Soyuz-L
Soyuz-L
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 |
5,500 kilograms (12,100 lb) |
Associated rockets |
Family |
R-7 |
Launch history |
Status |
Retired |
Launch sites |
Baikonur Site 31/6 |
Total launches |
3 |
Successes |
3 |
First flight |
24 November 1970 |
Last flight |
12 August 1971 |
Notable payloads |
LK |
Boosters |
No boosters |
4 |
Engines |
1 RD-107-8D728 |
Thrust |
995 kilonewtons (224,000 lbf) |
Specific impulse |
314 sec |
Burn time |
119 seconds |
Fuel |
RP-1/LOX |
First Stage |
Engines |
1 RD-108-8D727 |
Thrust |
977 kilonewtons (220,000 lbf) |
Specific impulse |
315 sec |
Burn time |
291 seconds |
Fuel |
RP-1/LOX |
Second Stage |
Engines |
1 RD-0110 |
Thrust |
294 kilonewtons (66,000 lbf) |
Specific impulse |
330 sec |
Burn time |
246 seconds |
Fuel |
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 used for tests of the LK Lunar lander in low Earth orbit, as part of the Soviet lunar programme.
The Soyuz-L was essentially a two-stage derivative of the Molniya-M, itself derived from the original Soyuz. It featured the reinforced first stage and boosters used to provide support for the Molniya's third stage, allowing it to carry a larger and more massive payload. A larger payload fairing was also fitted, to accommodate the LK spacecraft.[1] The Soyuz-L made its maiden flight in 1970, and was retired in 1971, having made three launches. All three launches were successful.[1] The later Soyuz-U used a similar configuration to the Soyuz-L.
References
- ↑ 1.0 1.1 Wade, Mark. "Soyuz". Encyclopedia Astronautica. Retrieved 2009-04-16.
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