Soyuz/Vostok

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Soyuz/Vostok
Function Interim carrier rocket
Manufacturer OKB-1
Country of origin  Soviet Union
Size
Stages Three
Capacity
Payload to
LEO
4,500 kilograms (9,900 lb)
Associated rockets
Family R-7
Launch history
Status Retired
Launch sites Baikonur 31/6
Total launches 2
Successes 2
First flight 27 December 1965
Last flight 20 July 1966
Notable payloads US-A
Boosters (Stage 0) - Block A/B/V/G
No boosters 4
Engines 1 RD-107
Thrust 994.3 kilonewtons (223,500 lbf)
Specific impulse 315 sec
Burn time 118 seconds
Fuel RP-1/LOX
First Stage - 11S59
Engines 1 RD-108
Thrust 977.7 kilonewtons (219,800 lbf)
Specific impulse 315 sec
Burn time 292 seconds
Fuel RP-1/LOX
Second Stage
Engines 1 RD-0109
Thrust 54.5 kN
Burn time 365 seconds
Fuel RP-1/LOX
Third Stage - Unknown
Engines
Thrust
Fuel

The Soyuz/Vostok, also known as just Soyuz or Vostok, or by its GRAU index, 11A510 was an interim expendable carrier rocket used by the Soviet Union in 1965 and 1966. Two were launched with prototype US-A satellites.[1]

The Soyuz/Vostok was launched from Site 31/6 at the Baikonur Cosmodrome. It consisted of the first stage and boosters from a Soyuz rocket combined with the second stage of the Vostok-2, and an unknown third stage.[1] Along with the Voskhod-derived Polyot, it was built as an interim between the cancellation of the UR-200 development programme, and the introduction of the Tsyklon-2, which took over US-A launches once it entered service.

References[edit]

  1. ^ a b Wade, Mark. "Soyuz". Encyclopedia Astronautica. Retrieved 2009-04-15.