Rocket Engine, Liquid Fuel, for Jupiter Missile

Rocket Engine, Liquid Fuel, for Jupiter Missile

     

This is the liquid propellant Jupiter rocket engine that powered the U.S.'s first intermediate ballistic missile (IRBM), the Jupiter, of 1,600 miles range. It was a modification of the Redstone rocket engine and used liquid oxygen and RP-1 (a type of kerosene). The engine produced 150,000 lbs of thrust. The Jupiter missile became operational in 1960 and retired from the military service in 1963. This engine was transferred to the Smithsonian in 1970 from the NASA Marshall Space Flight Center.

Transferred from NASA/Marshall Space Flight Center

Country of Origin
United States of America

Manufacturer
Rocketdyne Division, Rockwell International Corporation

Date
ca. 1956-1963

Type
PROPULSION-Rocket Engines

Materials
Primarily stainless steel; some aluminum piping
Dimensions
Overall: 68 in. diameter x 120 in. long, approximate weight 4400 lb. (172.72 cm. diameter x 304.8 cm, long approximate weight 1995.8 kg)

This is the liquid propellant Jupiter rocket engine that powered the U.S.'s first intermediate ballistic missile (IRBM), the Jupiter, of 1,600 miles range. It was a modification of the Redstone rocket engine and used liquid oxygen and RP-1 (a type of kerosene). The engine produced 150,000 lbs of thrust. The Jupiter missile became operational in 1960 and retired from the military service in 1963. This engine was transferred to the Smithsonian in 1970 from the NASA Marshall Space Flight Center.

Transferred from NASA/Marshall Space Flight Center

Country of Origin
United States of America

Manufacturer
Rocketdyne Division, Rockwell International Corporation

Date
ca. 1956-1963

Type
PROPULSION-Rocket Engines

Materials
Primarily stainless steel; some aluminum piping
Dimensions
Overall: 68 in. diameter x 120 in. long, approximate weight 4400 lb. (172.72 cm. diameter x 304.8 cm, long approximate weight 1995.8 kg)

ID: A19700263000