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Kosmos 63S1

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R-56, R-26, 63S1 From left to right, dynamic test models of: R-56 monster launch vehicle; R-26 ICBM; Kosmos 63S1 launch vehicle Credit: © Mark Wade

AKA: 63S1;B-1;Kosmos 2I;SL-7. Status: Retired 1967. First Launch: 1961-10-27. Last Launch: 1967-12-19. Number: 38 . Payload: 300 kg (660 lb). Thrust: 636.50 kN (143,091 lbf). Gross mass: 48,110 kg (106,060 lb). Height: 31.00 m (101.00 ft). Diameter: 1.60 m (5.20 ft). Apogee: 250 km (150 mi).

2 stage vehicle consisting of 1 x R-12 + 1 x S1.

LEO Payload: 300 kg (660 lb) to a 250 km orbit at 48.00 degrees.

Stage Data - Kosmos 63S1

• Stage 1. 1 x Kosmos A-1. Gross Mass: 39,515 kg (87,115 lb). Empty Mass: 3,150 kg (6,940 lb). Thrust (vac): 730.500 kN (164,223 lbf). Isp: 264 sec. Burn time: 125 sec. Isp(sl): 230 sec. Diameter: 1.60 m (5.20 ft). Span: 1.80 m (5.90 ft). Length: 18.00 m (59.00 ft). Propellants: Nitric acid/Kerosene. No Engines: 1. Engine: RD-214. Other designations: Sandal; SS-4; 8K63; R-12; 63; 11K63. Status: Out of Production.

• Stage 2. 1 x Kosmos A-2. Gross Mass: 8,595 kg (18,948 lb). Empty Mass: 840 kg (1,850 lb). Thrust (vac): 105.510 kN (23,720 lbf). Isp: 352 sec. Burn time: 250 sec. Isp(sl): 220 sec. Diameter: 1.60 m (5.20 ft). Span: 1.60 m (5.20 ft). Length: 7.80 m (25.50 ft). Propellants: Lox/UDMH. No Engines: 1. Engine: RD-119. Other designations: S1. Status: Out of Production.

• Kosmos 63S1 small booster and DS small satellites authorised. - . Nation: Russia. Spacecraft: DS-1, DS-2.

  Central Committee of the Communist Party and Council of Soviet Ministers Decree 'On the Creation of the Rocket-Carrier 63S1 Based on the R-12 Missile, and the Development and Launch of Small Artificial Satellite--start of work on launcher and satellites at OKB-586'

• DS-2 s/n 1 - . Payload: DS-1. Mass: 300 kg (660 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SA-200. Spacecraft: DS-1. 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..

• DS-1 s/n 1 - . Payload: DS-1. Mass: 300 kg (660 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: SA-200. Spacecraft: DS-1.

  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.

• Cosmos 1 - . Payload: DS-2 s/n 2. Mass: 47 kg (103 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-2. Completed Operations Date: 1962-03-26 . Decay Date: 1962-05-25 . USAF Sat Cat: 266 . COSPAR: 1962-Theta-1. Apogee: 649 km (403 mi). Perigee: 207 km (128 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.

• Cosmos 2 - . Payload: 1MS s/n 1. Mass: 285 kg (628 lb). Nation: Russia. Agency: RVSN. Program: MS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MS. Spacecraft: 1MS. Decay Date: 1963-08-20 . USAF Sat Cat: 269 . COSPAR: 1962-Iota-1. Apogee: 1,485 km (922 mi). Perigee: 207 km (128 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. .

• Cosmos 3 - . Payload: 2MS s/n 1. Mass: 330 kg (720 lb). Nation: Russia. Agency: RVSN. Program: MS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MS. Spacecraft: 2MS. Decay Date: 1962-10-17 . USAF Sat Cat: 281 . COSPAR: 1962-Nu-1. Apogee: 707 km (439 mi). Perigee: 216 km (134 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. .

