1974 July 4 - Launch Vehicle: R-36M. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 August 30 - Launch Vehicle: R-36M. Missile accuracy test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 October 23 - Launch Vehicle: R-36M. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1974 December 25 - Launch Vehicle: R-36M. State trials missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 February 26 - Launch Vehicle: R-36M. Missile accuracy test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 June 7 - Launch Vehicle: R-36M. SLI? Agency: RVSN. Apogee: 1,000 km (600 mi).

1975 August 26 - Launch Vehicle: R-36M. Missile accuracy test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1976 September 3 - Launch Vehicle: R-36M. Missile accuracy test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 May 17 - Launch Vehicle: R-36M. Missile accuracy test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 November 29 - Launch Vehicle: R-36M. Missile accuracy test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1977 December 30 - Launch Vehicle: R-36M. Missile accuracy test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1978 February 11 - Launch Vehicle: R-36M. Missile accuracy test launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1978 June 14 - Launch Vehicle: R-36M. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1980 March 6 - Launch Vehicle: R-36M. DP Agency: RVSN. Apogee: 1,000 km (600 mi).

1980 July 4 - Launch Vehicle: R-36M. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1982 July 15 - Launch Vehicle: R-36M. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1982 December 23 - Launch Vehicle: R-36M. Operational missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1983 July 14 - Launch Vehicle: R-36M. Joint flight trials launch Agency: RVSN. Apogee: 1,000 km (600 mi).

1983 October 11 - Launch Vehicle: R-36M. SLI missile test Agency: RVSN. Apogee: 1,000 km (600 mi).

1999 April 21 - 04:59 GMT - Launch Vehicle: R-36M. Dnepr 6703542509 UoSAT-12 Mass: 325 kg (716 lb). Spacecraft: MiniSat-400. Agency: SSTL. Perigee: 639 km (397 mi). Apogee: 654 km (406 mi). Inclination: 64.60 deg. Period: 97.70 min. First launch of Russia's Dnepr launch vehicle, a converted R-36M2 ICBM. The Dnepr was launched from a silo. The third stage maneuvring bus (used on the ICBM for dispensing multiple warheads) placed UoSAT-12 into a 638 km x 652 km x 64.6 deg orbit. The third stage separated from the payload at 05:13 GMT and then made a burn into a 599 km x 1403 km x 64.6 deg orbit. UoSAT-12 was the first test of the Minibus platform, at 325 kg a larger spacecraft than earlier 50 kg Surrey UoSATs. It carried a mobile radio experiment (MERLION), a GPS receiver, and imaging cameras.

2000 September 26 - 10:05 GMT - Launch Vehicle: R-36M. Tiungsat-1 Mass: 50 kg (110 lb). Spacecraft: MicroSat-70. Agency: BKSA. Perigee: 644 km (400 mi). Apogee: 658 km (409 mi). Inclination: 64.56 deg. Period: 97.67 min. Launch delayed from August 25/26. Customer: Astonautic Technology (M) SDN. BHD. Malaysia's first microsatellite built through a technology transfer programme with Surrey Satellite Technology Ltd Carried multi-spectral Earth imaging CCD cameras, meteorological Earth imaging CCD camera, digital store and forward communications, cosmic-ray energy deposition experiment (CEDEX)

2002 December 20 - 17:00 GMT - Launch Vehicle: R-36M. LatinSat 1 Mass: 12 kg (26 lb). Spacecraft: AprizeSat. Agency: Aprize Satellite. Perigee: 635 km (394 mi). Apogee: 679 km (421 mi). Inclination: 64.60 deg. Period: 97.90 min. Messaging satellite.

2004 June 29 - 06:30 GMT - Launch Vehicle: R-36M. Aprizesat 2 (LatinSat D) Mass: 12 kg (26 lb). Spacecraft: AprizeSat. Agency: Aprize Satellite. Perigee: 695 km (431 mi). Apogee: 853 km (530 mi). Inclination: 98.30 deg. Period: 100.30 min. Delayed from March. 31

2005 August 23 - 21:10 GMT - Launch Vehicle: R-36M. Kirari Mass: 570 kg (1,250 lb). Spacecraft: Kirari. Agency: JAXA. Perigee: 596 km (370 mi). Apogee: 614 km (381 mi). Inclination: 97.80 deg. Period: 96.80 min. Moved from J-1A . Delayed from August 15. Optical Inter-Orbit Communications Engineering Test Satellite. Its laser communications experiment was be used in with ESA's Artemis geostationary satellite. The satellite was renamed Kirari (twinkle) after launch.

2006 July 26 - 19:43 GMT - Launch Vehicle: R-36M. Dnepr 804 (4502973804) FAILURE: First stage engine failed. BelKA, Baumanets, Unisat 4, PicPot, and 9 nanosats Mass: 360 kg (790 lb). Agency: Belarus National Academy of Sciences. Payload consisted of 19 nanosats from academic institutions: BelKA; Baumanets; Unisat-4; PICPOT; ICECube-1; ION; RINCON; AeroCube-1; CalPoly CP1; SEEDS; nCube-1; HAUSAT-1; MEROPE; CalPoly CP2; KUTESat; SACRED; Voyager; ICECube 3

2007 April 17 - 06:46 GMT - Launch Vehicle: R-36M. Dnepr 806 MisrSat 1 Mass: 100 kg (220 lb). Spacecraft: MS-1. Agency: NARSSS. Perigee: 657 km (408 mi). Apogee: 667 km (414 mi). Inclination: 98.10 deg. Period: 98.00 min. MisrSat/Egyptsat carried an imaging payload for Egypt's National Authority for Remote Sensing and Space Sciences.