1959 December 21 - Launch Vehicle: Kosmos 2. Test mission Agency: MVS. Apogee: 402 km (249 mi).

1959 December 27 - Launch Vehicle: Kosmos 2. Test mission Agency: MVS. Apogee: 402 km (249 mi).

1961 October 27 - 16:30 GMT - Launch Vehicle: Kosmos 2. FAILURE: First stage failed. DS-2 s/n 1 Mass: 300 kg (660 lb). Spacecraft: DS-1. Agency: RVSN. Failed first attempt to launch a DS-1 technology test version of the DS satellite atop a Cosmos 63S1 small launch vehicle. The boster didn't reach orbital velocity due to the failure of an acceleration integrator in the velocity regulation control.

1961 December 21 - 12:30 GMT - Launch Vehicle: Kosmos 2. FAILURE: Second stage failed 354 seconds after launch. DS-1 s/n 1 Mass: 300 kg (660 lb). Spacecraft: DS-1. Agency: RVSN. Second attempted launch of Cosmos 63S1 small launch vehicle 2LK with a DS-1 satgellite. This time the new second stage failed. The oxidiser was exhausted before orbital velocity could be reached due to uncontrolled pumping of liquid oxygen into the combustion chamber. The upper stage and satellite impacted in the Kurile Islands. An Expert Commission headed by Ustinov was convened to review the program.

1962 March 16 - 11:59 GMT - Launch Vehicle: Kosmos 2. Kosmos 63S1 6LK Cosmos 1 Mass: 47 kg (103 lb). Spacecraft: DS-2. Agency: RVSN. Perigee: 207 km (128 mi). Apogee: 649 km (403 mi). Inclination: 49.00 deg. Period: 93.10 min. After five months of further work and tests to improve the reliability of the second stage, Yangel's team felt it was ready to again attempt a launch of the 63S1 booster. 63S1 s/n 6LK put a DS-2 satellite into orbit, which conducted studies of the ionosphere. This was the first successful launch of the Kosmos 63S1 launch vehicle. A decision was made after two unsuccessful launches of the DS-1 to create a simplified DS-2 spacecraft based on the equipment and structural elements of DS-1 spacecraft. The cylindrical section for mission avionics was completely omitted.

1962 April 6 - 17:15 GMT - Launch Vehicle: Kosmos 2. Kosmos 63S1 5LK Cosmos 2 Mass: 285 kg (628 lb). Spacecraft: 1MS. Agency: RVSN. Perigee: 207 km (128 mi). Apogee: 1,485 km (922 mi). Inclination: 49.00 deg. Period: 101.80 min. Radiation, cosmic ray data. Decay date suspect Investigation of the upper atmosphere and outer space; development of elements in the design of space craft.

1962 April 24 - 04:00 GMT - Launch Vehicle: Kosmos 2. Kosmos 63S1 4LK Cosmos 3 Mass: 330 kg (720 lb). Spacecraft: 2MS. Agency: RVSN. Perigee: 216 km (134 mi). Apogee: 707 km (439 mi). Inclination: 49.00 deg. Period: 93.80 min. Cosmic ray, radiation data. Investigation of the upper atmosphere and outer space; development of elements in the design of space craft.

1962 May 28 - 03:00 GMT - Launch Vehicle: Kosmos 2. Kosmos 63S1 3LK Cosmos 5 Mass: 280 kg (610 lb). Spacecraft: 2MS. Agency: RVSN. Perigee: 192 km (119 mi). Apogee: 1,578 km (980 mi). Inclination: 49.10 deg. Period: 102.60 min. Monitored artificial radiation. Investigation of the upper atmosphere and outer space; development of elements in the design of space craft.

1962 June 30 - 16:00 GMT - Launch Vehicle: Kosmos 2. Cosmos 6 Mass: 355 kg (782 lb). Spacecraft: DS-P1. Agency: RVSN. Perigee: 261 km (162 mi). Apogee: 348 km (216 mi). Inclination: 48.90 deg. Period: 90.60 min. Prototype ABM radar target; supported developmental experiments for ABM systems.

1962 August 18 - 15:00 GMT - Launch Vehicle: Kosmos 2. Cosmos 8 Mass: 337 kg (742 lb). Spacecraft: DS-K-8. Agency: RVSN. Perigee: 244 km (151 mi). Apogee: 598 km (371 mi). Inclination: 49.00 deg. Period: 92.90 min. Detected meteoroid flux in near-earth space and carried unspecified military research equipment.

1962 October 20 - 04:00 GMT - Launch Vehicle: Kosmos 2. Cosmos 11 Mass: 315 kg (694 lb). Spacecraft: DS-A1. Agency: RVSN. Perigee: 240 km (140 mi). Apogee: 858 km (533 mi). Inclination: 48.90 deg. Period: 95.60 min. Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.