• Cosmos 5 - . Payload: 2MS s/n 2. Mass: 280 kg (610 lb). Nation: Russia. Agency: RVSN. Program: MS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MS. Spacecraft: 2MS. Decay Date: 1963-05-02 . USAF Sat Cat: 297 . COSPAR: 1962-Upsilon-1. Apogee: 1,578 km (980 mi). Perigee: 192 km (119 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. .

• Cosmos 6 - . Payload: DS-P1 s/n 1. Mass: 355 kg (782 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1. Completed Operations Date: 1962-07-06 . Decay Date: 1962-09-08 . USAF Sat Cat: 338 . COSPAR: 1962-A-Delta-1. Apogee: 348 km (216 mi). Perigee: 261 km (162 mi). Inclination: 48.90 deg. Period: 90.60 min. Prototype ABM radar target; supported developmental experiments for ABM systems..

• Cosmos 8 - . Payload: DS-K-8 s/n 1. Mass: 337 kg (742 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Earth. Type: Micrometeoroid satellite. Spacecraft Bus: DS. Spacecraft: DS-K-8. Completed Operations Date: 1962-08-23 . Decay Date: 1963-08-17 . USAF Sat Cat: 367 . COSPAR: 1962-A-Xi-1. Apogee: 598 km (371 mi). Perigee: 244 km (151 mi). Inclination: 49.00 deg. Period: 92.90 min. Detected meteoroid flux in near-earth space and carried unspecified military research equipment..

• Cosmos 11 - . Payload: DS-A1 s/n 1. Mass: 315 kg (694 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1. Completed Operations Date: 1962-10-28 . Decay Date: 1964-05-18 . USAF Sat Cat: 441 . COSPAR: 1962-B-Theta-1. Apogee: 858 km (533 mi). Perigee: 240 km (140 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.

• 1MS - . Mass: 285 kg (628 lb). Nation: Russia. Agency: RVSN. Program: MS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: MS. Spacecraft: 1MS.

• DS-P1 s/n 2 - . Payload: DS-P1. Mass: 355 kg (782 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1. Prototype ABM radar target; supported developmental experiments for ABM systems..

• Cosmos 14 - . Payload: DS-U / Omega-1. Mass: 347 kg (765 lb). Nation: Russia. Agency: MO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: Omega. Decay Date: 1963-08-29 . USAF Sat Cat: 567 . COSPAR: 1963-010A. Apogee: 410 km (250 mi). Perigee: 250 km (150 mi). Inclination: 48.90 deg. Period: 91.10 min. Tested VNIIEM electric gyrodyne satellite orientation technology..

• Cosmos 17 - . Payload: DS-A1 s/n 2. Mass: 322 kg (709 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1. Completed Operations Date: 1963-05-30 . Decay Date: 1965-06-02 . USAF Sat Cat: 580 . COSPAR: 1963-017A. Apogee: 658 km (408 mi). Perigee: 251 km (155 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.

• DS-MT s/n 1 - . Payload: DS-MT. Mass: 340 kg (740 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MT. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays..

• Cosmos 19 - . Payload: DS-P1 s/n 3. Mass: 355 kg (782 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1. Completed Operations Date: 1964-03-29 . Decay Date: 1964-03-30 . USAF Sat Cat: 632 . COSPAR: 1963-033A. Apogee: 497 km (308 mi). Perigee: 267 km (165 mi). Inclination: 49.00 deg. Period: 92.10 min. Prototype ABM radar target; supported developmental experiments for ABM systems..

• DS-A1 s/n 3 - . Payload: DS-A1. Mass: 30 kg (66 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1.

  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.

• DS-A1 s/n 4 - . Payload: DS-A1. Mass: 30 kg (66 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1.

  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.

• Cosmos 23 - . Payload: DS-U / Omega-1. Mass: 347 kg (765 lb). Nation: Russia. Agency: MO. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: Omega. Decay Date: 1964-03-27 . USAF Sat Cat: 707 . COSPAR: 1963-050A. Apogee: 560 km (340 mi). Perigee: 232 km (144 mi). Inclination: 48.90 deg. Period: 92.40 min. Tested VNIIEM electric gyrodyne satellite orientation technology..

