S1.5400 home
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Engine Model: 8D726. Government Designation: 8D726. Designer: Korolev. Application: GR-1 Stage 3, N-11GR - V. Propellants: Lox/Kerosene. Thrust(vac): 66.700 kN (14,995 lbf). Isp: 350 sec. Burn time: 380 sec. Chambers: 1. Country: Russia.

Development based on S1.5400.

Engine Model: S1.5400. Government Designation: 11D33. Other Designations: S1.5400. Designer: Korolev. Developed in: 1958-60. Application: Molniya 8K78-3. Propellants: Lox/Kerosene. Thrust(vac): 66.700 kN (14,995 lbf). Isp: 340 sec. Burn time: 207 sec. Mass Engine: 153 kg (337 lb). Chambers: 1. Chamber Pressure: 53.50 bar. Thrust to Weight Ratio: 43.59. Country: Russia. First Flight: 1960. Last Flight: 1965. Flown: 26.

Originally designed by Korolev; passed to Isayev for production. Began a series of engines leading through the 8D726 for GR-1 to the Block D for the N1 and Proton. Earliest versions with 6380 kgf and 338.5 sec specific impulse.

Engine Model: 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.

S1.5400 used on Rocket Stages
  • Used on stage: Block L. on launch vehicle: N1.
S1.5400 used on Spacecraft
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