Jupiter IRBM Specifications

Length: 60 feet
Diameter: 8 feet, 9 inches
Weight: 108,804 pounds (fully fueled)
Fuel: Rocket grade RP-1 (kerosene)
Oxidizer: Liquid oxygen
Propulsion: A single S-3D engine generating 150,000 pounds of thrust
Range: 1,500 miles
Guidance: All-inertial
Accuracy: 1,500 meters
Reentry vehicle: Mark 3-ablative
Warhead: W-49, 1.44 megaton yield

Airframe: Prototypes were built by the Army Ballistic Missile Agency, Redstone Arsenal, Huntsville, Alabama. Full-scale production was by the Chrysler Corporation Ballistic Missile Division, Detroit, Michigan. Propulsion: Rocketdyne Division of North American Aviation, Canoga Park, California Guidance: Ford Instrument Company, Long Island City, New York Reentry vehicle: General Electric, Saratoga, New York

Jupiter was originally designed for shipboard use, and adapting a liquid-fuel missile to operate in that environment posed a host of challenges. For example, the Army initially proposed building a missile over 90 feet long, while the Navy wanted a 50-foot missile. After some discussion they compromised on a missile that was 60 feet long and 105 inches in diameter.