As to other missile vital statistics, the JUPITER was a single-stage, liquid-propelled, rocket-powered ballistic missile, designed to carry a 1,600-pound payload to a maximum range of 1,500 nautical miles, with a 1,500- meter circular probable error (CPE). It was composed of three major assemblies: the nose cone, the aft unit with instrument group, and the thrust unit. Structural loads were divided between the missile skin and a number of Z-ring stiffeners. The ablative heat- protected nose cone contained the warhead, fuzing and arming device, and related power equipment. G&C was housed in the aft unit, with the exception of such components as the swiveling actuators for the main rocket engine. Vernier engine spin rockets and jet nozzles for spatial attitude control were also located in the aft unit. When the nose cone and aft unit were joined, it became the missile body. The thrust unit was made up of a center unit containing the propellant tanks and lines, the rocket engine, and the tail section. The tail section also contained cabling and propulsion system accessories 63 . Propulsion of the JUPITER was accomplished by an NAA rocket engine (NAA-150-200-S-3D) rated at 150,000 pounds of thrust. Fuels used were liquid oxygen (L0X) as the oxidizer and kerosene or RP-1 as the propellant. The engine was mounted on gimbals which allowed a pitch or yaw movement up to plus or minus seven degrees. This action was produced by an electro- hydraulic actuator system which received its signals from the G&C system. Propellants were fed to the main engine by two turbine-operated pumps, which operated on a gas produced in a LOX-RP-1 gas generator. The generator was fueled from the main propellant tanks. _____________________________

63. Standard Msl Characteristics, SM-78B JUPITER, released by auth Secy AF, 16 May 60; SACOP 1-58, 4 Mar 58, Hist Off files.