Jupiter-A
 Takeoff of Jupiter-A CC-39 | |
| Manufacturer | Redstone Arsenal, Chrysler |
|---|---|
| Country of origin | United States |
| Size | |
| Height | 69.50 feet (21.18 m) |
| Diameter | 5.83 feet (1.78 m) |
| Mass | 64,060 pounds (29,060 kg) |
| Stages | 1 |
| Capacity | |
| Payload to Low Earth Orbit | |
| Mass | 11 kg (24 lb) |
| Launch history | |
| Status | Retired |
| Launch sites | LC-5 and 6, Cape Canaveral Missile Annex, Florida |
| Total launches | 25 |
| First flight | 1955-09-22 |
| Last flight | 1958-06-12 |
| First stage – Redstone | |
| Powered by | 1 North American Aviation (Rocketdyne) 75-110 A-3, A-4, A-6 |
| Maximum thrust | 91,350 lbf; 406.33 kN (41,434 kgf) |
| Specific impulse | 265 s (2.60 km/s) |
| Burn time | 155 s |
| Propellant | LOX/Ethanol, LOX/Hydyne |
The Jupiter-A was an American sounding rocket and test vehicle derived from the Redstone ballistic missile, developed in the mid-1950s by Redstone Arsenal and Chrysler. It was the first variant of the Redstone to fly, and served as a testbed for components intended for use in the PGM-19 Jupiter medium-range ballistic missile (MRBM).
Components tested aboard Jupiter-A flights included the Redstone ST-80 inertial guidance platform, Jupiter angle-of-attack sensors, warhead fuzing systems, and explosive bolts. The vehicle stood 21.20 metres (69.6 ft) tall with a diameter of 1.78 metres (5.8 ft).
A total of twenty-five launches were conducted from Cape Canaveral Air Force Station, Florida, using Launch Complexes 5 and 6, between September 1955 and June 1958.