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4K1. Agency: MOM. Perigee: 178 km (110 mi). Apogee: 280 km (170 mi). Inclination: 64.80 deg. Period: 89.10 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.
1989 May 24 - 10:30 GMT - Launch Vehicle: Soyuz. Cosmos 2021 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 280 km (170 mi). Inclination: 69.90 deg. Period: 89.40 min. Topographic mapping for the Army General Staff.
1989 June 16 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 2028 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 204 km (126 mi). Apogee: 243 km (150 mi). Inclination: 70.00 deg. Period: 89.00 min. Military cartographic satellite; returned film capsule.
1989 July 18 - 12:10 GMT - Launch Vehicle: Soyuz. Cosmos 2031 Mass: 6,500 kg (14,300 lb). Spacecraft: Orlets-1. Agency: MOM. Perigee: 211 km (131 mi). Apogee: 264 km (164 mi). Inclination: 50.40 deg. Period: 89.30 min. First launch of Orlets-1 long duration film return military reconnaissance satellite. After returning multiple film capsules, the spacecraft was deorbited.
1989 August 23 - 03:09 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 T15000-037 Progress M-1 Mass: 7,270 kg (16,020 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 187 km (116 mi). Apogee: 217 km (134 mi). Inclination: 51.60 deg. Period: 88.50 min. Flight: Mir EO-5. Unmanned supply vehicle to Mir; first flight of new vehicle design. Tested on-board systems under different conditions and delivered expendable materials and sundry cargo to the Mir manned space station. Docked with Mir on 25 Aug 1989 05:19:02 GMT. Undocked on 1 Dec 1989 09:02:23 GMT. Destroyed in reentry on 1 Dec 1989 11:21:00 GMT. Total free-flight time 2.19 days. Total docked time 98.16 days.
1989 September 5 - 21:38 GMT - Launch Vehicle: Soyuz. Soyuz TM-8 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 390 km (240 mi). Apogee: 392 km (243 mi). Inclination: 51.60 deg. Period: 92.40 min. Crew: Serebrov, Viktorenko. Flight: Mir EO-5. Manned two crew. Mir Expedition EO-05. Docked with Mir 8 September. Transported to the Mir orbital station a team consisting of A S Viktorenko, commander of the spacecraft, and A A Serebrov, on-board engineer, to carry out scientific and technological research and experiments. Flight cost 80 million rubles. Expected return 25 million rubles net profit.
1989 September 22 - 08:00 GMT - Launch Vehicle: Soyuz. Cosmos 2045 Mass: 6,300 kg (13,800 lb). Spacecraft: Zenit-8. Agency: MOM. Perigee: 205 km (127 mi). Apogee: 295 km (183 mi). Inclination: 70.00 deg. Period: 89.50 min. Military cartographic satellite; returned film capsule.
1989 November 17 - 10:50 GMT - Launch Vehicle: Soyuz. Cosmos 2049 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 232 km (144 mi). Apogee: 251 km (155 mi). Inclination: 64.80 deg. Period: 89.30 min. Photo/digital surveillance.
1989 December 20 - 03:30 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 T15000-039? Progress M-2 Mass: 7,300 kg (16,000 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 390 km (240 mi). Apogee: 392 km (243 mi). Inclination: 51.60 deg. Period: 92.40 min. Flight: Mir EO-5. Unmanned resupply vessel to Mir; carried US microgravity payload. Delivered various cargoes to the Mir orbital station, including scientific apparatus produced in the United States of America and intended, pursuant to a commercial agreement, for the conduct of experiments on space biotechnology. Docked with Mir on 22 Dec 1989 05:41:21 GMT. Undocked on 9 Feb 1990 02:33:07 GMT. Destroyed in reentry on 9 Feb 1990 07:56:00 GMT. Total free-flight time 2.31 days. Total docked time 48.87 days.
1990 February 11 - 06:16 GMT - Launch Vehicle: Soyuz. Soyuz TM-9 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 373 km (231 mi). Apogee: 387 km (240 mi). Inclination: 51.60 deg. Period: 92.20 min. Crew: Balandin, Solovyov. Flight: Mir EO-5, Mir EO-6. Manned two crew. Mir Expedition EO-06. Docked with Mir. Transported to the Mir orbital station a crew comprising the cosmonauts A Y Solovyov and A N Balandin to conduct an extensive programme of geophysical and astrophysical research, experiments on biology and biotechnology and work on space materials science.
1990 February 28 - 23:10 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 T15000-040 Progress M-3 Mass: 7,249 kg (15,981 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 183 km (113 mi). Apogee: 218 km (135 mi). Inclination: 51.60 deg. Period: 88.50 min. Flight: Mir EO-6. Unmanned resupply vessel to Mir. Docked with Mir on 3 Mar 1990 01:04:32 GMT. Undocked on 27 Apr 1990 20:24:43 GMT. Destroyed in reentry on 28 Apr 1990 00:52:00 GMT. Total free-flight time 2.26 days. Total docked time 55.81 days.
1990 April 13 - 18:53 GMT - Launch Vehicle: Soyuz. Cosmos 2072 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 232 km (144 mi). Apogee: 270 km (160 mi). Inclination: 64.70 deg. Period: 89.50 min. Photo/digital surveillance.
1990 May 5 - 20:44 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 T15000-041 Progress 42 Mass: 7,011 kg (15,456 lb). Spacecraft: Progress. Agency: MOM. Perigee: 188 km (116 mi). Apogee: 243 km (150 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Mir EO-6. Unmanned resupply vessel to Mir; last of original design Progress spacecraft. Conducted fifth and final test of Buran ejection seat during ascent to orbit. The K-36M.11F35 seat was installed in an 'experimental droppable compartment' installed in place of the Launch Escape Tower engine on top of the shroud. Docked with Mir on 7 May 1990 22:45:03 GMT. Undocked on 27 May 1990 07:08:58 GMT. Destroyed in reentry on 27 May 1990 12:27:30 GMT. Total free-flight time 2.31 days. Total docked time 19.35 days.
1990 May 15 - 09:55 GMT - Launch Vehicle: Soyuz. Cosmos 2078 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 196 km (121 mi). Apogee: 280 km (170 mi). Inclination: 70.00 deg. Period: 89.30 min. Topographic mapping for the Army General Staff.
1990 July 11 - 10:00 GMT - Launch Vehicle: Soyuz. Gamma Mass: 7,350 kg (16,200 lb). Spacecraft: Gamma. Agency: MOM. Perigee: 382 km (237 mi). Apogee: 387 km (240 mi). Inclination: 51.60 deg. Period: 92.30 min. Spacecraft mission was research in the field of high-energy (gamma/x-ray) astrophysics conducted jointly with France and Poland. The satellite was based on the Soyuz manned spacecraft and had an extremely long gestation - conceived in 1965, authorised in 1976, scheduled originally for launch in 1984, but further severe technical delays resulted in a 1990 launch.
1990 August 1 - 09:32 GMT - Launch Vehicle: Soyuz. Soyuz TM-10 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 198 km (123 mi). Apogee: 219 km (136 mi). Inclination: 51.60 deg. Period: 88.70 min. Crew: Manakov, Strekalov. Flight: Mir EO-7, Mir EO-6. Manned two crew. Docked with Mir. Mir Expedition EO-07. Transported to the Mir manned orbital station the crew consisting of the cosmonauts G M Manakov and G M Strekalov for the purpose of carrying out a programme of geophysical and astrophysical research, biological and biotechnological experiments, and work on space-materials science.
1990 August 15 - 04:00 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 T15000-042 Progress M-4 Mass: 7,294 kg (16,080 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 184 km (114 mi). Apogee: 219 km (136 mi). Inclination: 51.60 deg. Period: 88.50 min. Flight: Mir EO-7. Unmanned resupply vessel to Mir. Delivered cables for rewiring operations and equipment for Soyuz TM-11 Japanese journalist flight. Docked with Mir on 17 Aug 1990 05:26:13 GMT. Undocked on 17 Sep 1990 12:42:43 GMT. Destroyed in reentry on 20 Sep 1990 11:42:49 GMT. Total free-flight time 5.02 days. Total docked time 31.30 days.
1990 September 27 - 10:37 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 T15000-044 Progress M-5 Mass: 7,320 kg (16,130 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 186 km (115 mi). Apogee: 229 km (142 mi). Inclination: 51.60 deg. Period: 88.70 min. Flight: Mir EO-7. Unmanned resupply vessel to Mir. Included first Progress recoverable capsule for return of 150 kg of payload to earth. Docked with Mir on 29 Sep 1990 12:26:50 GMT. Undocked on 28 Nov 1990 06:15:46 GMT. After deorbit burn, capsule separated for reentry with an expected landing in Kazakhstan at 28 Nov 1990 11:04:05 GMT. However the recoverable capsule's beacon signal was never received after reentry. All experimental data and materials in capsule lost. Total free-flight time 2.28 days. Total docked time 59.74 days.
1990 October 1 - 11:00 GMT - Launch Vehicle: Soyuz. Cosmos 2101 Mass: 6,700 kg (14,700 lb). Spacecraft: Orlets-1. Agency: MOM. Perigee: 162 km (100 mi). Apogee: 304 km (188 mi). Inclination: 64.80 deg. Period: 89.20 min. Long duration film return military reconnaissance satellite. After returning multiple film capsules, the spacecraft was deorbited.
1990 December 2 - 08:13 GMT - Launch Vehicle: Soyuz. Soyuz TM-11 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 367 km (228 mi). Apogee: 400 km (240 mi). Inclination: 51.60 deg. Period: 92.20 min. Crew: Afanasyev, Akiyama, Manarov. Flight: Mir EO-8, Mir Kosmoreporter, Mir EO-7. Docked with Mir. Mir Expedition EO-08. Transported to the Mir manned orbital station the international crew consisting of the cosmonauts V M Afanasyev, M Kh Manarov, and T Akiyami (Japan) for the purpose of carrying out joint work with the cosmonauts G M Manakov and G M Strekalov. Launched jointly with the private Japanese company TBS. The Japanese television network ended up paying $ 28 million for the first commercial flight to Mir to put Akiyama, the first journalist in space aboard Soyuz TM-11. Akiyama made daily television broadcasts.
1990 December 21 - 06:20 GMT - Launch Vehicle: Soyuz. Cosmos 2113 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 225 km (139 mi). Apogee: 261 km (162 mi). Inclination: 64.80 deg. Period: 89.40 min. Photo/digital surveillance.
1991 January 14 - 14:50 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 T15000-045 Progress M-6 Mass: 7,125 kg (15,707 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 188 km (116 mi). Apogee: 205 km (127 mi). Inclination: 51.60 deg. Period: 88.40 min. Flight: Mir EO-8. Unmanned resupply vessel to Mir. Delivered new life support equipment to replace life-expired equipment aboard. Docked with Mir on 16 Jan 1991 16:35:25 GMT. Undocked on 15 Mar 1991 12:46:41 GMT. Destroyed in reentry on 15 Mar 1991 18:07:26 GMT. Total free-flight time 2.30 days. Total docked time 57.84 days.
1991 February 15 - 09:30 GMT - Launch Vehicle: Soyuz. Cosmos 2134 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 190 km (110 mi). Apogee: 306 km (190 mi). Inclination: 64.70 deg. Period: 89.50 min. Topographic mapping for the Army General Staff.
1991 March 19 - 13:05 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 R15000-049 Progress M-7 Mass: 7,307 kg (16,109 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 186 km (115 mi). Apogee: 213 km (132 mi). Inclination: 51.60 deg. Period: 88.50 min. Flight: Mir EO-8. Unmanned resupply vessel to Mir. Attempted to dock with Mir on 21 March 1998 14:28 GMT, but missed the station by 500 m. Docking attempted again on 23 March but at 50 meters the docking was aborted; the Progress missed hitting the station by five meters. Thereafter it was placed in a station-keeping co-orbit with Mir while the problem was diagnosed. Finally docked with Mir on 28 Mar 1991 12:02:28 GMT. On 12 and 14 Apr 1998 two burns of the engine of Progress M-7 raised the station's orbit from a 360 x 377 km orbit to a 370 x 382 km orbit. Undocked on 6 May 1991 22:59:36 GMT. Destroyed in reentry on 7 May 1991 17:20:05 GMT. Total free-flight time 9.72 days. Total docked time 39.46 days.
1991 May 18 - 12:50 GMT - Launch Vehicle: Soyuz. Soyuz TM-12 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 389 km (241 mi). Apogee: 397 km (246 mi). Inclination: 51.60 deg. Period: 92.40 min. Crew: Artsebarsky, Krikalyov, Sharman. Flight: Mir EO-9, Mir LD-3, Mir Juno, Mir EO-8. Docked with Mir. Mir Expedition EO-09. Carried Anatoli Artsebarski, Sergei Krikalev, Helen Sharman to Mir; returned Artsebarski, crew of Soyuz TM 8 to Earth. Second commercial flight with paying British passenger. Sponsoring British consortium was not quite able to come up with money, however. Flight continued at Soviet expense with very limited UK experiments.
