1964 December 1 - Launch Vehicle: Kosmos 2. FAILURE: Payload shroud did not separate. DS-2 s/n 2 Spacecraft: DS-2. Agency: RVSN. 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.

1964 December 9 - 23:02 GMT - Launch Vehicle: Kosmos 2. Cosmos 51 Mass: 350 kg (770 lb). Spacecraft: DS-MT. Agency: MO SSSR. Perigee: 258 km (160 mi). Apogee: 537 km (333 mi). Inclination: 48.80 deg. Period: 92.60 min. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays, and measured the luminosity of the starry sky.

1965 January 30 - 09:36 GMT - Launch Vehicle: Kosmos 2. Cosmos 53 Mass: 310 kg (680 lb). Spacecraft: DS-A1. Agency: MO SSSR. Perigee: 221 km (137 mi). Apogee: 1,172 km (728 mi). Inclination: 48.70 deg. Period: 98.70 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.

1965 February 12 - Launch Vehicle: Kosmos 2. FAILURE: Second stage failed. DS-P1-Yu s/n 2 Spacecraft: DS-P1-Yu. Agency: RVSN. Development of systems for air defence and the control of outer space.

1965 February 20 - Launch Vehicle: Kosmos 2. FAILURE: First stage failed 64 seconds after launch. DS-A1 s/n 6 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.

1965 July 2 - 06:30 GMT - Launch Vehicle: Kosmos 2. Cosmos 70 Mass: 250 kg (550 lb). Spacecraft: DS-A1. Agency: MO SSSR. Perigee: 223 km (138 mi). Apogee: 1,176 km (730 mi). Inclination: 48.80 deg. Period: 98.80 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.

1965 July 23 - 04:33 GMT - Launch Vehicle: Kosmos 2. Cosmos 76 Mass: 325 kg (716 lb). Spacecraft: DS-P1-Yu. Agency: MO SSSR. Perigee: 256 km (159 mi). Apogee: 513 km (318 mi). Inclination: 48.80 deg. Period: 92.20 min. Development of systems for air defence and the control of outer space.

1965 October 19 - 05:44 GMT - Launch Vehicle: Kosmos 2. Cosmos 93 Mass: 305 kg (672 lb). Spacecraft: DS-U2-V. Agency: MO SSSR. Perigee: 216 km (134 mi). Apogee: 513 km (318 mi). Inclination: 48.40 deg. Period: 91.80 min. Military technology development satellite - mission still classified.

1965 November 4 - 05:31 GMT - Launch Vehicle: Kosmos 2. Cosmos 95 Mass: 325 kg (716 lb). Spacecraft: DS-U2-V. Agency: MO SSSR. Perigee: 211 km (131 mi). Apogee: 521 km (323 mi). Inclination: 48.40 deg. Period: 91.90 min. Military technology development satellite - mission still classified.

1965 November 26 - 12:14 GMT - Launch Vehicle: Kosmos 2. Cosmos 97 Mass: 267 kg (588 lb). Spacecraft: DS-U2-M. Agency: MO SSSR. Perigee: 214 km (132 mi). Apogee: 2,144 km (1,332 mi). Inclination: 48.40 deg. Period: 108.90 min. Development tests of atomic clocks.

1965 December 21 - 06:14 GMT - Launch Vehicle: Kosmos 2. Cosmos 101 Mass: 325 kg (716 lb). Spacecraft: DS-P1-Yu. Agency: MO SSSR. Perigee: 256 km (159 mi). Apogee: 533 km (331 mi). Inclination: 48.80 deg. Period: 92.50 min. Development of systems for air defence and the control of outer space.

1965 December 28 - Launch Vehicle: Kosmos 2. FAILURE: First stage failed. DS-K-40 s/n 1 Spacecraft: DS-K-40. Agency: RVSN. Development of systems for the later operational Tselina satellites.

1966 January 25 - 12:28 GMT - Launch Vehicle: Kosmos 2. Cosmos 106 Mass: 325 kg (716 lb). Spacecraft: DS-P1-I. Agency: MO SSSR. Perigee: 281 km (174 mi). Apogee: 553 km (343 mi). Inclination: 48.40 deg. Period: 92.80 min. Operational radar target for the ABM forces.

1966 February 11 - 18:00 GMT - Launch Vehicle: Kosmos 2. Cosmos 108 Mass: 355 kg (782 lb). Spacecraft: DS-U1-G. Agency: MO SSSR. Perigee: 220 km (130 mi). Apogee: 850 km (520 mi). Inclination: 48.80 deg. Period: 95.30 min. Studied the relationship between variations in the upper atmosphere and solar activity.

