Rocket Engine, Liquid Fuel, XLR-AJ-87-1, Gemini Booster, E type

Rocket Engine, Liquid Fuel, XLR-AJ-87-1, Gemini Booster, E type

     

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.

Gift of Aeroject Solid Propulsion Company

Country of Origin
United States of America

Manufacturer
Aerojet General Corp.

Date
ca. 1965-1966

Type
PROPULSION-Rocket Engines

Materials
stainless steel, with some aluminum alloy piping
Dimensions
Overall: 10 ft. long x 7 ft. 8 in. diameter (304.8 x 233.68cm)

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.

Gift of Aeroject Solid Propulsion Company

Country of Origin
United States of America

Manufacturer
Aerojet General Corp.

Date
ca. 1965-1966

Type
PROPULSION-Rocket Engines

Materials
stainless steel, with some aluminum alloy piping
Dimensions
Overall: 10 ft. long x 7 ft. 8 in. diameter (304.8 x 233.68cm)

ID: A19710848000