• Cosmos 25 - . Payload: DS-P1 s/n 4. Mass: 355 kg (782 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1. Completed Operations Date: 1964-11-21 . Decay Date: 1964-11-21 . USAF Sat Cat: 757 . COSPAR: 1964-010A. Apogee: 495 km (307 mi). Perigee: 260 km (160 mi). Inclination: 49.10 deg. Period: 92.10 min. Prototype ABM radar target; supported developmental experiments for ABM systems..

• Cosmos 26 - . Payload: DS-MG s/n 1. Mass: 365 kg (804 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MG. Completed Operations Date: 1964-04-01 . Decay Date: 1964-09-28 . USAF Sat Cat: 766 . COSPAR: 1964-013A. Apogee: 376 km (233 mi). Perigee: 268 km (166 mi). Inclination: 48.90 deg. Period: 91.00 min. Payload developed by VNIIEM to test electric gyrodyne orientation systems. Also obtained radiation data..

• Cosmos 31 - . Payload: DS-MT s/n 2. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MT. Completed Operations Date: 1964-06-23 . Decay Date: 1964-10-20 . USAF Sat Cat: 803 . COSPAR: 1964-028A. Apogee: 485 km (301 mi). Perigee: 221 km (137 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..

• Cosmos 36 - . Payload: DS-P1-Yu s/n 1. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1-Yu. Completed Operations Date: 1965-02-27 . Decay Date: 1965-02-28 . USAF Sat Cat: 844 . COSPAR: 1964-042A. Apogee: 488 km (303 mi). Perigee: 253 km (157 mi). Inclination: 49.00 deg. Period: 92.00 min. Development of systems for air defence and the control of outer space..

• Cosmos 42 - . Mass: 100 kg (220 lb). Nation: Russia. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft Bus: Strela. Spacecraft: Strela-1. Decay Date: 1965-12-19 . USAF Sat Cat: 864 . COSPAR: 1964-050A. Apogee: 1,105 km (686 mi). Perigee: 228 km (141 mi). Inclination: 48.90 deg. Period: 98.10 min.

• Cosmos 43 - . Mass: 100 kg (220 lb). Nation: Russia. Agency: MO. Program: Strela. Class: Communications. Type: Military store-dump communications satellite. Spacecraft Bus: Strela. Spacecraft: Strela-1. Decay Date: 1965-12-27 . USAF Sat Cat: 867 . COSPAR: 1964-050C. Apogee: 1,093 km (679 mi). Perigee: 227 km (141 mi). Inclination: 48.90 deg. Period: 98.00 min.

• Cosmos 49 - . Payload: DS-MG s/n 2. Mass: 355 kg (782 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MG. Completed Operations Date: 1964-11-09 . Decay Date: 1965-08-21 . USAF Sat Cat: 913 . COSPAR: 1964-069A. Apogee: 472 km (293 mi). Perigee: 260 km (160 mi). Inclination: 48.90 deg. Period: 91.90 min. Payload developed by VNIIEM to test electric gyrodyne orientation systems. Also studied measured Earth infrared and ultraviolet flux..

• DS-2 s/n 2 - . Payload: DS-2. Mass: 315 kg (694 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-2. 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..

• Cosmos 51 - . Payload: DS-MT s/n 3. Mass: 350 kg (770 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-MT. Completed Operations Date: 1965-01-04 . Decay Date: 1965-11-14 . USAF Sat Cat: 947 . COSPAR: 1964-080A. Apogee: 537 km (333 mi). Perigee: 258 km (160 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..

• Cosmos 53 - . Payload: DS-A1 s/n 5. Mass: 310 kg (680 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1. Completed Operations Date: 1965-02-09 . Decay Date: 1966-08-12 . USAF Sat Cat: 983 . COSPAR: 1965-006A. Apogee: 1,172 km (728 mi). Perigee: 221 km (137 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.

• DS-P1-Yu s/n 2 - . Payload: DS-P1-Yu. Mass: 330 kg (720 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1-Yu. Development of systems for air defence and the control of outer space..

• DS-A1 s/n 6 - . Payload: DS-A1. Mass: 30 kg (66 lb). Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1.

  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.