1991 May 30 - 08:04 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 R15000-050 Progress M-8 Mass: 7,296 kg (16,084 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 390 km (240 mi). Apogee: 396 km (246 mi). Inclination: 51.60 deg. Period: 92.40 min. Flight: Mir EO-9, Mir LD-3. Unmanned resupply vessel to Mir. Docked with Mir on 1 Jun 1991 09:44:37 GMT. Undocked on 15 Aug 1991 22:16:59 GMT. Destroyed in reentry on 16 Aug 1991 06:56:32 GMT. Total free-flight time 2.43 days. Total docked time 75.52 days.
1991 August 20 - 22:54 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 G15000-047 Progress M-9 Mass: 7,311 kg (16,117 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 186 km (115 mi). Apogee: 230 km (140 mi). Inclination: 51.60 deg. Period: 88.70 min. Flight: Mir EO-9, Mir LD-3. Unmanned resupply vessel to Mir; carried reentry capsule for return of 150 kg of experiment results. Docked with Mir on 23 Aug 1991 00:54:17 GMT. Undocked on 30 Sep 1991 01:53:00 GMT. 350 kg return capsule detached from the Propess' orbital module at an altitude of 110 to 130 km. The capsule underwent a ballistic descent to 15 km, followed by a parachute descent from there to surface. The capsule's beacon began transmitting at 4.5 km. Landed in Kazakhstan on 30 Sep 1991 08:16:24 GMT. Total free-flight time 2.35 days. Total docked time 38.04 days.
1991 October 2 - 05:59 GMT - Launch Vehicle: Soyuz. Soyuz TM-13 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 195 km (121 mi). Apogee: 232 km (144 mi). Inclination: 51.70 deg. Period: 88.80 min. Crew: Aubakirov, Viehboeck, Volkov Aleksandr. Flight: Mir EO-10, Mir Austromir, Mir EO-9, Mir LD-3. Manned three crew. Docked with Mir. Mir Expedition EO-10. Transported to the Mir manned orbital station an international crew comprising the cosmonauts A Volkov (USSR), T Aubakirov (USSR) and F. Viehbock (Austria), to conduct joint scientific and technical research with the cosmonauts A. Artsebarsky and S Krikalev. Austria paid $ 7 million for mission. Kazakh cosmonaut added at last minute.
1991 October 9 - 13:15 GMT - Launch Vehicle: Soyuz. Cosmos 2163 Mass: 6,500 kg (14,300 lb). Spacecraft: Orlets-1. Agency: MOM. Perigee: 169 km (105 mi). Apogee: 308 km (191 mi). Inclination: 64.80 deg. Period: 89.30 min. Long duration film return military reconnaissance satellite. After returning multiple film capsules, the spacecraft was deorbited.
1991 October 17 - 00:05 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 15000-055 Progress M-10 Mass: 7,306 kg (16,106 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 185 km (114 mi). Apogee: 217 km (134 mi). Inclination: 51.70 deg. Period: 88.50 min. Flight: Mir EO-10, Mir LD-3. Unmanned resupply vessel to Mir. First attempted to dock with Mir on 19 October 1991. The docking was automatically aborted at a distance of 150 m from the station. Successfully docked with the forward port of Mir on on 21 Oct 1991 03:40:50 GMT. Unloading began next day. Undocked on 20 Jan 1992 07:13:44 GMT. Destroyed in reentry on 20 Jan 1992 12:03:30 GMT. Total free-flight time 4.35 days. Total docked time 91.15 days.
1992 January 25 - 07:50 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 R15000-058 Progress M-11 Mass: 7,320 kg (16,130 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 185 km (114 mi). Apogee: 227 km (141 mi). Inclination: 51.60 deg. Period: 88.60 min. Flight: Mir EO-10, Mir LD-3. Unmanned resupply vessel to Mir. Docked with Mir on 27 Jan 1992 09:30:43 GMT. Undocked on 13 Mar 1992 08:43:40 GMT. Destroyed in reentry on 13 Mar 1992 15:47:00 GMT. Total free-flight time 2.36 days. Total docked time 45.97 days.
1992 March 17 - 10:54 GMT - Launch Vehicle: Soyuz. Soyuz TM-14 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 373 km (231 mi). Apogee: 394 km (244 mi). Inclination: 51.60 deg. Period: 92.20 min. Crew: Flade, Kaleri, Viktorenko. Flight: Mir EO-11, Mir 92, Mir EO-10, Mir LD-3. Mir Expedition EO-11. Joint flight with Germany. Docked at the Kvant rear port at 12:33 GMT on March 19.
1992 April 19 - 21:29 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 R15000-059 Progress M-12 Mass: 7,320 kg (16,130 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 373 km (231 mi). Apogee: 394 km (244 mi). Inclination: 51.60 deg. Period: 92.20 min. Flight: Mir EO-11. Unmanned resupply vessel to Mir. Docked with Mir on 21 Apr 1992 23:21:59 GMT. Undocked on 27 Jun 1992 21:34:44 GMT. Destroyed in reentry on 28 Jun 1992 00:02:51 GMT. Total free-flight time 2.18 days. Total docked time 66.93 days.
1992 April 29 - 10:10 GMT - Launch Vehicle: Soyuz. Cosmos 2185 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-1KFT. Agency: MOM. Perigee: 209 km (129 mi). Apogee: 274 km (170 mi). Inclination: 70.00 deg. Period: 89.30 min. Topographic mapping for the Army General Staff.
1992 July 27 - 06:08 GMT - Launch Vehicle: Soyuz. Soyuz TM-15 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 196 km (121 mi). Apogee: 216 km (134 mi). Inclination: 51.60 deg. Period: 88.60 min. Crew: Avdeyev, Solovyov, Tognini. Flight: Mir EO-12, Mir Antares, Mir EO-11. Mir Expedition EO-12. Russian astronauts Solovyov and Avdeev and French astronaut Tognini were inserted into an initial 190 x 200 km orbit inclined 51.6 deg. Later on July 27 they maneuvered to a 223 x 343 km orbit, and on July 28 docked with Mir in its 405 x 410 km orbit.
1992 December 9 - 11:25 GMT - Launch Vehicle: Soyuz. Cosmos 2223 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 238 km (147 mi). Apogee: 271 km (168 mi). Inclination: 64.60 deg. Period: 89.60 min. Photo/digital surveillance.
1993 January 24 - 05:58 GMT - Launch Vehicle: Soyuz. Soyuz TM-16 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: RKA. Perigee: 393 km (244 mi). Apogee: 394 km (244 mi). Inclination: 51.60 deg. Period: 92.40 min. Crew: Manakov, Polishchuk. Flight: Mir EO-13, Mir EO-12. Manned two crew. Mir Expedition EO-13. Transported to the Mir manned orbital station a crew of the thirteenth main expedition comprising the cosmonauts G M Manakov and A F Poleschuk.The Soyuz carried the APAS androgynous docking system instead of the usual probe system.
1993 February 21 - 18:32 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 U15000-068 Progress M-16 Mass: 7,338 kg (16,177 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 189 km (117 mi). Apogee: 234 km (145 mi). Inclination: 51.70 deg. Period: 88.70 min. Flight: Mir EO-13. Unmanned resupply vessel to Mir. Docked with Mir on 23 Feb 1993 20:17:57 GMT. Undocked on 26 Mar 1993 06:50:00 GMT. Redocked with Mir on 1993-03-26 07:06:03 GMT. Final undocking on 1993-03-27 04:21:00 GMT. Destroyed in reentry on 27 Mar 1993 10:25:00 GMT. Total free-flight time 2.33 days. Total docked time 31.32 days.
1993 March 31 - 03:34 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U2 N15000-069 Progress M-17 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 362 km (224 mi). Apogee: 365 km (226 mi). Inclination: 51.60 deg. Period: 91.80 min. Flight: Mir EO-13. Unmanned resupply vessel to Mir. Conducted docked and undocked longevity spacecraft longevity tests. Docked with Mir on 1 Apr 1993 05:16:18 GMT. Undocked on 11 Aug 1993 15:36:42 GMT. Destroyed in reentry over the South Atlantic on 3 Mar 1994 03:28:00 GMT. Total free-flight time 204.56 days. Total docked time 132.43 days.
1993 May 22 - 06:41 GMT - Launch Vehicle: Soyuz. Progress M-18 Mass: 7,348 kg (16,199 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 188 km (116 mi). Apogee: 240 km (140 mi). Inclination: 51.60 deg. Period: 88.80 min. Flight: Mir EO-13. Unmanned resupply vessel to Mir. Last launch using Soyuz-U2 launch vehicle. Docked with Mir's front port on 24 May 1993 08:24:44 GMT. In addition to other supplies, carried repair equipment for a spacewalk device damaged a month before. Undocked on 3 Jul 1993 15:58:16 GMT, with Soyuz TM-17 docking at the same port only minutes later at 17:45 GMT. Meanwhile, Progress M-17 remained docked to the Kvant rear port on a longevity test. Progress M-18 was destroyed in reentry on 4 Jul 1993 17:13:00 GMT. Total free-flight time 3.12 days. Total docked time 40.31 days.
1993 July 1 - 14:32 GMT - Launch Vehicle: Soyuz. Soyuz TM-17 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 388 km (241 mi). Apogee: 397 km (246 mi). Inclination: 51.60 deg. Period: 92.40 min. Crew: Haignere, Serebrov, Tsibliyev. Flight: Mir EO-14, Mir Altair, Mir EO-13. Mir Expedition EO-14. Carried Vasili Tsibliyev, Alexander Serebrov, Jean-Pierre Haignere to Mir; returned Serebrov, Tsibliyev to Earth. Progress M-18 undocked from Mir's front port at around 17:25 GMT on July 3, and Soyuz TM-17 docked at the same port only 20 minutes later at 17:45 GMT.
1993 August 10 - 22:23 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U N15000-634 Progress M-19 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 179 km (111 mi). Apogee: 223 km (138 mi). Inclination: 51.80 deg. Period: 88.50 min. Flight: Mir EO-14. Unmanned resupply vessel to Mir. Docked with Mir at the Kvant rear port on 13 Aug 1993 00:00:06 GMT. Undocked on 13 Oct 1993 17:59:06 GMT. Destroyed in reentry on 19 Oct 1993 00:22:14 GMT. Total free-flight time 7.33 days. Total docked time 61.75 days.
1993 October 11 - 21:33 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 77044270 Progress M-20 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 187 km (116 mi). Apogee: 226 km (140 mi). Inclination: 51.80 deg. Period: 88.60 min. Flight: Mir EO-14. Unmanned resupply vessel to Mir, carried a Raduga reentry capsule for return of experimental materials to earth. Docked with Mir on 13 Oct 1993 23:24:46 GMT. Undocked on 21 Nov 1993 02:38:43 GMT. Capsule landed in Kazakhstan on 21 Nov 1993 09:06:00 GMT. Total free-flight time 2.35 days. Total docked time 38.13 days.
1993 November 5 - 08:25 GMT - Launch Vehicle: Soyuz. Cosmos 2267 Mass: 6,600 kg (14,500 lb). Spacecraft: Yantar-4KS1. Agency: MOM. Perigee: 228 km (141 mi). Apogee: 281 km (174 mi). Inclination: 70.40 deg. Period: 89.60 min. Photo/digital surveillance.
1994 January 8 - 10:05 GMT - Launch Vehicle: Soyuz. Soyuz TM-18 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 244 km (151 mi). Apogee: 335 km (208 mi). Inclination: 51.60 deg. Period: 90.10 min. Crew: Afanasyev, Polyakov, Usachyov. Flight: Mir EO-15, Mir EO-14, Mir LD-4. Mir Expedition EO-15. Docked at the Kvant module on January 10 at 11:15 GMT. Transported to the Mir orbital station of a crew comprising the cosmonauts V M Afanasev, Y V Usachev, and V V Polyakov for the fifteenth main expedition.
1994 January 28 - 02:12 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U N15000-635 Progress M-21 Mass: 7,130 kg (15,710 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 194 km (120 mi). Apogee: 236 km (146 mi). Inclination: 51.60 deg. Period: 88.50 min. Flight: Mir EO-15, Mir LD-4. Unmanned resupply vessel to Mir. Docked with Mir on 30 Jan 1994 03:56:13 GMT. Undocked on 23 Mar 1994 01:20:29 GMT. Destroyed in reentry on 23 Mar 1994 05:13:00 GMT. Total free-flight time 2.23 days. Total docked time 51.89 days.
