Rocket Engine, Liquid Fuel, S-3D for Jupiter Missile

Rocket Engine, Liquid Fuel, S-3D for Jupiter Missile

     

Developed in the 1950s, the S-3 D Jupiter engine powered the U.S.'s first intermediate range (1600 miles) ballistic missile (IRBM). A modification of the Redstone engine, the Jupiter engine, which operated on liquid oxygen and RP-1 (a type of kerosene), produced 150,000 lbs of thrust for 178 seconds. The Jupiter missile itself was 58 feet (17.7 m) long, 8.75 feet (2.7 m) in diameter, and weighed 110,000 lbs (49,900 kg).

NASA transferred this engine to the Museum in 1969.

Transferred from the National Aeronautics and Space Administration

Country of Origin
United States of America

Manufacturer
Rocketdyne Division, Rockwell International Corporation

Date
1958

Type
PROPULSION-Rocket Engines

Materials
Metal. mainly stainless steel; pumps, aluminum and magnesium alloys; piping, some aluminum, some wrapped with asbestos
Dimensions
Overall: 5ft 2in. x 5ft 2in. x 10ft 8in., 2084lb. (157.48 x 157.48 x 325.12cm, 945.3kg)

Developed in the 1950s, the S-3 D Jupiter engine powered the U.S.'s first intermediate range (1600 miles) ballistic missile (IRBM). A modification of the Redstone engine, the Jupiter engine, which operated on liquid oxygen and RP-1 (a type of kerosene), produced 150,000 lbs of thrust for 178 seconds. The Jupiter missile itself was 58 feet (17.7 m) long, 8.75 feet (2.7 m) in diameter, and weighed 110,000 lbs (49,900 kg).

NASA transferred this engine to the Museum in 1969.

Transferred from the National Aeronautics and Space Administration

Country of Origin
United States of America

Manufacturer
Rocketdyne Division, Rockwell International Corporation

Date
1958

Type
PROPULSION-Rocket Engines

Materials
Metal. mainly stainless steel; pumps, aluminum and magnesium alloys; piping, some aluminum, some wrapped with asbestos
Dimensions
Overall: 5ft 2in. x 5ft 2in. x 10ft 8in., 2084lb. (157.48 x 157.48 x 325.12cm, 945.3kg)

ID: A19700262000