• Cosmos 70 - . Payload: DS-A1 s/n 7. Mass: 250 kg (550 lb). Nation: Russia. Agency: MO. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-A1. Completed Operations Date: 1965-07-12 . Decay Date: 1966-12-18 . USAF Sat Cat: 1431 . COSPAR: 1965-052A. Apogee: 1,176 km (730 mi). Perigee: 223 km (138 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.

• Cosmos 76 - . Payload: DS-P1-Yu s/n 3. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1-Yu. Completed Operations Date: 1965-10-28 . Decay Date: 1966-03-16 . USAF Sat Cat: 1464 . COSPAR: 1965-059A. Apogee: 513 km (318 mi). Perigee: 256 km (159 mi). Inclination: 48.80 deg. Period: 92.20 min. Development of systems for air defence and the control of outer space..

• Cosmos 101 - . Payload: DS-P1-Yu s/n 4. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1-Yu. Completed Operations Date: 1966-03-11 . Decay Date: 1966-07-12 . USAF Sat Cat: 1846 . COSPAR: 1965-107A. Apogee: 533 km (331 mi). Perigee: 256 km (159 mi). Inclination: 48.80 deg. Period: 92.50 min. Development of systems for air defence and the control of outer space..

• DS-K-40 s/n 1 - . Payload: DS-K-40. Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-K-40. Development of systems for the later operational Tselina satellites..

• Cosmos 108 - . Payload: DS-U1-G s/n 1. Mass: 355 kg (782 lb). Nation: Russia. Agency: MO. Program: DS. Class: Earth. Type: Ionosphere satellite. Spacecraft Bus: DS. Spacecraft: DS-U1-G. Completed Operations Date: 1966-02-26 . Decay Date: 1966-11-21 . USAF Sat Cat: 2002 . COSPAR: 1966-011A. Apogee: 850 km (520 mi). Perigee: 220 km (130 mi). Inclination: 48.80 deg. Period: 95.30 min. Studied the relationship between variations in the upper atmosphere and solar activity..

• DS-K-40 s/n 2 - . Payload: DS-K-40. Nation: Russia. Agency: RVSN. Program: DS. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: DS. Spacecraft: DS-K-40. Development of systems for the later operational Tselina satellites..

• Cosmos 123 - . Payload: DS-P1-Yu s/n 5. Mass: 325 kg (716 lb). Nation: Russia. Agency: MO. Program: DS. Class: Military. Type: Military target satellite. Spacecraft Bus: DS. Spacecraft: DS-P1-Yu. Completed Operations Date: 1966-12-10 . Decay Date: 1966-12-10 . USAF Sat Cat: 2295 . COSPAR: 1966-061A. Apogee: 512 km (318 mi). Perigee: 256 km (159 mi). Inclination: 48.80 deg. Period: 92.30 min. Development of systems for air defence and the control of outer space..

• Cosmos 137 - . Payload: DS-U2-D s/n 1. Mass: 295 kg (650 lb). Nation: Russia. Agency: MO. Program: DS. Class: Earth. Type: Magnetosphere satellite. Spacecraft Bus: DS. Spacecraft: DS-U2-D. Completed Operations Date: 1969-05-12 . Decay Date: 1967-11-23 . USAF Sat Cat: 2627 . COSPAR: 1966-117A. Apogee: 1,718 km (1,067 mi). Perigee: 219 km (136 mi). Inclination: 48.80 deg. Period: 104.40 min. Studied charged particle flows..

• Cosmos 196 - . Payload: DS-U1-G s/n 2. Mass: 352 kg (776 lb). Nation: Russia. Agency: MO. Program: DS. Class: Earth. Type: Ionosphere satellite. Spacecraft Bus: DS. Spacecraft: DS-U1-G. Completed Operations Date: 1968-02-07 . Decay Date: 1968-07-07 . USAF Sat Cat: 3074 . COSPAR: 1967-125A. Apogee: 869 km (539 mi). Perigee: 220 km (130 mi). Inclination: 48.70 deg. Period: 95.50 min. Studied the relationship between variations in the upper atmosphere and solar activity..