R-56, R-26, 63S1 Credit - © Mark Wade

In 1960 the Soviet government decreed development of a lightweight launch vehicle for launch of payloads not requiring R-7 family of boosters. A modification of the R-12 IRBM was selected as the first stage; a new high-performance second stage was developed using a unique Lox/UDMH propellant combination. After two failures, the first successful flight was on March 16, 1962. The 63S1 was used through May 1966 for a total of 40 launches, of which 12 were failures. It was succeeded by the 63S1M prototype for the 11K63 production space launcher.

Serious consideration of designs for a Soviet light orbital launch vehicle began in the mid-fifties. At the end of 1956 Korolev studied a scientific launch vehicle based on an R-5 first stage and R-11 second stage. He concluded that it could only be used as a sounding rocket, that a new third stage would have to be developed for the combination to have orbital capability.

Yangel studied use of either the R-5M or the R-12 with various 'off the shelf' missile stages developed for surface-to-air missiles, but found that no such combination could reach orbit. Use of the R-12 in parallel stages was also possible, but the problem of in-flight ignition of the core stage was one not solved in the Soviet Union until 1955. Solid rockets available in the Soviet Union at that time had too low a specific impulse and too high a mass fraction to be useful in a satellite launcher. The only solution was a redesign of the R-12 to optimise it for the satellite launch role, and a small, new-design upper stage.

Korolev was anxioius to move on to manned space exploration and was not interested in developing small launch vehicles. He was glad for Yangel to pursue this. However design work at Yangel's bureau was limited and desultory, since there was no outside support for the project until after the worldwide sensation following the launch of the first Sputnik in late 1957. But by then development of Yangel's R-16 ICBM had priority.

A key element in the development of a two-stage space launch vehicle was the solution of in-flight separation and ignition of the second stage following burn-out of the first stage. Yangel's R-16 ICBM was fitted with thrusters on the interstage between the first and second stages to provide thrust between shut-down of the first stage and ignition of the second. This kept the propellants in the tanks and the engine under G-force; there was no coasting period. The solution already adopted for some surface-to-air missiles - a 'hot start' where the second stage ignited while the first stage still was firing - was not adopted due to performance reasons.

Start-up of a rocket stage in zero-G was not solved until Korolev's Luna upper stage for the R-7. This was developed in response to a 20 March 1958 government resolution requiring the first launch of a Soviet probe to the moon within a year. In this period Glushko was developing the RD-109 engine for a high performance R-7 third stage. This burned liquid oxygen and UDMH propellants, achieving the astonishing specific impulse of 350 seconds. This would potentially double the payload compared to a liquid oxygen/kerosene stage. But the new technology engine was considered too much of a risk by Korolev. It also used the toxic hydrazine fuel he detested on principal. So on 10 October 1958 he gave Kosberg the task of developing a third stage engine for the R-7 derived from the R-7 first stage verniers and burning his preferred liquid oxygen/kerosene propellants. Meanwhile Glushko pursued further development of the RD-109, which used a 75 atmosphere chamber pressure and a closed engine cycle. By mid-1958 he had encountered various knotty problems in chamber cooling and the gas generator. It was decided to stop all work on the RD-109 in order to concentrate on development of the engines for the R-14 IRBM and R-16 ICBM. The estimated date for completion of development slipped to the end of 1959, too late for it to be used for the Vostok lunar launches. However it could be ready for the Vostok/Zenit manned and reconnaissance spacecraft orbital flights.

Development of the engine on tests stands was finally completed in January 1959, with runs in a 90 cubic metre vacuum chamber at a pressure of 1 mm Hg. The RD-109 that finally emerged had a chamber pressure of 76 to 70 atm and a specific impulse of 334 seconds. The conventional liquid oxygen/kerosene engine that Kosberg had developed as a replacement in the Luna probes (the RD-0105/RO-5) had a specific impulse of 316 seconds. Use of the RD-109 in the Luna stage would have increased payload to 424 kg as opposed to 373 kg with the RD-0105. But for use on the piloted Vostok booster, Korolev refused to consider using UDMH as a fuel due to its toxicity. Therefore he opted to further develop the Kosberg engine for the Vostok, leaving the RD-109 an engine without an application.