1966 February 21 - Launch Vehicle: Kosmos 2. FAILURE: First stage failed 83 seconds after launch. DS-K-40 s/n 2 Spacecraft: DS-K-40. Agency: RVSN. Development of systems for the later operational Tselina satellites.

1966 April 26 - 10:04 GMT - Launch Vehicle: Kosmos 2. Cosmos 116 Mass: 325 kg (716 lb). Spacecraft: DS-P1-Yu. Agency: MO SSSR. Perigee: 288 km (178 mi). Apogee: 464 km (288 mi). Inclination: 48.40 deg. Period: 92.00 min. Development of systems for air defence and the control of outer space.

1966 May 24 - 05:31 GMT - Launch Vehicle: Kosmos 2. Cosmos 119 Mass: 250 kg (550 lb). Spacecraft: DS-U2-I. Agency: MO SSSR. Perigee: 209 km (129 mi). Apogee: 1,278 km (794 mi). Inclination: 48.40 deg. Period: 99.70 min. Studied the influence of the ionosphere on passing VLF radio waves.

1966 July 8 - 05:31 GMT - Launch Vehicle: Kosmos 2. Cosmos 123 Mass: 325 kg (716 lb). Spacecraft: DS-P1-Yu. Agency: MO SSSR. Perigee: 256 km (159 mi). Apogee: 512 km (318 mi). Inclination: 48.80 deg. Period: 92.30 min. Development of systems for air defence and the control of outer space.

1966 December 12 - 20:38 GMT - Launch Vehicle: Kosmos 2. Cosmos 135 Mass: 355 kg (782 lb). Spacecraft: DS-U2-MP. Agency: MO SSSR. Perigee: 253 km (157 mi). Apogee: 648 km (402 mi). Inclination: 48.40 deg. Period: 93.60 min. Studied cosmic dust particles in near-Earth space.

1966 December 21 - 13:12 GMT - Launch Vehicle: Kosmos 2. Cosmos 137 Mass: 295 kg (650 lb). Spacecraft: DS-U2-D. Agency: MO SSSR. Perigee: 219 km (136 mi). Apogee: 1,718 km (1,067 mi). Inclination: 48.80 deg. Period: 104.40 min. Studied charged particle flows.

1967 February 14 - 10:04 GMT - Launch Vehicle: Kosmos 2. Cosmos 142 Mass: 315 kg (694 lb). Spacecraft: DS-U2-I. Agency: MO SSSR. Perigee: 216 km (134 mi). Apogee: 1,320 km (820 mi). Inclination: 48.40 deg. Period: 100.10 min. Studied the influence of the ionosphere on passing VLF radio waves.

1967 March 3 - 06:44 GMT - Launch Vehicle: Kosmos 2. Cosmos 145 Mass: 250 kg (550 lb). Spacecraft: DS-U2-M. Agency: MO SSSR. Perigee: 226 km (140 mi). Apogee: 2,107 km (1,309 mi). Inclination: 48.40 deg. Period: 108.70 min. Development tests of atomic clocks.

1967 March 21 - 10:07 GMT - Launch Vehicle: Kosmos 2. Cosmos 149 Mass: 321 kg (707 lb). Spacecraft: DS-MO. Agency: MO SSSR. Perigee: 246 km (152 mi). Apogee: 284 km (176 mi). Inclination: 48.40 deg. Period: 89.80 min. Used in development of aerodynamic systems for stabilisation and orientation of spacecraft. Also carried military optical equipment experiments.

1967 June 5 - 05:03 GMT - Launch Vehicle: Kosmos 2. Cosmos 163 Mass: 357 kg (787 lb). Spacecraft: DS-U2-MP. Agency: MO SSSR. Perigee: 255 km (158 mi). Apogee: 598 km (371 mi). Inclination: 48.30 deg. Period: 93.10 min. Studied cosmic dust particles in near-Earth space.

1967 June 16 - 04:44 GMT - Launch Vehicle: Kosmos 2. Cosmos 166 Mass: 357 kg (787 lb). Spacecraft: DS-U3-S. Agency: MO SSSR. Perigee: 288 km (178 mi). Apogee: 555 km (344 mi). Inclination: 48.40 deg. Period: 93.00 min. Specialized orbital solar observatory for measuring solar rays in mulitple spectral zones.

1967 December 19 - 06:30 GMT - Launch Vehicle: Kosmos 2. Cosmos 196 Mass: 352 kg (776 lb). Spacecraft: DS-U1-G. Agency: MO SSSR. Perigee: 220 km (130 mi). Apogee: 869 km (539 mi). Inclination: 48.70 deg. Period: 95.50 min. Studied the relationship between variations in the upper atmosphere and solar activity.

1969 July 15 - Launch Vehicle: Kosmos 2. BOR-1 re-entry vehicle test flight Agency: RVSN. Apogee: 70 km (43 mi).