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 (12,000 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. The Soyuz-L made its maiden flight in 1970, and was retired in 1971, having made three launches. All three launches were successful. The later Soyuz-U used a similar configuration to the Soyuz-L.