1994 March 22 - 04:54 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 76032992 Progress M-22 Mass: 7,103 kg (15,659 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 260 km (160 mi). Apogee: 335 km (208 mi). Inclination: 51.70 deg. Period: 90.20 min. Flight: Mir EO-15, Mir LD-4. Unmanned resupply vessel to Mir. Launched into an initial 192 x 238 x 51.6 km orbit. Docked with Mir on 24 Mar 1994 06:39:37 GMT. Fired its engine around 15 May to raise the orbit of the Mir station from 381 x 400 km to 398 x 399 km. Undocked on 23 May 1994 00:58:38 GMT. Destroyed in reentry on 23 May 1994 04:40:00 GMT. Total free-flight time 2.23 days. Total docked time 59.76 days.
1994 May 22 - 04:30 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 76024355 Progress M-23 Mass: 7,117 kg (15,690 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 397 km (246 mi). Apogee: 399 km (247 mi). Inclination: 51.60 deg. Period: 92.52 min. Flight: Mir EO-15, Mir LD-4. Unmanned resupply vessel to Mir, with Raduga return capsule. Docked with Mir on 24 May 1994 06:18:35 GMT. Undocked on 2 Jul 1994 08:46:49 GMT. The braking engine was ignited at 14:44 GMT, and the Raduga VBK reentry capsule was ejected at 14:55:45 GMT. The Progress burnt up in the atmosphere at 14:57 GMT. The Raduga deployed its parachute after reentry and landed on 2 Jul 1994 15:09:00 GMT at 51 deg 41 min N, 59 deg 21 min E, in the Orenburg region. Total free-flight time 2.34 days. Total docked time 39.10 days.
1994 July 1 - 12:24 GMT - Launch Vehicle: Soyuz. Soyuz TM-19 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 396 km (246 mi). Apogee: 397 km (246 mi). Inclination: 51.60 deg. Period: 92.49 min. Crew: Malenchenko, Musabayev. Flight: Mir EO-16, Mir EO-15, Mir LD-4. Mir Expedition EO-16. Soyuz TM-19 docked at the rear port of the Kvant module (vacated by Progress M-23 on July 2) at 13:55:01 GMT on July 3.
1994 August 25 - 14:25 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U N15000-636 Progress M-24 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 394 km (244 mi). Apogee: 397 km (246 mi). Inclination: 51.60 deg. Period: 92.47 min. Flight: Mir EO-16, Mir LD-4. Unmanned resupply vessel to Mir. Failed to dock with Mir on 27 Aug 1994. A second automatic docking attempt on 30 Aug 1994 also failed and the Progress collided with the Kvant module. A third and final attempt, manually controlled by Mir commander Yuriy Malenchenko, was successful on 2 Sep 1994 13:30:28 GMT. The Mir commander and flight engineer, Yuriy Malenchenko and Talgat Musabaev, made a spacewalk on 9 Sep 1994 to inspect the damage to the Kvant module made when the Progress collided with Kvant. Undocked on 4 Oct 1994 18:55:52 GMT, leaving the rear docking port free for Soyuz TM-20. Destroyed in reentry over the Pacific at 38.4 deg S, 137.4 deg W,on 4 Oct 1994 22:43:00 GMT. Total free-flight time 8.12 days. Total docked time 32.23 days.
1994 October 3 - 22:42 GMT - Launch Vehicle: Soyuz. Soyuz TM-20 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 392 km (243 mi). Apogee: 395 km (245 mi). Inclination: 51.60 deg. Period: 92.43 min. Crew: Kondakova, Merbold, Viktorenko. Flight: Mir EO-17, Mir Euromir 94, Mir EO-16, Mir LD-4. Mir Expedition EO-17. Docked at the Mir forward port at 00:28 on 1994 October 6. The Mir crew of Viktorenko, Kondakova and Polyakov boarded Soyuz TM-20 on January 11, and undocked from Mir's front port at 09:00 GMT. The spacecraft withdrew to about two hundred metres from Mir and then redocked in a test of the automatic Kurs system, which had failed in Progress M-24's attempted docking. Redocking came at 09:25 GMT.
1994 November 11 - 07:21 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U Ya15000-638 Progress M-25 Mass: 7,125 kg (15,707 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 391 km (242 mi). Apogee: 394 km (244 mi). Inclination: 51.60 deg. Period: 92.41 min. Flight: Mir EO-17, Mir LD-4. Unmanned resupply vessel to Mir. Docked with Mir on 13 Nov 1994 09:04:29 GMT. Undocked on 16 Feb 1995 13:03:00 GMT. Destroyed in reentry on 16 Feb 1995 16:45:00 GMT. Total free-flight time 2.23 days. Total docked time 95.17 days.
1995 February 15 - 16:48 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U Ya15000-641 Progress M-26 Mass: 7,139 kg (15,738 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 391 km (242 mi). Apogee: 396 km (246 mi). Inclination: 51.60 deg. Period: 92.40 min. Flight: Mir EO-17, Mir LD-4. Unmanned resupply vessel to Mir. Docked with Mir on 17 Feb 1995 18:21:34 GMT. Undocked on 15 Mar 1995 02:26:38 GMT. Destroyed in reentry over the Pacific Ocean on 15 Mar 1995 06:15:00 GMT. Total free-flight time 2.22 days. Total docked time 25.34 days.
1995 March 14 - 06:11 GMT - Launch Vehicle: Soyuz. Soyuz TM-21 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 392 km (243 mi). Apogee: 398 km (247 mi). Inclination: 51.60 deg. Period: 92.50 min. Crew: Dezhurov, Strekalov, Thagard. Flight: Mir EO-18, Mir EO-17, Mir LD-4. Mir Expedition EO-18. Soyuz TM-21 carried the EO-18 Mir crew and American Norman Thagard. Thagard was the first American to be launched in a Soyuz. Soyuz docked with Mir at 07:45:26 GMT on March 16 . On July 4 Soyuz TM-21 undocked and backed off to a distance of 100 m from Mir. The US space shuttle Atlantis, with the EO-18 crew aboard, then undocked and began a flyaround at a distance of 210 m, while the EO-19 crew aboard Soyuz took pictures before redocking with the station. Soyuz TM-21 again undocked with the EO-19 crew on September 11 from the Kvant rear port on Mir and landed at 50 deg 41'N 68 deg 15'E, 108 km northeast of Arkalyk in Kazakhstan, at 06:52:40 GMT .
1995 April 9 - 19:34 GMT - Launch Vehicle: Soyuz. Progress M-27 Mass: 7,170 kg (15,800 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 396 km (246 mi). Apogee: 399 km (247 mi). Inclination: 51.60 deg. Period: 92.50 min. Flight: Mir EO-18. Unmanned resupply vessel to Mir; carried GFZ-1 German sub-satellite to Mir. Docked with Mir on 11 Apr 1995 21:00:44 GMT. Undocked on 22 May 1995 23:42:37 GMT. Destroyed in reentry on 23 May 1995 03:27:52 GMT. Total free-flight time 2.22 days. Total docked time 41.11 days.
1995 July 20 - 03:04 GMT - Launch Vehicle: Soyuz. Progress M-28 Mass: 7,125 kg (15,707 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 393 km (244 mi). Apogee: 398 km (247 mi). Inclination: 51.70 deg. Period: 92.50 min. Flight: Mir EO-19. Unmanned resupply vessel to Mir. Docked with Mir's front port on 22 Jul 1995 04:39:37 GMT. Undocked on 4 Sep 1995 05:09:53 GMT. Destroyed in reentry on 4 Sep 1995 08:58:55 GMT. Total free-flight time 2.22 days. Total docked time 44.02 days. Two Icons of Saint Anastasia were taken into space aboard the craft and transferred to the Mir station where they remained for about seven months. They were returned to earth, apparently aboard Soyuz TM-22, and later shown in diffent shrines around the world.
1995 September 3 - 09:00 GMT - Launch Vehicle: Soyuz. Soyuz TM-22 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 391 km (242 mi). Apogee: 398 km (247 mi). Inclination: 51.70 deg. Period: 92.50 min. Crew: Avdeyev, Gidzenko, Reiter. Flight: Mir EO-20, Mir EO-19. Mir Expedition EO-20. Crew commander was Yuriy Pavlovich Gidzenko of the Russian Air Force. Flight engineer was Sergey Vasilyevich Avdeev of RKK Energiya, and cosmonaut-researcher was Thomas Reiter of the European Space Agency. Soyuz TM-22 docked with Mir's front (-X) port at 10:29:54 GMT on September 5 and the hatch was opened at 11:01:23.
1995 October 8 - 18:50 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U V15000-645 Progress M-29 Mass: 7,122 kg (15,701 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 391 km (242 mi). Apogee: 400 km (240 mi). Inclination: 51.60 deg. Period: 92.50 min. Flight: Mir EO-20. Unmanned resupply vessel to Mir. Launched into an initial 194 x 242 km x 51.7 deg orbit. Docked with Mir's rear of the Kvant module port on 10 Oct 1995 20:32:40 GMT (Soyuz TM-22 was docked to the front port). Undocked on 19 Dec 1995 09:15:05 GMT. Destroyed in reentry on 19 Dec 1995 16:15:00 GMT. Total free-flight time 2.36 days. Total docked time 69.53 days.
1995 December 18 - 14:31 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 647 Progress M-30 Mass: 7,068 kg (15,582 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 391 km (242 mi). Apogee: 409 km (254 mi). Inclination: 51.70 deg. Period: 92.60 min. Flight: Mir EO-20. Unmanned resupply vessel to Mir. Docked with Mir on 20 Dec 1995 16:10:15 GMT. Undocked on 22 Feb 1996 07:30:02 GMT. Destroyed in reentry on 22 Feb 1996 11:02:36 GMT. Total free-flight time 2.22 days. Total docked time 63.64 days.
1996 February 21 - 12:34 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 651 Soyuz TM-23 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: MOM. Perigee: 375 km (233 mi). Apogee: 390 km (240 mi). Inclination: 51.70 deg. Period: 92.20 min. Crew: Onufrienko, Usachyov. Flight: Mir EO-21, Mir EO-20. Mir Expedition EO-21. Soyuz TM-23 docked with Mir at 14:20:35 on February 23.
1996 May 5 - 07:04 GMT - Launch Vehicle: Soyuz. Progress M-31 Mass: 7,140 kg (15,740 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 376 km (233 mi). Apogee: 390 km (240 mi). Inclination: 51.70 deg. Period: 92.20 min. Flight: Mir NASA-1, Mir EO-21. Unmanned resupply vessel to Mir. Delivered 1,140 kg of fuel and 1,700 kg of cargo to the Mir complex. Docked with Mir on 7 May 1996 08:54:19 GMT. Undocked on 1 Aug 1996 16:44:54 GMT. Destroyed in reentry over the Pacific on 1 Aug 1996 20:33:03 GMT. Total free-flight time 2.23 days. Total docked time 86.33 days.
1996 July 31 - 20:00 GMT - Launch Vehicle: Soyuz. Progress M-32 Mass: 7,130 kg (15,710 lb). Spacecraft: Progress M. Agency: MOM. Perigee: 371 km (230 mi). Apogee: 390 km (240 mi). Inclination: 51.70 deg. Period: 92.20 min. Flight: Mir NASA-1, Mir EO-21. Unmanned resupply vessel to Mir. This was the first successful launch of a Soyuz-U after two failures. Docked with Mir at the forward docking port on 2 Aug 1996 22:03:40 GMT. Undocked on 18 Aug 1996 09:33:45 GMT in order to free up the docking port. By 29 August 1994 Mir was in a 375 x 390 km x 51.6 deg orbit; the Progress M-32 cargo ship, flying separately, was in a 375 x 392 km x 51.6 deg orbit. Redocked with Mir on 3 Sep 1996 09:35:00 GMT at the rear port of the Kvant module. Finally undocked from Mir on 20 Nov 1996 19:51:20 GMT. Destroyed in reentry on 20 Nov 1996 22:42:25 GMT. Total free-flight time 2.20 days. Total docked time 93.91 days.
1996 August 17 - 13:18 GMT - Launch Vehicle: Soyuz. Soyuz TM-24 Mass: 7,150 kg (15,760 lb). Spacecraft: Soyuz TM. Agency: RKA. Perigee: 378 km (234 mi). Apogee: 394 km (244 mi). Inclination: 51.70 deg. Period: 92.30 min. Crew: Andre-Deshays, Kaleri, Korzun. Flight: Mir EO-22, Mir Cassiopee, Mir NASA-1, Mir EO-21. Mir Expedition EO-22. Valeriy Korzun and Aleksandr Kaleri of the Russian Space Agency (RKA) Claudie Andre-Deshays of the French space agency CNES. This launch was the first of the Soyuz-U booster with a crew aboard following two launch failures of on unmanned flights. Soyuz docked with Mir's front port at 14:50:21 GMT on August 19; Mir was in a 375 x 390 km x 51.6 deg orbit.
