Function | Carrier rocket |
---|---|
Manufacturer | OKB-1 |
Country of origin | Soviet Union |
Size | |
Height | 50 metres (160 ft) |
Diameter | 10.3 metres (34 ft) |
Mass | 300,000 kilograms (660,000 lb) |
Stages | Two |
Capacity | |
Payload to LEO | |
Mass | 5,500 kilograms (12,100 lb) |
Associated rockets | |
Family | R-7 |
Launch history | |
Status | Retired |
Launch sites | Baikonur Site 31/6 |
Total launches | 3[1] |
Success(es) | 3 |
First flight | 24 November 1970 |
Last flight | 12 August 1971 |
People or cargo transported | LK |
Boosters | |
No. boosters | 4 |
Powered by | 1 RD-107-8D728 |
Maximum thrust | 995 kilonewtons (224,000 lbf) |
Specific impulse | 314 sec |
Burn time | 119 seconds |
Propellant | RP-1/LOX |
First stage | |
Powered by | 1 RD-108-8D727 |
Maximum thrust | 977 kilonewtons (220,000 lbf) |
Specific impulse | 315 sec |
Burn time | 291 seconds |
Propellant | RP-1/LOX |
Second stage | |
Powered by | 1 RD-0110 |
Maximum thrust | 294 kilonewtons (66,000 lbf) |
Specific impulse | 330 sec |
Burn time | 246 seconds |
Propellant | RP-1/LOX |
The Soyuz-L (Russian: Союз, meaning "union"), GRAU index 11A511L was a Soviet expendable carrier rocket designed by OKB-1 and manufactured by State Aviation Plant No. 1 in Samara, Russia. It was created to test the LK lunar lander in low Earth orbit, as part of the Soviet lunar programme.
The Soyuz-L was a derivative of the original Soyuz rocket featuring the reinforced first stage and boosters supporting the Molniya-M's third stage, so that it could carry a more massive payload. A larger payload fairing was also fitted, to accommodate the LK spacecraft.[2] The Soyuz-L was only launched three times between 1970 and 1971, all successful.[1] The later Soyuz-U used a similar configuration to the Soyuz-L.
References
- ^ a b Krebs, Gunter. "Soyuz-L (11A511L)". Gunter's space page. Retrieved 6 May 2016.
- ^ Wade, Mark. "Soyuz". Encyclopedia Astronautica. Archived from the original on 2010-01-17. Retrieved 2009-04-16.