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

This is the Titan II missile engine as adapted to launch the Gemini manned spacecraft. The original Titan I liquid-fuel engine powered the first stage of the two-stage Titan I intercontinental ballistic missile (ICBM). It had two identical separate engine chamber assemblies, each generating 150,300 pounds of thrust, or 300,600 pounds total. The propellants were liquid oxygen (lox) and RP-1, a type of kerosene. This engine was donated to the Smithsonian by the Aerojet-General Corp. in 1971.

 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. 1965-1966 Country of Origin United States of America Type PROPULSION-Rocket Engines Manufacturer Aerojet General Corp.
 Dimensions Overall: 10 ft. long x 7 ft. 8 in. diameter (304.8 x 233.68cm)
 Materials stainless steel, with some aluminum alloy piping
 Inventory Number A19710848000 Credit Line Gift of Aeroject Solid Propulsion Company Data Source National Air and Space Museum Restrictions & Rights Usage conditions apply
For more information, visit the Smithsonians Terms of Use.