On Feb 7 at 16:28:01 GMT the EO-22 crew and American astronaut Linenger undocked the Soyuz TM-24 ferry from the front docking port, flew it around to the far side of the complex and redocked at the rear Kvant port at 16:51:27 GMT. This cleared the forward port for the arrival of the EO-23 crew, who brought with them German astronaut Reinhold Ewald on Feb 12.
1996 November 19 - 23:20 GMT - Launch Vehicle: Soyuz. Progress M-33 Mass: 7,190 kg (15,850 lb). Spacecraft: Progress M. Agency: RKA. Perigee: 361 km (224 mi). Apogee: 387 km (240 mi). Inclination: 51.70 deg. Period: 92.00 min. Flight: Mir NASA-2, Mir EO-22. Unmanned resupply vessel to Mir. Docked with Mir on 22 Nov 1996 01:01:30 GMT. Undocked on 6 Feb 1997 12:13:53 GMT. Thereafter in independent orbital flight in a 377 x 395 km x 51.65 deg orbit. Failed to redock with Mir on 4 Mar 1996. Destroyed in reentry on 12 Mar 1997 03:23:37 GMT. Total free-flight time 35.70 days. Total docked time 76.47 days.
1997 February 10 - 14:09 GMT - Launch Vehicle: Soyuz. Soyuz TM-25 Spacecraft: Soyuz TM. Agency: RKA. Perigee: 385 km (239 mi). Apogee: 392 km (243 mi). Inclination: 51.70 deg. Period: 92.30 min. Crew: Tsibliyev, Lazutkin, Ewald. Flight: Mir EO-23, Mir 97, Mir NASA-3, Mir EO-22. Mir Expedition EO-23. Soyuz TM-25 docked with Mir at the forward port on February 12 at 15:51:13 GMT.
1997 April 6 - 16:04 GMT - Launch Vehicle: Soyuz. Progress M-34 Mass: 7,156 kg (15,776 lb). Spacecraft: Progress M. Agency: RKA. Perigee: 375 km (233 mi). Apogee: 393 km (244 mi). Inclination: 51.70 deg. Period: 92.20 min. Flight: Mir NASA-3, Mir EO-23. Unmanned resupply vessel to Mir. It carried supplies for the Mir station and repair equipment for Mir's oxygen generators, replacement oxygen-generating 'candles' and a pair of new spacesuits. Docked with Mir at the rear Kvant module port on 8 Apr 1997 17:30:03 GMT. The Mir complex raised its orbit by 5 km on 15 Apr 1997 at 12:00 GMT, using Progress M-34's engine. Undocked on 24 Jun 1997 10:22:50 GMT. It was then used to perform a redocking test using newly developed remote-control procedures which were to replace the automatic system that Russia could no longer afford to buy from Ukraine. At 25 Jun 1997 09:18 GMT Mir commander Tsibliev was remotely commanding the approach of Progress to the Kvant module. This involved guiding the Progress via a television monitor. The Progress was difficult to see against the cloudy earth background at the time of the attempted docking. It went off course and collided with a solar array on the Spektr module and then the module itself. A large hole was made in a solar panel, one of the radiators was buckled, a hole was punched into Spektr's hull, and the module began to depressurize. This was not a slow leak - the crew heard a hissing sound and felt their ears pop. They disconnected the power cables leading from Mir to the main station and closed the hatch on the core module transfer section that led to Spektr. The Spektr module became fully depressurized, remaining docked to Mir with its docking hatch open. The loss of electrical connection between Spektr's solar panels and the main station cut the available power supply to the station, crippling its operations until later repairs reconnected the electrical lines. Tsibliev was also the pilot on a previous orbital collision, when he banged Soyuz TM-17 into Mir in Jan 1994. After the return of the crew to earth he was found to be to blame for the incident, although the fines assessed were later dismissed. The Progress M-34 cargo ship was backed to a safe distance from the station and was destroyed in reentry on 2 Jul 1997 06:31:50 GMT. Total free-flight time 9.90 days. Total docked time 76.70 days.
1997 July 5 - 04:11 GMT - Launch Vehicle: Soyuz. Progress M-35 Mass: 7,150 kg (15,760 lb). Spacecraft: Progress M. Agency: RKA. Perigee: 383 km (237 mi). Apogee: 391 km (242 mi). Inclination: 51.70 deg. Period: 92.30 min. Flight: Mir NASA-4, Mir EO-23. Unmanned resupply vessel to Mir. Docked with Mir on 7 Jul 1997 05:59:24 GMT. Undocked on 6 Aug 1997 11:46:45 GMT. Redocked with Mir on 18 Aug 1997 12:52:48 GMT. Final undocking on 7 Oct 1997 12:03:49 GMT. Destroyed in reentry on 7 Oct 1997 17:23:00 GMT. Total free-flight time 2.30 days. Total docked time 80.21 days.
1997 August 5 - 15:35 GMT - Launch Vehicle: Soyuz. Soyuz TM-26 Spacecraft: Soyuz TM. Agency: RKA. Perigee: 378 km (234 mi). Apogee: 385 km (239 mi). Inclination: 51.70 deg. Period: 92.20 min. Crew: Solovyov, Vinogradov. Flight: Mir EO-24, Mir NASA-4, Mir EO-23. Mir Expedition EO-24. The Soyuz docked manually at 17:02 GMT August 7. Over the next six months the crew undertook seven internal and external spacewalks to repair the crippled space station.
1997 October 5 - 15:08 GMT - Launch Vehicle: Soyuz. Progress M-36 Mass: 7,195 kg (15,862 lb). Spacecraft: Progress M. Agency: RKA. Perigee: 378 km (234 mi). Apogee: 390 km (240 mi). Inclination: 51.70 deg. Period: 92.20 min. Flight: STS-86, Mir NASA-5, Mir NASA-4, Mir EO-24. Unmanned resupply vessel to Mir. Docked with Mir on 8 Oct 1997 17:07:09 GMT. Undocked on 17 Dec 1997 06:01:53 GMT. Destroyed in reentry on 19 Dec 1997 13:20:01 GMT. Total free-flight time 5.39 days. Total docked time 69.54 days.
1997 December 20 - 08:45 GMT - Launch Vehicle: Soyuz. Progress M-37 Mass: 7,040 kg (15,520 lb). Spacecraft: Progress M. Agency: RKA. Perigee: 363 km (225 mi). Apogee: 403 km (250 mi). Inclination: 51.80 deg. Period: 92.20 min. Flight: Mir NASA-5, Mir EO-24. Unmanned resupply vessel to Mir. Docked with Mir at the rear Kvant port on 22 Dec 1997 10:22:20 GMT. Undocked on 30 Jan 1998 12:00:00 GMT. Redocked with Mir on 23 Feb 1998 09:42:28 GMT. Final undocking 15 Mar 1998 19:16:01 GMT. Destroyed in reentry on 15 Mar 1998 23:04:00 GMT. Total free-flight time 2.23 days. Total docked time 59.47 days.
1998 January 29 - 16:33 GMT - Launch Vehicle: Soyuz. Soyuz TM-27 Spacecraft: Soyuz TM. Agency: RKA. Perigee: 363 km (225 mi). Apogee: 373 km (231 mi). Inclination: 51.70 deg. Period: 91.90 min. Crew: Musabayev, Budarin, Eyharts. Flight: Mir EO-25, Mir Pegase, Mir NASA-5, Mir EO-24, STS-89, Mir NASA-6. Soyuz TM-27 carried the Mir EO-25 crew and French astronaut Leopold Eyharts. NASA and the Russian Space Agency had hoped Soyuz TM-27 could dock with Mir while Endeavour was still there, resulting in an on-board crew of 13, a record which would have stood for years or decades. But the French vetoed this, saying the commotion and time wasted would ruin Eyharts Pegase experimental programme. Soyuz TM-27 docked at the Kvant module port at 17:54 GMT on January 31, 1998, less than five hours before Endeavour landed in Florida.
Solovyov handed over command of Mir to EO-25 commander Musabayev, and the Mir EO-24 crew and Eyharts undocked from the forward port of Mir at 05:52 GMT on February 19 aboard the Soyuz TM-26 for their return home. On February 20, the EO-25 crew and Andy Thomas of the NASA-7 mission boarded Soyuz TM-27 and undocked from the Kvant port at 08:48 GMT. They redocked with the forward port on Mir at 09:32 GMT. This freed up the Kvant port for a test redocking of the Progress M-37 cargo ship, parked in a following orbit with Mir during the crew transfer.
1998 March 14 - 22:45 GMT - Launch Vehicle: Soyuz. Progress M-38 Mass: 7,007 kg (15,447 lb). Spacecraft: Progress M. Agency: RKA. Perigee: 372 km (231 mi). Apogee: 379 km (235 mi). Inclination: 51.70 deg. Period: 92.10 min. Flight: Mir NASA-6, Mir EO-25. Progress M-38 was specially modified to carry the second 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 spacewalks 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 station. By 03:20 GMT on March 15 1998 Progress M-38 had successfully completed its first two orbital manoeuvres. It replaced Progress M-37 at the docking port on the Kvant module, with a successful docking on March 16 1998 at 22:45 GMT. Undocked May 15 at 1844 UTC, freeing up the docking port on the Kvant module for Progress M-39. Deorbited over Pacific May 15, 1998.
1998 May 14 - 22:12 GMT - Launch Vehicle: Soyuz. Progress M-39 Spacecraft: Progress M. Agency: RKA. Perigee: 360 km (220 mi). Apogee: 373 km (231 mi). Inclination: 51.70 deg. Period: 91.90 min. Flight: Mir NASA-6, Mir EO-25. Docked with Mir at the Kvant port at 23:51 GMT on May 16 1998, bringing supplies and scientific experiments to the station. Undocked 09:28 GMT on August 12 1998 in order to clear the port for Soyuz TM-28. Deorbited over Pacific Ocean on October 29, 1998.
1998 August 13 - 09:43 GMT - Launch Vehicle: Soyuz. Soyuz TM-28 Spacecraft: Soyuz TM. Agency: RKA. Perigee: 363 km (225 mi). Apogee: 373 km (231 mi). Inclination: 51.70 deg. Period: 91.90 min. Crew: Padalka, Avdeyev, Baturin. Flight: Mir EP-4, Mir EO-26, Mir EO-25, Mir EO-26/-27. Soyuz TM-28 docked at 10:56 GMT on August 15 with the rear (Kvant) port of the Mir space station, which had been vacated at 09:28 GMT on August 12 by Progress M-39. The EO-25 crew, Musabayev and Budarin, landed with Baturin on Aug 25, leaving the EO-26 crew of Padalka and Avdeyev on the station. As only one final Soyuz mission to Mir was planned, with two of the seats on that Soyuz pre-sold to Slovak and French experimenters, the return crew of Soyuz TM-28 was subject to constant replanning and revision. On February 8, 1999, at 11:23 GMT Padalka and Avdeyev undocked from Mir's -X port in Soyuz TM-28, and redocked at the +X Kvant port at 11:39 GMT, freeing up the front port for the Soyuz TM-29 docking. Finally on February 27, 1999 EO-26 commander Padalka and Slovak cosmonaut Bella undocked Soyuz TM-28 from the Kvant rear docking port at 22:52 GMT, landing in Kazakhstan on February 28 at 02:14 GMT. Avdeyev remained on Mir with the EO-27 crew delivered on Soyuz TM-29, heading for a manned space flight time record.
1998 October 25 - 04:14 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 660 Progress M-40 Spacecraft: Progress M. Agency: RKA. Perigee: 349 km (216 mi). Apogee: 360 km (220 mi). Inclination: 51.60 deg. Period: 91.63 min. Flight: Mir EO-26, Mir EO-26/-27. Docked with the rear (+X, Kvant) docking port of the Mir station on October 27. Delivered fuel, dry cargo, and the Znamya-2.5 solar illumination experiment. This was a follow-on to the earlier Znamya-2 experiment on Progress M-15 in 1992. The 25 m diameter Znamya reflector, which would unfold from the nose of the Progress, was to reflect sunlight over a 6 km area onto selected cities. Znamya-2.5 was developed by the Space Regatta Consortium, led by RKK Energia. Energia had long studied such space mirrors as a means of providing lighting to Siberian towns. The project was opposed by environmentalists and astronomers, who feared light pollution. Progress M-40 undocked on February 4, 1999 at 09:59 GMT, but the attempted deployment of the Znamya-2.5 reflector was thwarted when it snagged on a rendezvous system antenna. After two more failed attempts to deploy the antenna the experiment was abandoned. Progress M-40 fired its engines at 10:16 GMT on February 5, braked out of orbit, and burned up over the Pacific Ocean.