However Yangel saw that the engine would be a good match for a high-performance upper stage application. Therefore Glushko agreed to continue to refine the RD-109, now designated the RD-119. The new engine had many improvements in the chamber and nozzle profile and could run at higher chamber temperatures through the use of double-shell wall cooling. The result was a specific impulse of 352 seconds. The engine was run at up to 260 seconds firing durations as opposed to the 150 seconds rated ability.

A government resolution of 8 August 1960 authorised Yangel to develop the 63S1 light orbital launch vehicle for launch of payloads not requiring the R-7 family of boosters and to produce a series of ten for launch of small satellites. The booster had to use the existing R-12 IRBM as a first stage, the existing Mayak launch silo as a launcher, and an existing engine for the upper stage. Since the R-12 was built for silo launch (it could not be held on a surface pad exposed to the elements), the existing R-12 silo 'Mayak-2' at Kapustin Yar was adapted. A swing-back shelter above the top of silo covered the second stage and payload during launch preparations.

The 63S1 was used through May 1966 for a total of 40 launches, of which 12 were failures. The Mayak complex was built for missile launches and was not durable enough for repeated space launches. A space launch complex had to be a virtual 'launch chimney' and endure the flames of many launches and accomodate many different payloads. Therefore the Mayak complex was abandoned and the Voskhod and Raduga complexes were designed for later R-12 and R-14 derived space launchers. The same military cadres designed and built the R-7 Angara complex and missile sites.

Manufacturer: Yuzhnoye. Launches: 38. Failures: 12. Success Rate: 68.42%. First Launch Date: 1961-10-27. Last Launch Date: 1967-12-19. Launch data is: complete. LEO Payload: 300 kg (660 lb). to: 250 km Orbit. at: 48.00 degrees. Apogee: 2,000 km (1,200 mi). Associated Spacecraft: 1MS, 2MS, DS-1, DS-2, DS-A1, DS-K-40, DS-K-8, DS-MG, DS-MT, DS-P1, DS-P1-Yu, DS-U1-G, DS-U2-D, Omega, Strela-1. Liftoff Thrust: 636.500 kN (143,091 lbf). Total Mass: 48,110 kg (106,060 lb). Core Diameter: 1.60 m (5.20 ft). Total Length: 31.00 m (101.00 ft).

• Stage Number: 1. 1 x Stage: 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 Number: 2. 1 x Stage: 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.

1960 August 8 - Launch Vehicle: Kosmos 63S1.

• Kosmos 63S1 small booster and DS small satellites authorised. Nation: USSR. 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'References: 474.

• DS-2 s/n 1 Nation: USSR. Program: DS. Payload: DS-1. Mass: 300 kg (660 lb). Class: Technology. Spacecraft: DS-1. Agency: RVSN. COSPAR: F611027A. 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 Nation: USSR. Program: DS. Payload: DS-1. Mass: 300 kg (660 lb). Class: Technology. Spacecraft: DS-1. Agency: RVSN. COSPAR: F611221A. 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 Nation: USSR. Program: DS. Payload: DS-2 s/n 2. Mass: 47 kg (103 lb). Class: Technology. Spacecraft: DS-2. Agency: RVSN. Perigee: 207 km (128 mi). Apogee: 649 km (403 mi). Inclination: 49.00 deg. Period: 93.10 min. COSPAR: 1962-Theta-1. USAF Sat Cat: 266. Completed Operations Date: 1962-03-26. Decay Date: 1962-05-25. 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.References: 1, 2, 5, 6, 99.

