Date: ca. 1956-1963
Country of Origin: United States of America
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)
Materials:
Primarily stainless steel; some aluminum piping
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
