Soyuz/Vostok

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 - Block A/B/V/G
N^o 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
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

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