• Cosmos 2 Nation: USSR. Program: MS. Payload: 1MS s/n 1. Mass: 285 kg (628 lb). Class: Technology. Spacecraft: 1MS. Agency: RVSN. Perigee: 207 km (128 mi). Apogee: 1,485 km (922 mi). Inclination: 49.00 deg. Period: 101.80 min. COSPAR: 1962-Iota-1. USAF Sat Cat: 269. Decay Date: 1963-08-20. Radiation, cosmic ray data. Decay date suspect Investigation of the upper atmosphere and outer space; development of elements in the design of space craft. References: 1, 2, 5, 6.

• Cosmos 3 Nation: USSR. Program: MS. Payload: 2MS s/n 1. Mass: 330 kg (720 lb). Class: Technology. Spacecraft: 2MS. Agency: RVSN. Perigee: 216 km (134 mi). Apogee: 707 km (439 mi). Inclination: 49.00 deg. Period: 93.80 min. COSPAR: 1962-Nu-1. USAF Sat Cat: 281. Decay Date: 1962-10-17. Cosmic ray, radiation data. Investigation of the upper atmosphere and outer space; development of elements in the design of space craft. References: 1, 2, 5, 6.

• Cosmos 5 Nation: USSR. Program: MS. Payload: 2MS s/n 2. Mass: 280 kg (610 lb). Class: Technology. Spacecraft: 2MS. Agency: RVSN. Perigee: 192 km (119 mi). Apogee: 1,578 km (980 mi). Inclination: 49.10 deg. Period: 102.60 min. COSPAR: 1962-Upsilon-1. USAF Sat Cat: 297. Decay Date: 1963-05-02. Monitored artificial radiation. Investigation of the upper atmosphere and outer space; development of elements in the design of space craft. References: 1, 2, 5, 6.

• Cosmos 6 Nation: USSR. Program: DS. Payload: DS-P1 s/n 1. Mass: 355 kg (782 lb). Class: Military. Type: Target. Spacecraft: DS-P1. Agency: RVSN. Perigee: 261 km (162 mi). Apogee: 348 km (216 mi). Inclination: 48.90 deg. Period: 90.60 min. COSPAR: 1962-A-Delta-1. USAF Sat Cat: 338. Completed Operations Date: 1962-07-06. Decay Date: 1962-09-08. Prototype ABM radar target; supported developmental experiments for ABM systems. References: 1, 2, 5, 6, 99.

• Cosmos 8 Nation: USSR. Program: DS. Payload: DS-K-8 s/n 1. Mass: 337 kg (742 lb). Class: Earth. Type: Micrometeoroid. Spacecraft: DS-K-8. Agency: RVSN. Perigee: 244 km (151 mi). Apogee: 598 km (371 mi). Inclination: 49.00 deg. Period: 92.90 min. COSPAR: 1962-A-Xi-1. USAF Sat Cat: 367. Completed Operations Date: 1962-08-23. Decay Date: 1963-08-17. Detected meteoroid flux in near-earth space and carried unspecified military research equipment. References: 1, 2, 5, 6, 99.

• Cosmos 11 Nation: USSR. Program: DS. Payload: DS-A1 s/n 1. Mass: 315 kg (694 lb). Class: Technology. Type: Navigation. Spacecraft: DS-A1. Agency: RVSN. Perigee: 240 km (140 mi). Apogee: 858 km (533 mi). Inclination: 48.90 deg. Period: 95.60 min. COSPAR: 1962-B-Theta-1. USAF Sat Cat: 441. Completed Operations Date: 1962-10-28. Decay Date: 1964-05-18. 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.References: 1, 2, 5, 6, 99.

• 1MS Nation: USSR. Program: MS. Class: Technology. Spacecraft: 1MS. Agency: RVSN. COSPAR: F621025A.

• DS-P1 s/n 2 Nation: USSR. Program: DS. Payload: DS-P1. Class: Military. Type: Target. Spacecraft: DS-P1. Agency: RVSN. COSPAR: F630406A. Prototype ABM radar target; supported developmental experiments for ABM systems.

