S1.5400A Government Designation: 11D33M. Other Designations: S1.5400A. Designer: Korolev. Developed in: 1961-64. Application: Molniya 8K78M-3. Propellants: Lox/Kerosene. Thrust(vac): 67.300 kN (15,130 lbf). Isp: 342 sec. Burn time: 200 sec. Mass Engine: 148 kg (327 lb). Chambers: 1. Chamber Pressure: 54.00 bar. Thrust to Weight Ratio: 46.25. Country: Russia. First Flight: 1964. Last Flight: 2006. Flown: 294. S1.5400A used on Rocket Stages Used on stage: Molniya 8K78M-3. on launch vehicle: Kvant-1. Used on stage: Molniya 8K78M-3. on launch vehicle: Molniya 8K78M. S1.5400A used on Spacecraft Used on: Block L Molniya 8K78M. Bibliography and Further Reading Varfolomyev, Timothy, Spaceflight, "Soviet Rocketry that Conquered Space - Part 5", 1998, Volume 40, page 85. 1: Sp 95/37-260; Sp 96/38-31 (8K71 launches); 2: Sp 96/38-48; 3: Sp 96/38-206; Sp 96/38-317 (designatons); 4: Sp 98/40-28; 5:Sp 98/40-85                   Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2007 except where otherwise noted.

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