1999 February 9 - 03:53 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U/Ikar S15000-058 ST01 Globalstar FM36 Mass: 222 kg (489 lb). Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. The first launch of the Soyuz- Ikar launch vehicle, selected by Orbcomm after failure of the Zenit launcher. The Ikar upper stage was derived from the Yantar reconnaissance satellite's propulsion module. The Soyuz second stage separated at 8 minutes 48 seconds into flight after placing the Ikar into a 236 km x 884 km x 52.0 deg transfer orbit. The Ikar stage burned at the second apogee passage, at 06:23 GMT, and released the Globalstar satellite at the top of the dispenser into a 915 km x 947 km x 52.0 deg orbit at 07:27 GMT. The three remaining satellites mounted around the side of the dispenser were released into a 903 km x 946 km x 52.0 deg orbit. This was also the first launch carried out by the Starsem organization, a joint venture including Aerospatiale and TsSKB-Progress (the launch vehicle manufacturer). The dispenser was built by Aerospatiale/Aquitaine (Bordeaux).
1999 February 20 - 04:18 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U M15000-662 Soyuz TM-29 Spacecraft: Soyuz TM. Agency: RKA. Perigee: 341 km (211 mi). Apogee: 357 km (221 mi). Inclination: 51.60 deg. Period: 91.52 min. Crew: Afanasyev, Haignere, Bella. Flight: Mir EO-27, Mir Stefanik, Mir EO-26, Mir EO-26/-27. Soyuz TM-29 docked with Mir on February 22 at 05:36 GMT. Since two crew seats had been sold (to Slovakia and France), Afansyev was the only Russian cosmonaut aboard. This meant that Russian engineer Avdeyev already aboard Mir would have to accept a double-length assignment. After the February 27 departure of EO-26 crew commander Padalka and Slovak cosmonaut Bella aboard Soyuz TM-28, the new EO-27 Mir crew consisted of Afanasyev as Commander, Avdeyev as Engineer and French cosmonaut Haignere. Follwoing an extended mission and three space walks, the last operational crew aboard Mir prepared to return. The station was powered down and prepared for free drift mode.
1999 March 15 - 03:06 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U/Ikar - ST02 Globalstar M022 Mass: 222 kg (489 lb). Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min. In the second Soyuz/Ikar launch four Globalstar satellites were delivered with the Ikar upper stage into a 235 km x 899 km x 52.0 degree transfer orbit. The Ikar stage then placed itself and its payload into a 897 km x 950 km x 52.0 degree deployment orbit. Satellite M022 was separated first from the top of the dispenser, followed by ejection of the other three satellites from the sides at 06:37 GMT. After dispensing the satellites, the Ikar deorbited itself on March 16.
1999 April 2 - 11:28 GMT - Launch Vehicle: Soyuz. Progress M-41 Spacecraft: Progress M. Agency: RKA. Perigee: 336 km (208 mi). Apogee: 361 km (224 mi). Inclination: 51.60 deg. Period: 91.51 min. Flight: Mir EO-27, Mir EO-26/-27. Resupply craft docked uneventfully with the Mir complex two days later. It also delivered the Sputnik-99 amateur radio satellite, launched into orbit by hand by the cosmonauts during an EVA on April 16. Still hopeful of finding a backer to pay to keep Mir in space, Progress M-41 began a series of engine burns in late April to raise the orbit of the station. It finally undocked from Mir at 11:20 GMT on July 17 and was deorbited over the Pacific later the same day.
1999 April 15 - 00:46 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U/Ikar S15000-060 ST03 Globalstar M019 Mass: 222 kg (489 lb). Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,412 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. The Ikar upper stage entered a 234 km x 900 km transfer orbit, then maneuvered to dispense the four spacecraft into 900 km x 950 km x 52.0 deg parking orbits. The satellite's own thrusters would be used to place them into their 1410 km circular operational orbits. The Ikar stage deorbited itself after one day. The Globalstar satellites, built by Alenia and Loral, are L-band comsats which provide satellite phone service.
1999 July 16 - 16:37 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 667 Progress M-42 Spacecraft: Progress M. Agency: RAKA. Perigee: 340 km (210 mi). Apogee: 348 km (216 mi). Inclination: 51.60 deg. Period: 91.42 min. Flight: Mir EO-27, Mir EO-26/-27. Delivered supplies to the crew of the Mir complex. Docked with the Kvant port at 17:53 GMT on July 18. Remained docked to the station after the departure of the last operational crew in September 1999. Undocked on February 2. 2000, to clear the port for Progress M1, at 0311:52 GMT. Deorbited over the Pacific later the same day at 0610:40 UTC with an 8 minute burn.
1999 September 22 - 14:33 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U/Ikar S15000-061 ST04 Globalstar 33 Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,412 km (877 mi). Apogee: 1,416 km (879 mi). Inclination: 52.00 deg. Period: 114.10 min. The third stage put the complex into a 235 km x 906 km x 51.9 degree transfer orbit. The Ikar upper stage maneouvered, placed the four satellites into their final parking orbit, then made a deorbit burn and re-entered on September 24.
1999 October 18 - 13:22 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U/Ikar M15000-062 ST05 Globalstar 31 Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min. At the time of this launch Globalstar began limited service of its satellite telephone system.
1999 November 22 - 16:20 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U/Ikar - ST06 Globalstar 29 Spacecraft: Globalstar. Agency: Globalst. Perigee: 1,413 km (877 mi). Apogee: 1,414 km (878 mi). Inclination: 52.00 deg. Period: 114.10 min. Additional launches into Globalstar communications satellite constellation.
2000 February 1 - 06:47 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U A15000-669 Progress M1-1 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M1. Agency: RAKA. Perigee: 342 km (212 mi). Apogee: 348 km (216 mi). Inclination: 51.60 deg. Period: 91.44 min. Progress M1 was a modification of the Progress M for the International Space Station. The first such spacecraft was diverted to raise the orbit of Mir. It docked with the unoccupied Mir space station on February 3 at 0802:20 GMT. Burns of its motor to raise Mir's orbit began on February 5 and continued through February 9. Progress M1-1 undocked at 16:33 GMT on April 26 to clear the docking port for Progress M1-2. It was deorbited over the Pacific at 19:27 GMT the same day.
2000 April 4 - 05:01 GMT - Launch Vehicle: Soyuz. Soyuz TM-30 Mass: 7,250 kg (15,980 lb). Spacecraft: Soyuz TM. Agency: RAKA. Perigee: 358 km (222 mi). Apogee: 384 km (238 mi). Inclination: 51.60 deg. Period: 91.97 min. Crew: Kaleri, Zalyotin. Flight: Mir EO-28. Soyuz TM-30 docked with Mir's forward (-X) port on April 6 at 0631 GMT. Zalyotin and Kaleri reactivated the uninhabited station. Unloading Progress M1-1 and M1-2, they resupplied the station. The Progress spacecraft were also used to raise the station's orbit to 360 x 378 km x 51.6 deg. The orbital plane of Mir was then around 120 degrees away from that of ISS (making transport between the stations impossible, as desired by NASA).
2000 April 25 - 20:08 GMT - Launch Vehicle: Soyuz. Progress M1-2 Mass: 7,280 kg (16,040 lb). Spacecraft: Progress M1. Agency: RAKA. Perigee: 363 km (225 mi). Apogee: 380 km (230 mi). Inclination: 51.60 deg. Period: 91.98 min. Flight: Mir EO-28. Progress M1-2 docked with the rear Kvant port of Mir at 2128 GMT on April 27. Mir's orbit was raised on April 29 in the first of a series of three burns by Progress M1-2. It later undocked and was deorbited over the Pacific on 15 October.
2000 May 3 - 13:25 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U A15000-649 Cosmos 2370 Mass: 6,700 kg (14,700 lb). Spacecraft: Yantar-4KS1. Agency: MO RF. Perigee: 244 km (152 mi). Apogee: 312 km (194 mi). Inclination: 64.73 deg. Period: 90.00 min. Military Observation. Advanced imaging reconnaissance satellite. Relays digital imagery to earth via geostationary comsats. The last such satellite, Cosmos 2359, reentered in July 1999 after one year in orbit. The Soyuz-U launcher placed it in a 183 x 277 km x 64.8 deg initial orbit; it raised altitude to 240 x 300 km about 24 hr after launch.
2000 August 6 - 18:26 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U K15000-668 Progress M1-3 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M1. Agency: RAKA. Perigee: 347 km (215 mi). Apogee: 362 km (224 mi). Inclination: 51.50 deg. Period: 91.63 min. Flight: STS-106. Progress M1-3 automatically docked with the International Space Station on August 8 at 20:13 GMT at the rear Zvezda port. The supply ship began refuelling of the station a few days later. It remained attached for offloading of its dry cargo by the STS-106 crew. It later separated from Zvezda's rear port at 0405 GMT November 1 and was deorbited over the Pacific at 0705 GMT.
2000 October 16 - 21:27 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U K15000-085 Progress M-43 Mass: 6,860 kg (15,120 lb). Spacecraft: Progress M. Agency: RAKA. Perigee: 186 km (115 mi). Apogee: 228 km (141 mi). Inclination: 51.60 deg. Period: 88.64 min. Mir Servicing flight. Launch delayed from October 15. Progress docked with Mir, primarily to raise its orbit and preserve the option of a MirCorp-financed flight in 2001. However the funding never came through and the decision was taken to deorbit Mir. Progress M-43 undocked at 0519 GMT on January 25 from the +X Kvant port to clear it for Progress M1-5 (which would deorbit the Mir station). On January 29 Progress M-43 was in a 271 x 280 km x 51.6 deg orbit.
2000 October 31 - 07:52 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U A15000-666 Soyuz TM-31 Mass: 7,250 kg (15,980 lb). Spacecraft: Soyuz TM. Agency: RAKA. Perigee: 378 km (234 mi). Apogee: 385 km (239 mi). Inclination: 51.50 deg. Period: 92.18 min. Crew: Gidzenko, Krikalyov, Shepherd. Flight: ISS EO-1. Soyuz TM-31 delivered the Expedition One crew to the International Space Station with Gidzenko as the Soyuz crew commander with the call-sign 'Uran'. The spacecraft docked at Zvezda's rear port at 0921 GMT on November 2. The hatch to Zvezda was opened at 1023 GMT. Once aboard ISS, Shepherd became the ISS Commander, with 'Station Alpha' as the ISS callsign. Soyuz TM-31, with Shepherd, Gidzenko and Krikalyov aboard, undocked from the -Y port on Zvezda on February 24, 2001 at 1006 GMT and redocked with the -Z port on Zarya at 1037 GMT. This freed the Zvezda port for a Progress resupply ship. After the departure of the Progress, Soyuz TM-31 undocked from the Zarya nadir port April 18 2001 at 1240 GMT and redocked with the Zvezda aft port at 1301 GMT, leaving clearance for the Raffaello MPLM module to be berthed at the Unity nadir during the STS-100 mission.
2000 November 16 - 00:00 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U K15000-671 Progress M1-4 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M1. Agency: RAKA. Perigee: 357 km (221 mi). Apogee: 369 km (229 mi). Inclination: 51.60 deg. Flight: ISS EO-1. Progress M1-4 was an unmanned resupply craft that rendezvoused with the International Space Station on November 18. After problems with the automatic system, ISS Expedition 1 crew member Gidzenko took over manual control with the remote TORU system at 0302 GMT. The first docking attempt was aborted when M1-4 was only 5 m from the station at 0309 GMT. On the second attempt docking was successfully achieved at 0348 GMT at Zarya's nadir port. The problem on the first attempt was icing of the TORU system TV camera on the Progress when the spacecraft was in shadow. Progress M1-4 undocked from ISS at 1623 GMT on December 1. Following the mission of STS-97 Progress M1-4 redocked to Zarya's nadir port on December 26 at 1054 GMT. The redocking tested a fix to the software that caused problems in the vehicle's first docking attempt on November 18. Yuri Gidzenko completed the docking manually using the remote control TORU system. Progress M1-4 undocked from Zarya's nadir port for the last time at 1126 GMT on February 8. It was deorbited over the Pacific and reentered at 1350 GMT the same day.
2001 January 24 - 04:28 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U K15000-673 Progress M1-5 Mass: 7,300 kg (16,000 lb). Spacecraft: Progress M1. Agency: RAKA. Perigee: 278 km (172 mi). Apogee: 299 km (185 mi). Inclination: 51.60 deg. Mir Deorbiting mission. Launch delayed from January 16 and 18. The Mir station had a power failure on January 18, delaying the launch of the Progress cargo ship that was to deorbit it for a few days. Nick-named "Hearse", it was to deliver the 130 tonne Mir station to its cremation over the southern Pacific. Six cosmonauts were on "Hot-Standby" to reach Mir in the event the automatic docking failed. Progress M1-5 carried 2677 kg of fuel. A special three-day fuel-economy approach was be used to keep as much fuel as possibile for the deorbit. Progress M1-5 docked with the +X Kvant port at 0533 GMT on January 27. It later undocked and was deorbited over the Pacific together with Mir on 23 March.