• Cosmos 14 Nation: USSR. Payload: DS-U / Omega-1. Class: Technology. Spacecraft: Omega. Agency: MO SSSR. Perigee: 250 km (150 mi). Apogee: 410 km (250 mi). Inclination: 48.90 deg. Period: 91.10 min. COSPAR: 1963-010A. USAF Sat Cat: 567. Decay Date: 1963-08-29. Tested VNIIEM electric gyrodyne satellite orientation technology. References: 1, 2, 5, 6.

• Cosmos 17 Nation: USSR. Program: DS. Payload: DS-A1 s/n 2. Mass: 322 kg (709 lb). Class: Technology. Type: Navigation. Spacecraft: DS-A1. Agency: MO SSSR. Perigee: 251 km (155 mi). Apogee: 658 km (408 mi). Inclination: 48.90 deg. Period: 93.70 min. COSPAR: 1963-017A. USAF Sat Cat: 580. Completed Operations Date: 1963-05-30. Decay Date: 1965-06-02. 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.References: 1, 2, 5, 6, 99.

• DS-MT s/n 1 Nation: USSR. Program: DS. Payload: DS-MT. Class: Technology. Spacecraft: DS-MT. Agency: RVSN. COSPAR: F630601A. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays.

• Cosmos 19 Nation: USSR. Program: DS. Payload: DS-P1 s/n 3. Mass: 355 kg (782 lb). Class: Military. Type: Target. Spacecraft: DS-P1. Agency: MO SSSR. Perigee: 267 km (165 mi). Apogee: 497 km (308 mi). Inclination: 49.00 deg. Period: 92.10 min. COSPAR: 1963-033A. USAF Sat Cat: 632. Completed Operations Date: 1964-03-29. Decay Date: 1964-03-30. Prototype ABM radar target; supported developmental experiments for ABM systems. References: 1, 2, 5, 6, 99.

• DS-A1 s/n 3 Nation: USSR. Program: DS. Payload: DS-A1. Class: Technology. Type: Navigation. Spacecraft: DS-A1. Agency: RVSN. COSPAR: F630822A. 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 Nation: USSR. Program: DS. Payload: DS-A1. Class: Technology. Type: Navigation. Spacecraft: DS-A1. Agency: RVSN. COSPAR: F631024A. 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 Nation: USSR. Payload: DS-U / Omega-1. Mass: 347 kg (765 lb). Class: Technology. Spacecraft: Omega. Agency: MO SSSR. Perigee: 232 km (144 mi). Apogee: 560 km (340 mi). Inclination: 48.90 deg. Period: 92.40 min. COSPAR: 1963-050A. USAF Sat Cat: 707. Decay Date: 1964-03-27. Tested VNIIEM electric gyrodyne satellite orientation technology. References: 1, 2, 5, 6.

• Cosmos 25 Nation: USSR. Program: DS. Payload: DS-P1 s/n 4. Mass: 355 kg (782 lb). Class: Military. Type: Target. Spacecraft: DS-P1. Agency: MO SSSR. Perigee: 260 km (160 mi). Apogee: 495 km (307 mi). Inclination: 49.10 deg. Period: 92.10 min. COSPAR: 1964-010A. USAF Sat Cat: 757. Completed Operations Date: 1964-11-21. Decay Date: 1964-11-21. Prototype ABM radar target; supported developmental experiments for ABM systems. References: 1, 2, 5, 6, 99.

• Cosmos 26 Nation: USSR. Program: DS. Payload: DS-MG s/n 1. Mass: 365 kg (804 lb). Class: Technology. Spacecraft: DS-MG. Agency: MO SSSR. Perigee: 268 km (166 mi). Apogee: 376 km (233 mi). Inclination: 48.90 deg. Period: 91.00 min. COSPAR: 1964-013A. USAF Sat Cat: 766. Completed Operations Date: 1964-04-01. Decay Date: 1964-09-28. Payload developed by VNIIEM to test electric gyrodyne orientation systems. Also obtained radiation data. References: 1, 2, 5, 6, 99.

