H-1

H-1
Credit - Boeing / Rocketdyne

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.

H-1 used on Rocket Stages

Used on stage: Saturn I. on launch vehicle: Juno V-A.

Used on stage: Saturn I. on launch vehicle: Juno V-B.

Used on stage: Saturn I. on launch vehicle: Saturn A-1.

Used on stage: Saturn I. on launch vehicle: Saturn C-2.

Used on stage: Saturn I. on launch vehicle: Saturn I.

Bibliography and Further Reading

Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993. ISBN: 5060025632. Russian-language textbook on rocket theory. More at amazon.com...

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