Soyuz-L

Summary

Soyuz-L
FunctionCarrier rocket
ManufacturerOKB-1
Country of originSoviet Union
Size
Height50 metres (160 ft)
Diameter10.3 metres (34 ft)
Mass300,000 kilograms (660,000 lb)
StagesTwo
Capacity
Payload to LEO
Mass5,500 kilograms (12,100 lb)
Associated rockets
FamilyR-7
Launch history
StatusRetired
Launch sitesBaikonur Site 31/6
Total launches3[1]
Success(es)3
First flight24 November 1970
Last flight12 August 1971
Notable payloadsLK
Boosters
No. boosters4
Engines1 RD-107-8D728
Thrust995 kilonewtons (224,000 lbf)
Specific impulse314 sec
Burn time119 seconds
FuelRP-1/LOX
First stage
Engines1 RD-108-8D727
Thrust977 kilonewtons (220,000 lbf)
Specific impulse315 sec
Burn time291 seconds
FuelRP-1/LOX
Second stage
Engines1 RD-0110
Thrust294 kilonewtons (66,000 lbf)
Specific impulse330 sec
Burn time246 seconds
FuelRP-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

  1. ^ a b Krebs, Gunter. "Soyuz-L (11A511L)". Gunter's space page. Retrieved 6 May 2016.
  2. ^ Wade, Mark. "Soyuz". Encyclopedia Astronautica. Archived from the original on 2010-01-17. Retrieved 2009-04-16.