• Cosmos 31 Nation: USSR. Program: DS. Payload: DS-MT s/n 2. Mass: 325 kg (716 lb). Class: Technology. Spacecraft: DS-MT. Agency: MO SSSR. Perigee: 221 km (137 mi). Apogee: 485 km (301 mi). Inclination: 48.90 deg. Period: 91.70 min. COSPAR: 1964-028A. USAF Sat Cat: 803. Completed Operations Date: 1964-06-23. Decay Date: 1964-10-20. Payload developed by the VNIIEM to test electric gyrodyne orientation systems. Also studied variations in the intensity of cosmic rays. References: 1, 2, 5, 6, 99.

• Cosmos 36 Nation: USSR. Program: DS. Payload: DS-P1-Yu s/n 1. Mass: 325 kg (716 lb). Class: Military. Type: Target. 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. COSPAR: 1964-042A. USAF Sat Cat: 844. Completed Operations Date: 1965-02-27. Decay Date: 1965-02-28. Development of systems for air defence and the control of outer space. References: 1, 2, 5, 6, 99.

• Cosmos 42 Nation: USSR. Program: Strela. Mass: 100 kg (220 lb). Class: Communications. Type: Military Store-dump. 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. COSPAR: 1964-050A. USAF Sat Cat: 864. Decay Date: 1965-12-19. References: 1, 2, 5, 6.

• Cosmos 43 Nation: USSR. Program: Strela. Mass: 100 kg (220 lb). Class: Communications. Type: Military Store-dump. Spacecraft: Strela-1. Agency: MO SSSR. Perigee: 227 km (141 mi). Apogee: 1,093 km (679 mi). Inclination: 48.90 deg. Period: 98.00 min. COSPAR: 1964-050C. USAF Sat Cat: 867. Decay Date: 1965-12-27. References: 2, 5, 6.

• Cosmos 49 Nation: USSR. Program: DS. Payload: DS-MG s/n 2. Mass: 355 kg (782 lb). Class: Technology. Spacecraft: DS-MG. Agency: MO SSSR. Perigee: 260 km (160 mi). Apogee: 472 km (293 mi). Inclination: 48.90 deg. Period: 91.90 min. COSPAR: 1964-069A. USAF Sat Cat: 913. Completed Operations Date: 1964-11-09. Decay Date: 1965-08-21. Payload developed by VNIIEM to test electric gyrodyne orientation systems. Also studied measured Earth infrared and ultraviolet flux. References: 1, 2, 5, 6, 99.

• DS-2 s/n 2 Nation: USSR. Program: DS. Payload: DS-2. Class: Technology. Spacecraft: DS-2. Agency: RVSN. COSPAR: F641201A. 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 Nation: USSR. Program: DS. Payload: DS-MT s/n 3. Mass: 350 kg (770 lb). Class: Technology. Spacecraft: DS-MT. Agency: MO SSSR. Perigee: 258 km (160 mi). Apogee: 537 km (333 mi). Inclination: 48.80 deg. Period: 92.60 min. COSPAR: 1964-080A. USAF Sat Cat: 947. Completed Operations Date: 1965-01-04. Decay Date: 1965-11-14. 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. References: 1, 2, 5, 6, 99.

• Cosmos 53 Nation: USSR. Program: DS. Payload: DS-A1 s/n 5. Mass: 310 kg (680 lb). Class: Technology. Type: Navigation. 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. COSPAR: 1965-006A. USAF Sat Cat: 983. Completed Operations Date: 1965-02-09. Decay Date: 1966-08-12. 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.References: 1, 2, 5, 6, 99.

• DS-P1-Yu s/n 2 Nation: USSR. Program: DS. Payload: DS-P1-Yu. Class: Military. Type: Target. Spacecraft: DS-P1-Yu. Agency: RVSN. COSPAR: F650212A. Development of systems for air defence and the control of outer space.