2001 February 26 - 08:09 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 670 / ISS-3P Progress M-44 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: RAKA. Perigee: 193 km (119 mi). Apogee: 243 km (150 mi). Inclination: 51.60 deg. Flight: ISS EO-1. ISS Servicing flight. Launch delayed from February10/20. Progress M-44 was a Russian, automatic cargo carrier that carried 2.5 tonnes of food, water, fuel, oxygen, and equipment to the International Space Station. In preparation for the docking, the ISS crew repositioned the Soyuz TM-31 escape craft from its port on Zvezda to a port on the Zarya module. Progress M-44 docked with the -Y port on Zvezda at 09:47 UT on 28 February. It undocked from Zvezda's aft port on April 16 at 0848 GMT and was deorbited at 1323 GMT over the Pacific Ocean.
2001 April 28 - 07:37 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 674 Soyuz TM-32 Mass: 6,750 kg (14,880 lb). Spacecraft: Soyuz TM. Agency: RAKA. Perigee: 254 km (157 mi). Apogee: 326 km (202 mi). Inclination: 51.60 deg. Crew: Musabayev, Baturin, Tito. Flight: ISS EP-1. Soyuz TM-32 was designated ISS flight 2S by NASA and EP-1 (Visiting Crew 1) by RKK Energia. Soyuz TM-32 was a fresh lifeboat for the station; the Soyuz TM-31 crew themselves would return in Soyuz TM-31, which was at the end of its rated in-space storage tie. Dennis Tito's inclusion in the crew created controversy between NASA and the Russians since he was the first space tourist to fly to ISS. He had originally paid to fly to the Mir station but funds ran out to keep that station in orbit. Soyuz TM-32 docked with the -Z port on Zarya at 0758 GMT on April 30 after Endeavour had departed.. The crew transferred their customized reentry seat liners to Soyuz TM-31, at which point TM-32 became the Station's rescue vehicle. After a six day stay, the Soyuz TM-32 crew returned to earth aboard Soyuz TM-31. The Expedition 3 crew entered Soyuz TM-32) on October 19, 2001 and undocked from the nadir port of Zarya at 1048 GMT, flying it out and then sideways a few meters before approaching the station again to dock with the Pirs nadir port at 1104 GMT. This freed up Zarya for the arrival of a new Soyuz. The docking port at the aft end of Zvezda was occupied by the Progress M-45 cargo ship.
2001 May 20 - 22:32 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG F15000-001? Progress M1-6 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M1. Agency: RAKA. Perigee: 270 km (160 mi). Apogee: 316 km (196 mi). Inclination: 51.60 deg. Flight: ISS EO-2. ISS Servicing flight. Launch delayed from april 12. This Progress resupply mission to the ISS was launched by the first Soyuz-FG rocket - a modified Soyuz-U with 5 percent improved perfomance using new fuel utilisation systems. Progress M1-6 after launch was also designated as ISS supply mission 4P. It carried 2.5 tonnes of food, fuel, water, life-support material, and equipment, including spare computer equipment for the ISS Destiny module. Nearly one tonne of the fuel was for raising the altitude of the ISS. Progress M1-6 docked with Zvezda's aft (-Y) port at 0024 GMT on May 23. It undocked at 0601 GMT on August 22 and deorbited at around 0900 GMT the same day.
2001 August 21 - 09:23 GMT - Launch Vehicle: Soyuz. Progress M-45 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: Rosaviakosmos (Russia). Perigee: 193 km (119 mi). Apogee: 245 km (152 mi). Inclination: 51.70 deg. Flight: ISS EO-3. ISS Servicing Mission. Launch delayed from July 4 and 24. Progress M-45, 7K-TGM No. 245 (of the older generation series of Progress) docked with the ISS at 0951 GMT on August 23 at the aft Zvezda port vacated by Progress M6-1 a day earlier. It and delivered 2.5 tonnes of fuel, water, oxygen, equipment and spare parts. Progress M-45 undocked on November 22 and was deorbited over the Pacific later the same day.
2001 September 14 - 23:34 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 677 Progress M-SO1 Mass: 6,900 kg (15,200 lb). Spacecraft: Progress M-SO. Agency: RAKA. Perigee: 388 km (241 mi). Apogee: 394 km (245 mi). Inclination: 51.60 deg. Flight: ISS EO-3. Progress M-SO1 was the designation given to the service module section of a Progress M; the 3900 kg Pirs docking and airlock module for the ISS replaced the standard cargo and fuel sections. It also carried an astronaut chair, a space suit, a small crane, and some equipment for the Zvezda module of the ISS. Progress-M No. 301 was launched into an initial 180 km circular orbit. By September 16 it had maneuvered into a 238 x 264 km orbit; by 0038 GMT on September 17, a 385 x 395 km x 51.6 deg orbit upon rendezvous with the ISS. The Progress began a fly around of the station and lined up with the nadir port on Zvezda. Docking of Pirs with Zvezda came at 0105 GMT on September 17. The Progress M-SO1 later undocked from the Pirs nadir port to leave it free for future dockings. Pirs gave extra clearance from the Station for ships docking underneath Zvezda, and was also used as an airlock for spacewalks using the Russian Orlan EVA suits. Progress M-SO1 service module undocked from the Pirs module at 1536 GMT on September 26 and was deorbited over the Pacific at 2330 GMT the same day.
2001 October 21 - 08:59 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 672 Soyuz TM-33 Mass: 6,750 kg (14,880 lb). Spacecraft: Soyuz TM. Agency: RAKA. Perigee: 388 km (241 mi). Apogee: 399 km (247 mi). Inclination: 51.60 deg. Crew: Afanasyev, Kozeyev, Andre-Deshays. Flight: ISS EP-2. Soyuz TM-33, an ISS lifeboat, carried two Russian and one French cosmonaut to the International Space Station (ISS). It docked with the ISS at 10:00 UT on 23 October. This new crew spent eight days on the ISS, and returned on the older Soyuz TM-32 at 03:59 UT on 31 October. The new Soyuz was to remain docked as a lifeboat craft for the long-term ISS crew of three (two Russian and one American) astronauts. On May 5, 2002, after a week aboard the station, the visting Soyuz TM-34 crew moved to the old Soyuz TM-33, docked at the Pirs port. They undocked at 0031:08 UTC on May 5, leaving the EO-4 crew of Onufrienko, Walz and Bursch with the new Soyuz TM-34 as their rescue vehicle. Soyuz TM-33 made its deorbit burn at 0257 UTC and landed successfully at 0352 UTC 25 km SE of Arkalyk.
2001 November 26 - 18:24 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG F15000-002 / ISS-6P Progress M1-7 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M1. Agency: Rosaviakosmos (Russia). Perigee: 230 km (140 mi). Apogee: 244 km (151 mi). Inclination: 51.60 deg. Flight: ISS EO-3. ISS Servicing flight. Launch delayed from November 14. The Progress M1-7 Russian automatic cargo carrier soft docked with the International Space Station Zvezda module at 1943 GMT on Nov 28. The docking probe retracted, but the eight peripheral latches would not engage. It turned out that a rubber seal had been left on the docking ring by Progress M-45. Cosmonauts from aboard the station cleared the debris in a spacewalk on December 3. As they watched from a few meters away Progress M1-7 was commanded to a hard dock with the station. NASA referred to this flight as `Progress 6'. It delivered 2.5 tonnes of food, fuel and equipment to the station, as well as a microsatellite named Kolibri. The Expedition 4 crew finished loading trash into Progress M1-7 on 19 March 2002, and it undocked from Zvezda's aft port at 1743 UTC. The Kolibri-2000 microsatellite was ejected from the Progress cargo compartment at 2228 UTC; Progress fired its engines to deorbit over the Pacific at about 0127 UTC on Mar 20.
2002 March 21 - 20:13 GMT - Launch Vehicle: Soyuz. Soyuz 11A511U 678 / ISS-7P Progress M1-8 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M1. Agency: Rosaviakosmos (Russia). Perigee: 379 km (235 mi). Apogee: 398 km (247 mi). Inclination: 51.60 deg. Period: 92.30 min. Flight: ISS EO-4. ISS Servicing mission. Launch delayed from February 15 and 28. The Progress M1-8 resupply spacecraft was flown on ISS mission 7P. It docked with the Zvezda module on the Station at 2058 UTC on March 24. Progress M1-8 undocked from the Zvezda module at 0826 UTC on June 25. The deorbit burn was at 1135 UTC, lowering its orbit from 379 x 398 km x 51.6 deg to 50 x 398 km. The spacecraft reentered over the Pacific at 1213 UTC with debris impact near 46 S 144 W.
2002 April 25 - 06:26 GMT - Launch Vehicle: Soyuz. Soyuz TM-34 Mass: 6,750 kg (14,880 lb). Spacecraft: Soyuz TM. Agency: RAKA. Perigee: 387 km (240 mi). Apogee: 397 km (246 mi). Inclination: 51.60 deg. Period: 92.40 min. Crew: Gidzenko, Vittori, Shuttleworth. Flight: ISS EP-3. Launch delayed from April 10, 22 and 17. Soyuz TM-34 was launched on ISS Mission 4S with Commander Yuri Gidzenko of Rosaviakosmos, Flight Engineer is Roberto Vittori of ESA, and Tourist Mark Shuttleworth, a South African citizen. At 1210 UTC Soyuz TM-34 was in a 242 x 269 km x 51.6 deg orbit. The flight was also referred to as ISS Mission 4S, the EP-3 visiting crew flight, and even as 'Soyuz 4' by NASA. Soyuz TM-34 docked with the nadir port on the Zarya module at 0755 UTC on April 27. The 4S flight docked at the Zarya nadir port on April 27. and the crew would return to Earth in the old TM-33 vehicle, leaving TM-34 as the active ISS rescue vehicle.
2002 June 26 - 05:36 GMT - Launch Vehicle: Soyuz. Progress M-46 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: Rosaviakosmos (Russia). Perigee: 387 km (240 mi). Apogee: 397 km (246 mi). Inclination: 51.60 deg. Period: 92.40 min. Flight: ISS EO-5. Launch delayed from May 21, then moved forward from July 14. Progress M-46 was launched on ISS mission 8P and docked with the Zvezda module at 0623 UTC on June 29 after carrying out tests of the Kurs rendezvous system on June 28. Seperated from ISS and commanded to destructive re-entry on 14 October 2002.
2002 September 25 - 16:58 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG E15000-003 Progress M1-9 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M1. Agency: Rosaviakosmos (Russia). Perigee: 282 km (175 mi). Apogee: 324 km (201 mi). Inclination: 51.63 deg. Period: 90.60 min. Flight: ISS EO-5. Launch delayed from July 22, September 10 and 20. Progress-M1 9, known to NASA as Progress 9P, was a Russian automatic cargo transportation craft that was to deliver food, fuel, and supplies to the International Space Station (ISS). It docked with the Zvezda module of the ISS on September 29 at 1700 UTC. Prior to the docking, the port was vacated by the earlier Progress-M 46. Undocked from the station on 1 February 2003 and commanded to destructive re-entry in the atmosphere.
2002 October 30 - 03:11 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG E15000-004 Soyuz TMA-1 Mass: 7,250 kg (15,980 lb). Spacecraft: Soyuz TMA. Agency: RAKA. Perigee: 278 km (172 mi). Apogee: 295 km (183 mi). Inclination: 51.62 deg. Period: 90.20 min. Crew: Zalyotin, De Winne, Lonchakov. Flight: ISS EP-4. Launch delayed from October 22, 28 pending investigation of causes of failure of another Soyuz booster on 15 October. Soyuz-TMA 1 was a Russian automatic passenger craft. It carried the EP-4 visiting crew of three astronauts (two Russians and one Belgian) to automatically dock with the International Space Station (ISS). This was the first flight of the new Soyuz-TMA model. It was to remain parked at the ISS as the escape craft, relieving the Soyuz TM-34. The crew conducted several microgravity experiments on the ISS during their 10-day stay before returning in Soyuz TM-34.
2003 February 2 - 12:59 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz 11A511U . Soyuz-U E15000-680 Progress M-47 Mass: 7,290 kg (16,070 lb). Spacecraft: Progress M. Agency: Rosaviakosmos. Perigee: 195 km (121 mi). Apogee: 247 km (154 mi). Inclination: 51.65 deg. Period: 88.77 min. Flight: ISS EO-6. Launch delayed from original schedule of January 30, and was made just one day after the Columbia disaster resulted in a suspension of shuttle flights. Docked successfully with the ISS on 14:49 GMT on 4 February 2003. Undocked from Zvezda on August 27 and deorbited later the same day.
