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This rocket article contains payload capacity, but does not include orbital altitude or inclination , which greatly affects the capacity. |
| Function | Small-lift launch vehicle |
|---|---|
| Manufacturer | OKB-1 |
| Country of origin | Soviet Union |
| Size | |
| Stages | 4 |
| Capacity | |
| Payload to LEO | |
| Mass | 4,500 kg (9,900 lb) |
| Associated rockets | |
| Family | R-7 |
| Launch history | |
| Status | Retired |
| Launch sites | Baikonur, Site 31/6 |
| Total launches | 2 |
| Success(es) | 2 |
| First flight | 27 December 1965 |
| Last flight | 20 July 1966 |
| Carries passengers or cargo | US-A |
| Boosters (First stage) – Block B, V, G & D [a] | |
| No. boosters | 4 |
| Powered by | 1 × RD-107 |
| Maximum thrust | 994.3 kN (223,500 lbf) |
| Total thrust | 3,977.2 kN (894,100 lbf) |
| Specific impulse | 315 s (3.09 km/s) |
| Burn time | 118 seconds |
| Propellant | LOX / RP-1 |
| Second stage (core) –Block A | |
| Powered by | 1 × RD-108 |
| Maximum thrust | 977.7 kN (219,800 lbf) |
| Specific impulse | 315 s (3.09 km/s) |
| Burn time | 292 seconds |
| Propellant | LOX / RP-1 |
| Third stage | |
| Powered by | 1 × RD-0109 |
| Maximum thrust | 54.5 kN (12,300 lbf) |
| Specific impulse | 365 s (3.58 km/s) |
| Burn time | 365 seconds |
| Propellant | LOX / 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.