Rocket Engine, Liquid Fuel, H-1A

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    Rocket Engine, Liquid Fuel, H-1A

    Bell-shaped nozzle with attached slightly tapering combustion chamber on top, with adjoining pumps and associated plumbing fixed on one side and top of combustion chamber. Nozzle with longitudinally placed nickel alloy cooling tubes with 10 equi-distant support bands around nozzle, plus one rim band. Steel thrust chamber.

    1 of 4

    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

    Rocket Engine, Liquid Fuel, H-1A

    Bell-shaped nozzle with attached slightly tapering combustion chamber on top, with adjoining pumps and associated plumbing fixed on one side and top of combustion chamber. Nozzle with longitudinally placed nickel alloy cooling tubes with 10 equi-distant support bands around nozzle, plus one rim band. Steel thrust chamber.

    2 of 4

    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

    Rocket Engine, Liquid Fuel, H-1A

    Bell-shaped nozzle with attached slightly tapering combustion chamber on top, with adjoining pumps and associated plumbing fixed on one side and top of combustion chamber. Nozzle with longitudinally placed nickel alloy cooling tubes with 10 equi-distant support bands around nozzle, plus one rim band. Steel thrust chamber.

    3 of 4

    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

    Rocket Engine, Liquid Fuel, H-1A

    Bell-shaped nozzle with attached slightly tapering combustion chamber on top, with adjoining pumps and associated plumbing fixed on one side and top of combustion chamber. Nozzle with longitudinally placed nickel alloy cooling tubes with 10 equi-distant support bands around nozzle, plus one rim band. Steel thrust chamber.

    4 of 4

Display Status:

This object is not on display at the National Air and Space Museum. It is either on loan or in storage.

The H-1 liquid-fuel rocket engine was the first stage powerplant 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. The model shown here appears to be the second variation which produced 188,000 pounds of thrust.

The H-1 was evolved directly from the Jupiter missile's engine. In 1958, during the earliest days of the Space Race, the Army Ballistic Missile Agency proposed a large launch vehicle for lifting military satellites. This vehicle was known as the Juno V. In its final configuration its first stage was to be powered by eight uprated Jupiter engines which were subsequently named the H-1 engine. With the approval of the Apollo Project to land men on the Moon, the Juno V was re-designated the Saturn. The Saturn 1 and Saturn 1B were successfully test flown with the H-1's and led the way to the Saturn V. The Saturn 1, with its eight H-1's, first flew on 27 October 1961 while the last Saturn 1B was flown on 15 July 1975 for the low-Earth orbit Apollo-Soyuz Test Project.