S2.1150
Burya engine
Credit - Lavochkin
Other Designations: S2.1150. Designer: Isayev. Developed in: 1953-59. Application: Burya booster. Propellants: Nitric acid/Amine. Thrust(vac): 671.200 kN (150,892 lbf). Isp: 250 sec. Isp (sea level): 218 sec. Burn time: 70 sec. Mass Engine: 650 kg (1,430 lb). Diameter: 1.21 m (3.96 ft). Length: 1.87 m (6.13 ft). Chambers: 4. Chamber Pressure: 53.00 bar. Thrust to Weight Ratio: 105.29. Country: Russia. Status: Out of production. First Flight: 1957. Last Flight: 1960. Flown: 36.

Booster engine for Burya missile. Two used to boost ramjet second stage to ignition conditions. Engines developed by Isayev from R-11 S2.253 engine. Early Buryas had S2.1100 engine. Two thrust levels. 671,20 / 477 kN sea-level. While Glushko found the nitric acid/kerosene combination acceptable for the Buran cruise missile / RD-212 application, Isayev turned to a different combination for his booster for the competing Burya missile booster. Isayev tested nitric acid with many fuels, including amines, before finally selecting hydrazine. Cluster testing of Isayev's engine was also conducted with TM-185 turpentine. Stand tests began with four prototypes in March 1957 at NII-229 Zagorsk.

S2.1150 used on Rocket Stages

Bibliography and Further Reading
  • Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
 
 
 
 
 
 
 
 
 
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