• DS-A1 s/n 6 Nation: USSR. Program: DS. Payload: DS-A1. Class: Technology. Type: Navigation. Spacecraft: DS-A1. Agency: RVSN. COSPAR: F650220A. 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 Nation: USSR. Program: DS. Payload: DS-A1 s/n 7. Mass: 250 kg (550 lb). Class: Technology. Type: Navigation. 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. COSPAR: 1965-052A. USAF Sat Cat: 1431. Completed Operations Date: 1965-07-12. Decay Date: 1966-12-18. 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.References: 1, 2, 5, 6, 99.

• Cosmos 76 Nation: USSR. Program: DS. Payload: DS-P1-Yu s/n 3. Mass: 325 kg (716 lb). Class: Military. Type: Target. 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. COSPAR: 1965-059A. USAF Sat Cat: 1464. Completed Operations Date: 1965-10-28. Decay Date: 1966-03-16. Development of systems for air defence and the control of outer space. References: 1, 2, 5, 6, 99.

• Cosmos 101 Nation: USSR. Program: DS. Payload: DS-P1-Yu s/n 4. Mass: 325 kg (716 lb). Class: Military. Type: Target. 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. COSPAR: 1965-107A. USAF Sat Cat: 1846. Completed Operations Date: 1966-03-11. Decay Date: 1966-07-12. Development of systems for air defence and the control of outer space. References: 1, 2, 5, 6, 99.

• DS-K-40 s/n 1 Nation: USSR. Program: DS. Payload: DS-K-40. Class: Technology. Spacecraft: DS-K-40. Agency: RVSN. COSPAR: F651228A. Development of systems for the later operational Tselina satellites.

• Cosmos 108 Nation: USSR. Program: DS. Payload: DS-U1-G s/n 1. Mass: 355 kg (782 lb). Class: Earth. Type: Ionosphere. 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. COSPAR: 1966-011A. USAF Sat Cat: 2002. Completed Operations Date: 1966-02-26. Decay Date: 1966-11-21. Studied the relationship between variations in the upper atmosphere and solar activity. References: 1, 2, 5, 6, 99.

• DS-K-40 s/n 2 Nation: USSR. Program: DS. Payload: DS-K-40. Class: Technology. Spacecraft: DS-K-40. Agency: RVSN. COSPAR: F660221A. Development of systems for the later operational Tselina satellites.

• Cosmos 123 Nation: USSR. Program: DS. Payload: DS-P1-Yu s/n 5. Mass: 325 kg (716 lb). Class: Military. Type: Target. 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. COSPAR: 1966-061A. USAF Sat Cat: 2295. Completed Operations Date: 1966-12-10. Decay Date: 1966-12-10. Development of systems for air defence and the control of outer space. References: 1, 2, 5, 6, 99.

• Cosmos 137 Nation: USSR. Program: DS. Payload: DS-U2-D s/n 1. Mass: 295 kg (650 lb). Class: Earth. Type: Magnetosphere. 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. COSPAR: 1966-117A. USAF Sat Cat: 2627. Completed Operations Date: 1969-05-12. Decay Date: 1967-11-23. Studied charged particle flows. References: 1, 2, 5, 6, 99.

• Cosmos 196 Nation: USSR. Program: DS. Payload: DS-U1-G s/n 2. Mass: 352 kg (776 lb). Class: Earth. Type: Ionosphere. 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. COSPAR: 1967-125A. USAF Sat Cat: 3074. Completed Operations Date: 1968-02-07. Decay Date: 1968-07-07. Studied the relationship between variations in the upper atmosphere and solar activity. References: 1, 2, 5, 6, 99.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.

• Zak, Anatoly, Spaceflight, "Cosmos Launcher", 1996, Volume 38, page 416.

• Agapov, V, Novosti Kosmonavtiki, "K zapusku pervovo ISZ serii 'DS'", 1997, Issue 6.