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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. 1inSamara, Russia. It was created to test the LK lunar landerinlow Earth orbit, as part of the Soviet lunar programme.
| 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 | |
| Mass | 5,500 kilograms (12,100 lb) |
| Associated rockets | |
| Family | R-7 |
| Launch history | |
| Status | Retired |
| Launch sites | Baikonur Site 31/6 |
| Total launches | 3[1] |
| Success(es) | 3 |
| First flight | 24 November 1970 |
| Last flight | 12 August 1971 |
| Type of passengers/cargo | LK |
| Boosters | |
| No. boosters | 4 |
| Powered by | 1RD-107-8D728 |
| Maximum thrust | 995 kilonewtons (224,000 lbf) |
| Specific impulse | 314 sec |
| Burn time | 119 seconds |
| Propellant | RP-1/LOX |
| First stage | |
| Powered by | 1RD-108-8D727 |
| Maximum thrust | 977 kilonewtons (220,000 lbf) |
| Specific impulse | 315 sec |
| Burn time | 291 seconds |
| Propellant | RP-1/LOX |
| Second stage | |
| Powered by | 1RD-0110 |
| Maximum thrust | 294 kilonewtons (66,000 lbf) |
| Specific impulse | 330 sec |
| Burn time | 246 seconds |
| Propellant | RP-1/LOX |
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.
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