Multiple-source solid rocket engine. 6.660 kN. Out of Production. Used in Jupiter C, Juno 2. Isp=235s. First flight 1956.
Thrust (sl): 6.073 kN (1,365 lbf). Thrust (sl): 619 kgf. Propellant Formulation: Polysulfide.
Status: Out of Production.
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Gross mass: 42 kg (92 lb).
Unfuelled mass: 21 kg (46 lb).
Height: 1.00 m (3.20 ft).
Diameter: 0.30 m (0.98 ft).
Thrust: 6.66 kN (1,497 lbf).
Specific impulse: 235 s.
Specific impulse sea level: 214 s.
Burn time: 6.00 s.
Number: 285 .
Associated Launch Vehicles
Jupiter C American orbital launch vehicle. Re-entry vehicle test booster and satellite launcher derived from Redstone missile. The Jupiter A version of the Redstone missile was modified with upper stages to test Jupiter re-entry vehicle configurations. Von Braun's team was ordered to ballast the upper stage with sand to prevent any 'inadvertent' artificial satellites from stealing thunder from the official Vanguard program. Korolev's R-7 orbited the first earth satellite instead. The Jupiter C was retroactively named the 'Juno I' by Von Braun's team. More...
Juno II American orbital launch vehicle. Satellite launcher derived from Jupiter IRBM. Basic 4 stage vehicle consisted of 1 x Jupiter + 1 x Cluster stage 2 + 1 x Cluster stage 3 + 1 x RTV Motor More...
Solid Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. Solid propellants have the fuel and oxidiser embedded in a rubbery matrix. They were developed to a high degree of perfection in the United States in the 1950's and 1960's. In Russia, development was slower, due to a lack of technical leadership in the area and rail handling problems. More...
Sergeant Solid propellant rocket stage. Loaded/empty mass 42/21 kg. Thrust 6.66 kN. Vacuum specific impulse 235 seconds. More...
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