2003 April 26 - 03:53 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG ?15000-006 Soyuz TMA-2 Mass: 7,250 kg (15,980 lb). Spacecraft: Soyuz TMA. Agency: Rosaviakosmos. Perigee: 386 km (239 mi). Apogee: 394 km (244 mi). Inclination: 51.60 deg. Period: 92.40 min. Crew: Malenchenko, Lu. Flight: ISS EO-7. Two-man Russian/American crew to provide minimal manning of space station while shuttle is grounded. Replaced three-man crew aboard ISS since before STS-107 disaster.
2003 June 8 - 10:34 GMT - Launch Vehicle: Soyuz. Soyuz-U D15000-681 Progress M1-10 Mass: 7,270 kg (16,020 lb). Spacecraft: Progress M1. Agency: Rosaviakosmo. Perigee: 247 km (153 mi). Apogee: 341 km (211 mi). Inclination: 51.60 deg. Period: 90.40 min. Flight: ISS EO-7. Resupply of International Space Station. Additional water carried to meet needs of skeleton crew. Successfully docked with the nadir port on Pirs at 1115 GMT on June 11. It undocked from the station on September 4 to clear the port for Soyuz TMA-3 but then unusually spent a month on an autonomous earth observation mission. The deorbit engine ignited at 11:26 GMT on October 3 from a 247 x 340 km x 51.6 deg orbit, reducing the perigee to 69 km. Progress M1-10 reentered the atmosphere over the Pacific at 11:58 GMT and broke up around 12:05 GMT.
2003 August 29 - 01:47 GMT - Launch Vehicle: Soyuz. Soyuz-U D15000-682 Progress M-48 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: Rosaviakosmos. Perigee: 376 km (233 mi). Apogee: 383 km (237 mi). Inclination: 51.60 deg. Period: 92.10 min. Flight: ISS EO-7. Delayed from July 30, moved up from September 18 and August 30. Docked with the Zvezda module of the ISS on August 31. Undocked from the station at 08:36 GMT on 28 January 2004 after being filled with trash and unneeded equipment. Deorbited and reentered over the Pacific at 13:46 GMT.
2003 October 18 - 05:38 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG D15000-007 / ISS-7S Soyuz TMA-3 Mass: 7,250 kg (15,980 lb). Spacecraft: Soyuz TMA. Agency: Rosaviakosmos. Perigee: 376 km (233 mi). Apogee: 384 km (238 mi). Inclination: 51.60 deg. Period: 92.20 min. Crew: Foale, Kaleri, Duque. Flight: ISS EO-8, ISS Cervantes, ISS EO-7. The spacecraft carried the Expedition 8 crew of Mike Foale and Aleksandr Kaleri and the EP-5 (Cervantes) mission crewmember Pedro Duque. During the flight to the station spacecraft Commander was Aleksandr Kaleri . Soyuz TMA-3 docked with the Pirs module at 07:16 GMT on October 20. Once the EO-7 crew aboard the ISS was relieved, the roles switched, with Foale becoming the ISS Commander. Duque carried out out 24 experiments in the fields of life and physical sciences, Earth observation, education and technology. The experiments were sponsored by the European Space Agency and Spain. After ten days in space, Duque returned to earth with the EO-7 crew of Malenchenko and Lu aboard Soyuz TMA-2.
2004 January 29 - 11:58 GMT - Launch Vehicle: Soyuz. Soyuz-U D15000-683 Progress M1-11 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M1. Agency: Rosaviakosmos. Perigee: 192 km (119 mi). Apogee: 263 km (163 mi). Inclination: 51.65 deg. Period: 88.73 min. Flight: ISS EO-8. ISS resupply, to dock at the Zvezda module of the station 13:15 GMT on 31 January. Launch delayed from November 20, 2003. Payload delivered amounted to 2345 kg and included a new flex hose for the Destiny module's leaky window, replacement parts for the Russian Elektron oxygen-generating unit, a spare Elektron, new Russian Solid Fuel Oxygen Generator candles, batteries for the Zarya and Zvezda modules, gas analyser equipment, updated fire suppression and detection equipment, a new Russian Orlan spacesuit, film, cameras, data cassettes and the Matreshka experiment package for installation on Zvezda's exterior during a spacewalk.
A few days prior to its departure from the ISS, ground controllers fired the Progress M1-11's engines for 11 minutes, boosting the Station's altitude by 3.7 km and adjusting its inclination by one one-hundredth of a degree. Progress M1-11 undocked from the Station at 11:19 GMT on 24 May 2005, clearing the way for the arrival of Progress M-49. It was thereafter commanded to a destructive re-entry over the Pacific Ocean.
2004 April 19 - 03:19 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG Zh15000-009 Soyuz TMA-4 Mass: 7,250 kg (15,980 lb). Spacecraft: Soyuz TMA. Agency: Rosaviakosmos. Perigee: 359 km (223 mi). Apogee: 367 km (228 mi). Inclination: 51.60 deg. Period: 91.80 min. Crew: Fincke, Padalka, Kuipers. Flight: ISS EO-8, ISS EO-9, ISS Delta. Soyuz TMA-4 was ISS transport mission ISS 8S and delivered the EO-9 caretaker crew of Gennadiy Padalka and Michael Fincke, together with the ESA/Netherlands Delta mission crewmember Andre Kuipers, to the Space Station. Soyuz TMA-4 docked with the nadir port on Zarya at 05:01 GMT on April 21 and the hatches to the ISS were opened at 06:30 GMT. Another gyro on the station had shut down prior to the docking and possibly would require a maintenance spacewalk to replace its failed electronics.
After Soyuz TMA-5 docked with the ISS on October 16, the EO-9 crew handed activities over to the EO-10 crew.
2004 May 25 - 12:34 GMT - Launch Vehicle: Soyuz. Soyuz-U D15000-684 Progress M-49 Mass: 7,283 kg (16,056 lb). Spacecraft: Progress M. Agency: Rosaviakosmos. Perigee: 359 km (223 mi). Apogee: 367 km (228 mi). Inclination: 51.60 deg. Period: 91.80 min. Flight: ISS EO-9. Docked at the aft port of the Zvezda Service Module of the International Space Station on 27 May at 13:55 GMT. Delivered two and a half tons of food, water, fuel, spare parts and supplies. Progress M-49 undocked from the Zvezda module on 30 July 2004 at 7:05 GMT, after having been filled with a tonne of trash. Fincke filmed its departure, and Station exterior cameras captured rare footage of the Progress' fiery re-entry into Earth's atmosphere after it was deorbited.
2004 August 11 - 05:01 GMT - Launch Vehicle: Soyuz. Soyuz-U D15000-685 Progress M-50 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: RKA. Perigee: 358 km (222 mi). Apogee: 365 km (226 mi). Inclination: 51.60 deg. Period: 91.80 min. Flight: ISS EO-9. Delayed from July 22 and 28. Docked with the International Space Station at 05:01 GMT on August 14. Undocked from the Zvezda module of the ISS on December 22 at 19:34 GMT and was deorbited over the Pacific at 22:32 GMT.
2004 October 14 - 03:06 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG Zh15000-012 Soyuz TMA-5 Mass: 7,250 kg (15,980 lb). Spacecraft: Soyuz TMA. Perigee: 353 km (219 mi). Apogee: 359 km (223 mi). Inclination: 51.60 deg. Period: 91.70 min. Crew: Chiao, Sharipov, Shargin. Flight: ISS EO-10. Soyuz TMA-5 docked with the Pirs module on October 16 at 0416 GMT. Aboard the spacecraft were the EO-10 crew of Sharipov and Chiao, and guest cosmonaut Shargin. After a week at the station, the EO-9 crew of Padalka and Fincke, together with Shargin, entered Soyuz TMA-4 at 18:14 GMT on October 23 and returned to earth. Chiao and Sharipov continued as the ISS skeleton station crew.
2004 December 23 - 22:19 GMT - Launch Vehicle: Soyuz. Soyuz-U Zh15000-092 / ISS-16P Progress M-51 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: RKA. Perigee: 316 km (196 mi). Apogee: 355 km (220 mi). Inclination: 51.60 deg. Period: 91.20 min. Flight: ISS EO-10. Launch delayed from November 24, December 22 . Progress M-51 docked with the Zvezda module of the International Space Station on December 25 at 23:58 GMT, bringing critical food supplies to the EO-10 crew. Press hype during the delays prior to the launch had portrayed the situation as one where failure of the Progress to dock would have required the crew to either return to earth or starve.
Undocked from at 16:06 GMT on February 27, 2005, in order to clear the port for Progress M-52, which would launch the next day. Progress M-51 lowered its perigee at around 18:30 GMT and remained in orbit for several days. FInally an engine firing was commanded, bringing it down in a destructive re-entry over the Pacific Ocean on March 9.
2005 February 28 - 19:09 GMT - Launch Vehicle: Soyuz. Soyuz-U Zh15000-093 / ISS-17P Progress M-52 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: Russian Space Agency. Perigee: 350 km (210 mi). Apogee: 360 km (220 mi). Inclination: 51.60 deg. Period: 91.60 min. Flight: ISS EO-10. Docked with the Zvezda module of the International Space Station at 20:10 GMT on March 2. Undocked at 20:16 GMT on 15 June. Retrofire at 23:16 GMT lowered its perigee to 62 km, and resulting in a destructive re-entry over the Pacific at 23:57 GMT.
2005 April 15 - 00:45 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG Zh15000-014 / ISS-10S Soyuz TMA-6 Mass: 7,250 kg (15,980 lb). Spacecraft: Soyuz TMA. Perigee: 350 km (210 mi). Apogee: 360 km (220 mi). Inclination: 51.60 deg. Period: 91.60 min. Crew: Krikalyov, Phillips, Vittori. Flight: ISS EO-11, ISS EP-8, ISS EO-10. The Soyuz TMA-6 docked with International Space Station's Pirs module at 02:20 GMT on April 17. Commander of the long-duration EO-11 crew was Russian cosmonaut Sergey Krikalyov. Flight engineer and science officer was American astronaut John Phillips. Italian Roberto Vittori accompanied the EO-10 crew aboard Soyuz TMA-6 to the station on the European Space Agency EP-8 Eneide mission.
2005 May 31 - 12:00 GMT - Launch Vehicle: Soyuz. Soyuz-U Zh15000-091 Foton M-2 Mass: 6,535 kg (14,407 lb). Spacecraft: Foton. Agency: Roskosmos. Perigee: 262 km (162 mi). Apogee: 304 km (188 mi). Inclination: 63.00 deg. Period: 89.93 min. Microgravity mission with the experiments being returned to earth after 16 days in a spherical Vostok capsule of the type that first carried Yuri Gagarin into space in 1961. The capsule landed in Kazakhstan at 07:36 GMT on 16 June. For this mission a 385 kg European payload of 39 experiments in fluid physics, biology, material science, meteoritics, radiation dosimetry and exobiology was carried. A further 215 kg of Russian instruments were also flown. Many were experiments were being reflown following loss of Foton-M1 on 15 October 2002. The planned Fotino miniature re-entry capsule experiment was not flown.
Applied research included heat transfer experiments with the European FluidPac facility, chemical diffusion experiments in the SCCO (Soret Coefficients in Crude Oil), and material science investigations in the Agat and Polizon furnaces. These experiments were expected to contribute to new heat-exchanger designs, more efficient oil exploration processes, and better semiconductor alloys. The Biopan facility carried life science experiments, including a student seed germination test.
2005 June 16 - 23:10 GMT - Launch Vehicle: Soyuz. Soyuz-U Zh15000-094 / ISS-18P Progress M-53 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: Roskosmos. Perigee: 350 km (210 mi). Apogee: 353 km (219 mi). Inclination: 51.60 deg. Period: 91.60 min. Flight: ISS EO-11. Delayed from June 10. Space station resupply mission. After a communications failure, ISS Commander Krikalyov took manual remote control used the TORU system to guide Progress M-53 to a docking at the ISS Zvezda module at 00:42 GMT on 19 June. Undocked at 10:26 GMT on 7 September into a 350 km x 351 km orbit. Progress M-53 began retrofire at 13:26 GMT the same day, lowering its perigee to 56 km and thereby ensuring a destructive re-entry into the Pacific Ocean.
