Lox/Alcohol propellant rocket stage. Loaded/empty mass 28,440/3,125 kg. Thrust 414.34 kN. Vacuum specific impulse 265 seconds. Used for Jupiter-C satellite missions, and greatly modified, for Mercury manned positions. For Jupiter-C missions, used Hydyne fuel, which was toxic but increased specific impulse.
Cost $ : 4.930 million.
Status: Out of Production.
More... - Chronology...
Gross mass: 28,440 kg (62,690 lb).
Unfuelled mass: 3,125 kg (6,889 lb).
Height: 17.58 m (57.67 ft).
Diameter: 1.77 m (5.80 ft).
Span: 4.19 m (13.74 ft).
Thrust: 414.34 kN (93,147 lbf).
Specific impulse: 265 s.
Specific impulse sea level: 235 s.
Burn time: 155 s.
Number: 44 .
A-7 Rocketdyne Lox/Hydyne rocket engine. 416.2 kN. Out of Production. Version of Redstone engine for Jupiter-C test vehicle, with Hydyne fuel and 140 seconds burn time. Flew 1956-1959. Gas generator, pump-fed. Thrust 370 kN at sea level. Isp=265s. More...
Associated Launch Vehicles
Redstone MRLV American suborbital launch vehicle. Greatly modified Redstone rocket used to launch the Mercury manned spacecraft on a suborbital trajectory, typically 380 km downrange, 220 km altitude, and a speed of 6800 kph. More...
Lox/Alcohol Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Alcohol (C2H5OH) was the fuel used for the German V-2 rocket, and the first derivative rocket engines in the United States, Soviet Union, and China used it as well. Better performance was achieved by increasing the alcohol concentration in the post-war engines. But after better-performance rocket-grade kerosene was developed by Rocketdyne in the REAP program of 1953, use of alcohol was abandoned. More...
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