1962 October 25 - Launch Vehicle: Kosmos 2. FAILURE: Launch vehicle failed to orbit - unknown cause. 1MS Spacecraft: 1MS. Agency: RVSN.

1963 April 6 - Launch Vehicle: Kosmos 2. FAILURE: First stage failed. DS-P1 s/n 2 Spacecraft: DS-P1. Agency: RVSN. Prototype ABM radar target; supported developmental experiments for ABM systems.

1963 April 13 - 11:00 GMT - Launch Vehicle: Kosmos 2. Cosmos 14 Spacecraft: Omega. Agency: MO SSSR. Perigee: 250 km (150 mi). Apogee: 410 km (250 mi). Inclination: 48.90 deg. Period: 91.10 min. Tested VNIIEM electric gyrodyne satellite orientation technology.

1963 May 22 - 03:00 GMT - Launch Vehicle: Kosmos 2. Cosmos 17 Mass: 322 kg (709 lb). Spacecraft: DS-A1. Agency: MO SSSR. Perigee: 251 km (155 mi). Apogee: 658 km (408 mi). Inclination: 48.90 deg. Period: 93.70 min. Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.

1963 June 1 - 02:50 GMT - Launch Vehicle: Kosmos 2. FAILURE: First stage failed 4 seconds after launch. DS-MT s/n 1 Spacecraft: DS-MT. Agency: RVSN. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays.

1963 August 6 - 06:00 GMT - Launch Vehicle: Kosmos 2. Cosmos 19 Mass: 355 kg (782 lb). Spacecraft: DS-P1. Agency: MO SSSR. Perigee: 267 km (165 mi). Apogee: 497 km (308 mi). Inclination: 49.00 deg. Period: 92.10 min. Prototype ABM radar target; supported developmental experiments for ABM systems.

1963 August 22 - Launch Vehicle: Kosmos 2. FAILURE: First stage failed. DS-A1 s/n 3 Spacecraft: DS-A1. Agency: RVSN. Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.

1963 October 24 - Launch Vehicle: Kosmos 2. FAILURE: Second stage failed 353 seconds after launch. DS-A1 s/n 4 Spacecraft: DS-A1. Agency: RVSN. Carried military experiments to test communications and navigation equipment needed for command and control of Soviet nuclear forces (later used on the Uragan navigation satellites). Also conducted operational monitoring of cosmic rays, radiation from nuclear tests, and natural and artifically-produced radiation belts.

1963 December 13 - 14:15 GMT - Launch Vehicle: Kosmos 2. Cosmos 23 Mass: 347 kg (765 lb). Spacecraft: Omega. Agency: MO SSSR. Perigee: 232 km (144 mi). Apogee: 560 km (340 mi). Inclination: 48.90 deg. Period: 92.40 min. Tested VNIIEM electric gyrodyne satellite orientation technology.

1964 February 27 - 13:26 GMT - Launch Vehicle: Kosmos 2. Cosmos 25 Mass: 355 kg (782 lb). Spacecraft: DS-P1. Agency: MO SSSR. Perigee: 260 km (160 mi). Apogee: 495 km (307 mi). Inclination: 49.10 deg. Period: 92.10 min. Prototype ABM radar target; supported developmental experiments for ABM systems.

1964 March 18 - 15:07 GMT - Launch Vehicle: Kosmos 2. Cosmos 26 Mass: 365 kg (804 lb). Spacecraft: DS-MG. Agency: MO SSSR. Perigee: 268 km (166 mi). Apogee: 376 km (233 mi). Inclination: 48.90 deg. Period: 91.00 min. Payload developed by VNIIEM to test electric gyrodyne orientation systems. Also obtained radiation data.

1964 June 6 - 06:00 GMT - Launch Vehicle: Kosmos 2. Cosmos 31 Mass: 325 kg (716 lb). Spacecraft: DS-MT. Agency: MO SSSR. Perigee: 221 km (137 mi). Apogee: 485 km (301 mi). Inclination: 48.90 deg. Period: 91.70 min. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays.

1964 July 30 - 03:36 GMT - Launch Vehicle: Kosmos 2. Cosmos 36 Mass: 325 kg (716 lb). Spacecraft: DS-P1-Yu. Agency: MO SSSR. Perigee: 253 km (157 mi). Apogee: 488 km (303 mi). Inclination: 49.00 deg. Period: 92.00 min. Development of systems for air defence and the control of outer space.

1964 August 22 - 11:02 GMT - Launch Vehicle: Kosmos 2. Cosmos 42 Mass: 100 kg (220 lb). Spacecraft: Strela-1. Agency: MO SSSR. Perigee: 228 km (141 mi). Apogee: 1,105 km (686 mi). Inclination: 48.90 deg. Period: 98.10 min.