2005 September 8 - 13:08 GMT - Launch Vehicle: Soyuz. Soyuz-U P15000-095 / ISS-19P Progress M-54 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: RKA. Perigee: 347 km (215 mi). Apogee: 348 km (216 mi). Inclination: 51.60 deg. Period: 91.50 min. Flight: ISS EO-11. Delayed from August 24. Resupply spacecraft which docked with the ISS Zvezda module at 14:42 GMT on 10 September. Undocked from the Zvezda module on March 3 2006 at 10:06 GMT and fired its engines to reenter over the Pacific at 13:05 GMT.
2005 October 1 - 03:54 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG Zh15000-017 / ISS-11S Soyuz TMA-7 Mass: 7,250 kg (15,980 lb). Spacecraft: Soyuz TMA. Agency: Roskosmos, NASA , Space Adentures. Perigee: 347 km (215 mi). Apogee: 348 km (216 mi). Inclination: 51.60 deg. Period: 91.50 min. Crew: Tokarev, McArthur, Olsen. Flight: ISS EO-11, ISS EO-12, ISS EP-10. Launch delayed from September 27. Soyuz TMA-7 docked with the International Space Station at 05:27 GMT on 3 October, bringing the long duration EO-12 crew of (McArthur, Commander; Tokarev, Flight Engineer) and space tourist Olsen. McArthur, Tokarev and Pontes (brought to the station aboard Soyuz TMA-8) transferred to TMA-7 on April 8, 2006, closing the hatches at 17:15 GMT and undocking from Zvezda at 20:28 GMT, leaving Vinogradov and Williams from Soyuz TMA-8 as the Expedition 13 in charge of the station. Soyuz TMA-7 fired its engines at 22:58 GMT for the deorbit burn and landed in Kazakhstan at 23:48 GMT.
2005 December 21 - 18:38 GMT - Launch Vehicle: Soyuz. Soyuz-U F15000-080 / ISS-20P Progress M-55 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: Roskosmos. Perigee: 336 km (208 mi). Apogee: 349 km (216 mi). Inclination: 51.60 deg. Period: 91.40 min. Flight: ISS EO-12. The resupply spacecraft docked with the ISS Pirs module at 19:46 GMT on 23 December. It undocked at 14:06 GMT on June 19, 2006; fired its engines at 17:06 GMT to lower its orbit into the atmosphere; and burned up over the Pacific Ocean at 17:41 GMT.
2006 March 30 - 02:30 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG P15000-018 Soyuz TMA-8 Mass: 7,250 kg (15,980 lb). Spacecraft: Soyuz TMA. Agency: Roskosmos, NASA. Perigee: 336 km (208 mi). Apogee: 349 km (216 mi). Inclination: 51.60 deg. Period: 91.40 min. Crew: Vinogradov, Williams Jeffrey, Pontes. Flight: ISS EO-13, ISS EO-12, ISS EP-10. Soyuz TMA-8 docked with the Zarya nadir port of the ISS at 04:19 GMT on April 1. It undocked from Zarya on 28 September at 21:53 GMT, with the return crew of Vinogradov, Williams and space tourist Ansari aboard. It landed in Kazakhstan at 01:13 GMT on 29 September.
2006 April 24 - 16:03 GMT - Launch Vehicle: Soyuz. Soyuz-U P15000-100 / ISS-21P Progress M-56 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: Roskosmos. Perigee: 336 km (208 mi). Apogee: 349 km (216 mi). Inclination: 51.60 deg. Period: 91.40 min. Flight: ISS EO-13. Progress M-56 docked at the Zvezda port of the International Space Station on 26 April at 17:41 GMT. It undocked at 00:28 GMT on 29 September and was then commanded to a destructive reentry over the south Pacific Ocean.
2006 June 15 - 08:00 GMT - Launch Vehicle: Soyuz. Soyuz-U 096 Resurs DK-1 Mass: 7,250 kg (15,980 lb). Spacecraft: Yantar-4KS1. Agency: Roskosmos. Perigee: 355 km (220 mi). Apogee: 585 km (363 mi). Inclination: 69.90 deg. Period: 94.00 min. Civilian remote sensing satellite with a one-meter-resolution-class Geoton-1 camera payload.that relayed its data to the ground via a digital link. It was based on the Terilen/Neman class military reconnaissance satellite in use since the 1980s, using the Yantar satellite bus.
2006 June 24 - Launch Vehicle: Soyuz. Soyuz-U Zh15000-101 / ISS-22P Progress M-57 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: Roskosmos. Perigee: 335 km (208 mi). Apogee: 349 km (216 mi). Inclination: 51.60 deg. Period: 91.30 min. Flight: ISS EO-13. The Progress flew International Space Station resupply mission 22P (NASA called the flight Progress 22). It docked at the ISS Pirs port at 16:25 GMT on June 26.
2006 September 18 - 04:08 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG Ts15000-023 Soyuz TMA-9 Mass: 7,250 kg (15,980 lb). Spacecraft: Soyuz TMA. Agency: Roskosmos. Perigee: 330 km (200 mi). Apogee: 348 km (216 mi). Inclination: 51.60 deg. Period: 91.30 min. Crew: Tyurin, Lopez-Alegria, Ansari. Flight: ISS EO-14, ISS EO-13. Carried the Expedition 14 crew and space tourist Anousheh Ansari to the International Space Station. Ansari replaced tourist Daisuke Enomoto, who was removed from flight status by the Russians just 28 days before the flight. Docked at the Zvezda port of the station at 05:21 GMT on September 20. On 21 April 2007, Lopez-Alegria, Tyurin and space tourist Charles Simonyi (who was taken to the station aboard Soyuz TMA-10) boarded Soyuz TMA-9, separated from the ISS, conducted retrofire, and landed in Kazakhstan at 12:31 GMT.
2006 October 23 - 13:40 GMT - Launch Vehicle: Soyuz. Soyuz-U Ts15000-102 / ISS-23P Progress M-58 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: Roskosmos. Perigee: 321 km (199 mi). Apogee: 351 km (218 mi). Inclination: 51.60 deg. Period: 91.30 min. Flight: ISS EO-13. The Progress docked with the Zvezda module of the ISS at 14:29 GMT on October 26. There were indications that the Kurs rendezvous antenna on the forward docking ring had not retracted correctly, but this proved not to be the case. Hard dock was commanded at 18:06 GMT. Progress M-58 undocked from the Zvezda module on 27 March 2007 at 18:11 GMT and was deorbited at 22:44 GMT.
2007 January 18 - 02:12 GMT - Launch Vehicle: Soyuz. Soyuz-U Zh15000-107 / ISS-24P Progress M-59 Mass: 7,250 kg (15,980 lb). Spacecraft: Progress M. Agency: Roskosmos. Perigee: 321 km (199 mi). Apogee: 351 km (218 mi). Inclination: 51.60 deg. Period: 91.30 min. Flight: ISS EO-14, ISS EO-14-1. Progress docked to the Pirs port of the ISS at 01:59 GMT on 20 January. The cargo craft brought up 780 kg of propellant for the Russian thrusters, 50 kg of oxygen and 1500 kg of spare parts, experiment hardware and life support components.
2007 April 7 - 17:31 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG 019 Soyuz TMA-10 Mass: 7,200 kg (15,800 lb). Spacecraft: Soyuz TMA. Agency: Roskosmos. Perigee: 330 km (200 mi). Apogee: 341 km (211 mi). Inclination: 51.60 deg. Period: 91.20 min. Crew: Yurchikhin, Kotov, Simonyi. Flight: ISS EO-15, ISS EP-12. Carried the Expedition 15 crew and space tourist Charles Simonyi to the International Space Station. Soyuz TMA-10 docked at the Zarya port of the International Space Station at 19:10 GMT on 9 April. It undocked from Zarya at 19:20 GMT on Sep 27 September and docked at the Zvezda port at 19:47 GMT to clear Zarya for Soyuz TMA-10.
The EO-15 crew and EP-13 space tourist Shukor (brought to the station by Soyuz TMA-11) boarded Soyuz TM-10 and undocked from the Zvezda port at 07:14 GMT on 21 October. The re-entry burn began at 09:47 and was normal. But afterwards, due to failure of an explosive bolt, the Soyuz service module remained connected to the re-entry capsule. The Soyuz tumbled, then began re-entry with the forward hatch taking the re-entry heating, until the connecting strut burned through. The Soyuz the righted itself with the heat shield taking the heating, but defaulted to an 8.6 G ballistic re-entry, landing 340 km short of the aim point at 10:36 GMT. Improved procedures after the ballistic re-entry of Soyuz TMA-1 meant a helicopter recovery crew reached the capsule only 20 minutes after thumpdown. However the true nature of the failure was concealed from the world until the same thing happened on Soyuz TMA-11.
2007 May 12 - 03:25 GMT - Launch Vehicle: Soyuz. Soyuz-U Ts15000-104 / ISS-25P Progress M-60 Mass: 7,280 kg (16,040 lb). Spacecraft: Progress M. Agency: Roskosmos. Perigee: 330 km (200 mi). Apogee: 341 km (211 mi). Inclination: 51.60 deg. Period: 91.20 min. Flight: ISS EO-15, ISS EO-14-1. Space station resupply spacecraft which docked with the Zvezda port of the International Space Station at 05:10 GMT on 15 May. It undocked on 19 September was conducted plasma depletion experiments before being deorbited over the Pacific at 19:01 GMT on 25 September..
2007 August 2 - 17:33 GMT - Launch Vehicle: Soyuz. Soyuz-U Sh15000-108 / ISS-26P Progress M-61 Spacecraft: Progress M. Agency: Roskosmos. Perigee: 334 km (207 mi). Apogee: 346 km (214 mi). Inclination: 51.60 deg. Period: 91.30 min. International space station resupply; docked with the Pirs module at 18:40 GMT on 5 August. Undocked at 03:59 GMT on 22 December to clear port for Progress M-62 launched the next day. Deorbited over the Pacific on 22 January 2008 after a month of free flight carrying out the Plazma-Progress experiment.
2007 September 14 - 11:00 GMT - Launch Vehicle: Soyuz. Soyuz-U 098 Foton M-3 Spacecraft: Foton. Agency: Roskosmos. Perigee: 258 km (160 mi). Apogee: 280 km (170 mi). Inclination: 62.90 deg. Period: 89.90 min. Recoverable spacecraft derived from the Vostok. Carried Russian and European microgravy, life sciences and technology experiments. After deploying the YES-2 tether on 25 September, Foton M-3 was deorbited at 07:23 GMT on 26 September and successfully landed at 07:58 GMT in Kazakhstan.
2007 October 10 - 13:22 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz FG . Soyuz-FG Ts15000-020 Soyuz TMA-11 Mass: 7,200 kg (15,800 lb). Spacecraft: Soyuz TMA. Perigee: 340 km (210 mi). Apogee: 344 km (213 mi). Inclination: 51.60 deg. Period: 91.40 min. Crew: Whitson, Malenchenko, Muszaphar. Flight: ISS EO-16, ISS EP-13. Soyuz TMA-11 delivered the EO-16 crew of Whitson and Malenchenko and EP-13 space tourist Shukor to the International Space Station. The Soyuz docked at the Zarya module at 14:50 GMT on 12 October. Whitson was EO-16 commander, with third astronaut Clay Anderson remaining aboard the station after the EO-15 crew and Shukor returned to earth on Soyuz TMA-10.
Malenchenko and Whitson, together with visiting Korean astronaut Yi, who had been delivered to the ISS by Soyuz TMA-12, undocked from the station aboard Soyuz TMA-11 at 05:06 GMT on 19 April 2008. Following the deorbit burn at 07:40 GMT the aft service module of the Soyuz failed to separate and the spacecraft began re-entry in a reversed position, with the forward hatch taking the initial re-entry heating. As was the case with Soyuz 5 in 1970, the connections with the service module finally melted away, and the freed capsule righted itself aerodynamically with the heat shield taking the brunt of the re-entry heating. However the crew experienced a rough ride, a ballistic re-entry of over 8 G's force, smoke in the cabin, a failure of the soft landing system, and a very hard landing. They landed 470 km short of the target point at 50 deg 31" N, 61 deg 7" E at 08:29 GMT. A small grass fire was started at the landing point and the injured crew had to be helped from the capsule by passers-by. Malenchenko and Whitson suffered no permanent injury, but Yi was hit by Whitson's personal effects bag on impact and required physical therapy for neck and spine injuries.
2007 December 23 - 07:12 GMT - Launch Vehicle: Soyuz. LV Model: Soyuz-U . ISS-27P Progress M-62 Spacecraft: Progress M. Agency: Roskosmos. Perigee: 333 km (206 mi). Apogee: 341 km (211 mi). Inclination: 51.60 deg. Period: 91.30 min. Flight: ISS EO-16. Resupply spacecraft that docked with the Pirs port of the International Space Station at 08:14 GMT on 26 December. Undocked on 4 February 2008 at 10:32 GMT and then carried out Earth observations for ten days before being deorbited on 15 February at 09:44 GMT.
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