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Catalog Data

Manufacturer:
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: 75 in. tall x 98 in. long x 47 in. diameter, 1870 lb. (190.5 x 248.92 x 119.38cm, 848.2kg)
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, the rocket that propelled astronauts 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.
The H-1 was evolved directly from Army Ballistic Missile Agency projects, specifically the Jupiter and Juno V - later 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's Marshall Space Flight Center transferred this H-1 engine to the Smithsonian Institution in 1970.
Credit Line:
Transferred from the National Aeronautics and Space Administration
Inventory Number:
A19700284000
Restrictions & Rights:
Usage conditions apply
See more items in:
National Air and Space Museum Collection
Data Source:
National Air and Space Museum
GUID:
http://n2t.net/ark:/65665/nv93451a5c4-6eb9-4a09-8e69-97c3c8154c72
EDAN-URL:
edanmdm:nasm_A19700284000