Soyuz/Vostok

Vostok-2 (11A510)
FunctionSmall-lift launch vehicle
ManufacturerOKB-1
Country of originSoviet Union
Size
Stages4
Capacity
Payload to LEO
Mass4,500 kg (9,900 lb)
Associated rockets
FamilyR-7
Launch history
StatusRetired
Launch sitesBaikonur, Site 31/6
Total launches2
Success(es)2
First flight27 December 1965
Last flight20 July 1966
Carries passengers or cargoUS-A
Boosters (First stage) – Block B, V, G & D[a]
No. boosters4
Powered by1 × RD-107
Maximum thrust994.3 kN (223,500 lbf)
Total thrust3,977.2 kN (894,100 lbf)
Specific impulse315 s (3.09 km/s)
Burn time118 seconds
PropellantLOX / RP-1
Second stage (core) – Block A
Powered by1 × RD-108
Maximum thrust977.7 kN (219,800 lbf)
Specific impulse315 s (3.09 km/s)
Burn time292 seconds
PropellantLOX / RP-1
Third stage
Powered by1 × RD-0109
Maximum thrust54.5 kN (12,300 lbf)
Specific impulse365 s (3.58 km/s)
Burn time365 seconds
PropellantLOX / RP-1
Fourth stage – Unknown

The Soyuz/Vostok (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 boosters (first stage) and second stage (core) from a Soyuz rocket combined with the third stage of the Vostok-2, and an unknown fourth 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.

Notes

  1. ^ This is a transliteration of the second through fifth letters of the Cyrillic alphabet (Б, В, Г, Д). A sense-for-sense translation would correspond to the second through fifth letters of the Latin alphabet, 'Block B, C, D & E'.

References

  1. ^ a b Wade, Mark. "Soyuz". Encyclopedia Astronautica. Archived from the original on 2010-01-07. Retrieved 2009-04-15.