Soyuz-L

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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 (Stage 0)
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[edit]

  1. ^ a b Wade, Mark. "Soyuz". Encyclopedia Astronautica. Retrieved 2009-04-16.