Usage Conditions May Apply Usage Conditions Apply There are restrictions for re-using this media. For more information, visit the Smithsonian's Terms of Use page. IIIF provides researchers rich metadata and image viewing options for comparison of works across cultural heritage collections. More - https://iiif.si.edu View Manifest View in Mirador Viewer Usage Conditions May Apply Usage Conditions Apply There are restrictions for re-using this media. For more information, visit the Smithsonian's Terms of Use page. IIIF provides researchers rich metadata and image viewing options for comparison of works across cultural heritage collections. More - https://iiif.si.edu View Manifest View in Mirador Viewer Usage Conditions May Apply Usage Conditions Apply There are restrictions for re-using this media. For more information, visit the Smithsonian's Terms of Use page. IIIF provides researchers rich metadata and image viewing options for comparison of works across cultural heritage collections. More - https://iiif.si.edu View Manifest View in Mirador Viewer Usage Conditions May Apply Usage Conditions Apply There are restrictions for re-using this media. For more information, visit the Smithsonian's Terms of Use page. IIIF provides researchers rich metadata and image viewing options for comparison of works across cultural heritage collections. More - https://iiif.si.edu View Manifest View in Mirador Viewer

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 used RP-1 (kerosene) and liquid oxygen as fuel. The Saturn 1 first flew in 1961 while the last Saturn 1B was flown in 1975 for the Apollo-Soyuz Test Project. The Rocketdyne Division of Rockwell International donated this engineering model to the Smithsonian Institution in 1976.

 Display Status

This object is not on display at the National Air and Space Museum. It is either on loan or in storage.
Object Details
Date ca. 1958-1975 Country of Origin United States of America Type PROPULSION-Rocket Engines Manufacturer Rocketdyne Division, Rockwell International
 Dimensions Overall: 100 in. long x 47 in. diameter (254 x 119.38cm)
 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.
 Inventory Number A19760772000 Credit Line Gift of the Rocketdyne Division of Rockwell International Data Source National Air and Space Museum Restrictions & Rights Usage conditions apply
For more information, visit the Smithsonians Terms of Use.