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H-1 -

Credit: Boeing / Rocketdyne. 9,616 bytes. 164 x 235 pixels.

Manufacturer Name: H-1. Designer: Rocketdyne. Developed in: 1958. Application: . Used on stages: Saturn I. Used on launch vehicles: Juno V-A, Juno V-B, Saturn A-1, Saturn C-2, Saturn I. Propellants: Lox/Kerosene Thrust(vac): 96,645 kgf. Thrust(vac): 947.70 kN. Isp: 289 sec. Isp (sea level): 255 sec. Burn time: 150 sec. Mass Engine: 635 kg. Diameter: 0.8 m. Length: 2.1 m. 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. Status: Out of Production. First Flight: 1961. Last Flight: 1965. Flown: 80. References: 225 . Comments: Saturn l/lB. Designed for booster applications. Gas generator, pump-fed.
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Last update 12 March 2001.
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