Rocketdyne Division, Rockwell International Search this
Materials:
Chamber and nozzle coolant passages 347 stainless steel. Propellant tanks, lines, and valves, stainless steel. Pumps, aluminum alloys; turbine, Hastealloy. Injector, OHFC copper and 347 stainless steel.
Combustion chamber made of 292 stainless steel tubes. The assembly, except for inlet manifold, was furnaced brazed with gold brazing alloy. Injectors, furnaced brazed.
Dimensions:
Overall: 100 in. long x 47 in. diameter (254 x 119.38cm)
Type:
PROPULSION-Rocket Engines
Country of Origin:
United States of America
Date:
ca. 1958-1975
Summary:
The H-1 liquid-fuel rocket engine was the first stage power plant for the Saturn 1 and Saturn 1B launch vehicles, the precursors to the Saturn V which took men to the Moon in the Apollo program. The Saturn 1 and Saturn 1B were each fitted with eight H-1 engines in their first stages. The engine uses RP-1 (kerosene) and liquid oxygen for this model's 188,000 pounds of thrust.
The H-1 was evolved directly from Army Ballistic Missile Agency projects, specifically the Jupiter and Juno V. With the approval of the Apollo Project, the Juno V was re-designated the Saturn. The successful launches of the Saturn 1 and Saturn 1B led the way to the Saturn V. The Saturn 1, with its eight H-1's, first flew on October 27, 1961, while the last Saturn 1B was flown on July 15, 1975, for the Apollo-Soyuz Test Project.
NASA transferred this H-1 engine to the Smithsonian Institution in 1980.
Credit Line:
Transferred from the National Aeronautics and Space Administration
