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H-1
Credit - Boeing / Rocketdyne
Engine Model: H-1. Manufacturer Name: H-1. Designer: Rocketdyne. Developed in: 1958. Propellants: Lox/Kerosene. Thrust(vac): 947.700 kN (213,051 lbf). Thrust(sl): 836.200 kN (187,985 lbf). Isp: 289 sec. Isp (sea level): 255 sec. Burn time: 150 sec. Mass Engine: 635 kg (1,399 lb). Diameter: 0.82 m (2.67 ft). Length: 2.13 m (6.98 ft). Chambers: 1. Chamber Pressure: 40.00 bar. Area Ratio: 8.00. Oxidizer to Fuel Ratio: 2.23. Thrust to Weight Ratio: 152.20. Country: USA. First Flight: 1961. Last Flight: 1965. Flown: 80.

Saturn l/lB. Designed for booster applications. Gas generator, pump-fed.

Engine Model: H-1-3. Designer: Nissan. Propellants: Solid. Thrust(vac): 77.000 kN (17,310 lbf). Isp: 291 sec. Isp (sea level): 220 sec. Burn time: 68 sec. Diameter: 1.34 m (4.39 ft). Length: 2.34 m (7.67 ft). Chambers: 1. Country: Japan. First Flight: 1986. Last Flight: 1992. Flown: 9.00.

Engine Model: H-1b. Designer: Rocketdyne. Propellants: Lox/Kerosene. Thrust(vac): 1,030.200 kN (231,598 lbf). Thrust(sl): 911.900 kN (205,003 lbf). Isp: 296 sec. Isp (sea level): 262 sec. Burn time: 155 sec. Mass Engine: 988 kg (2,178 lb). Diameter: 0.82 m (2.67 ft). Length: 2.20 m (7.20 ft). Chambers: 1. Chamber Pressure: 48.00 bar. Area Ratio: 8.00. Thrust to Weight Ratio: 106.33. Country: USA. First Flight: 1966. Last Flight: 1975. Flown: 72.

Engine Model: H-1c. Designer: Rocketdyne. Propellants: Lox/Kerosene. Thrust(vac): 1,130.000 kN (254,030 lbf). Isp: 296 sec. Isp (sea level): 262 sec. Burn time: 128 sec. Chambers: 1. Country: USA. Status: Study 1965.

H-1 used on Rocket Stages
Bibliography:

  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
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