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

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Object Details

Manufacturer

Rocketdyne Division, Rockwell International (CA)

Summary

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.

Credit Line

Transferred from the National Aeronautics and Space Administration

Date

1958

Inventory Number

A19700262000

Restrictions & Rights

Usage conditions apply

Type

PROPULSION-Rocket Engines

Materials

HAZ MAT: Asbestos

HAZ MAT: Thoriated Magnesium

Ferrous Alloy

Aluminum Alloy

Rubber

Copper Alloy

Electrical Wiring

Dimensions

3-D (Approximate): 398.8 × 190.5 × 205.7cm (13 ft. 1 in. × 6 ft. 3 in. × 6 ft. 9 in.)

Country of Origin

United States of America

See more items in

National Air and Space Museum Collection

Data Source

National Air and Space Museum

Metadata Usage

Not determined

Link to Original Record

http://n2t.net/ark:/65665/nv9bcbacdcf-3f04-4236-9534-250c083419bb

Record ID

nasm_A19700262000