This page no longer updated from 31 October 2001. Latest version can be found at H-1b

Designer: Rocketdyne. Used on stages: Saturn IB, Saturn IB-11, Saturn IB-15, Saturn S-1B-4 H-1. Used on launch vehicles: Saturn A-2, Saturn B-1, Saturn IB, Saturn IB-C, Saturn IB-CE, Saturn IB-D, Saturn INT-11, Saturn INT-12, Saturn INT-13, Saturn INT-14, Saturn INT-15. Propellants: Lox/Kerosene Thrust(vac): 105,053 kgf. Thrust(vac): 1,030.20 kN. Isp: 296 sec. Isp (sea level): 262 sec. Burn time: 155 sec. Mass Engine: 988 kg. Diameter: 0.8 m. Length: 2.2 m. Chambers: 1. Chamber Pressure: 48.00 bar. Area Ratio: 8.00. Thrust to Weight Ratio: 106.33. Country: USA. Status: Out of Production. First Flight: 1966. Last Flight: 1975. Flown: 72.
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Last update 12 March 2001.
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© Mark Wade, 2001 .