This article needs additional citations for verification. Please help improve this article by adding citations to reliable sources. Unsourced material may be challenged and removed.Find sources: "Soyuz-L" – news · newspapers · books · scholar · JSTOR (December 2009) (Learn how and when to remove this message)
FunctionCarrier rocket
Country of originSoviet Union
Height50 metres (160 ft)
Diameter10.3 metres (34 ft)
Mass300,000 kilograms (660,000 lb)
Payload to LEO
Mass5,500 kilograms (12,100 lb)
Associated rockets
Launch history
Launch sitesBaikonur Site 31/6
Total launches3[1]
First flight24 November 1970
Last flight12 August 1971
Type of passengers/cargoLK
No. boosters4
Powered by1 RD-107-8D728
Maximum thrust995 kilonewtons (224,000 lbf)
Specific impulse314 sec
Burn time119 seconds
First stage
Powered by1 RD-108-8D727
Maximum thrust977 kilonewtons (220,000 lbf)
Specific impulse315 sec
Burn time291 seconds
Second stage
Powered by1 RD-0110
Maximum thrust294 kilonewtons (66,000 lbf)
Specific impulse330 sec
Burn time246 seconds

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.


  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 2010-01-07. Retrieved 2009-04-16.