Object Details
Manufacturer
Rocketdyne Division, Rockwell International (CA)
Summary
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.
Credit Line
Transferred from NASA/Marshall Space Flight Center
Date
ca. 1956-1963
Inventory Number
A19700263000
Restrictions & Rights
Usage conditions apply
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)
Country of Origin
United States of America
See more items in
National Air and Space Museum Collection
Data Source
National Air and Space Museum
Link to Original Record
Record ID
nasm_A19700263000