Hyperion Interplanetary Spacecraft
Credit: © Mark Wade
American nuclear-powered orbital launch vehicle. Hyperion was considered in 1958 as a ca. 1970 Saturn follow-on. It used a small jettisonable chemical booster stage that contained chemical engines and the LOX oxidizer for the conventional engines.
This booster stage surrounded the nuclear core vehicle with its large liquid hydrogen tank. The conventional stage would draw fuel from the main hydrogen tank until burnout. Hyperion would have doubled the translunar trajectory performance of the Saturn V and less than one third of the liftoff mass.
LEO Payload: 145,000 kg (319,000 lb) to a 485 km orbit at 28.00 degrees. Payload: 82,000 kg (180,000 lb) to a earth escape.
Status: Study 1959.
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Gross mass: 850,000 kg (1,870,000 lb).
Payload: 145,000 kg (319,000 lb).
Height: 85.40 m (280.10 ft).
Diameter: 8.54 m (28.01 ft).
Thrust: 10,700.00 kN (2,405,400 lbf).
Apogee: 485 km (301 mi).
Associated Manufacturers and Agencies
Convair American manufacturer of rockets, spacecraft, and rocket engines. Convair, USA. More...
Koelle, Heinz Hermann,, Handbook of Astronautical Engineering, McGraw-Hill,New York, 1961.
Hyperion Booster Lox/LH2 propellant rocket stage. Loaded/empty mass 394,625/18,144 kg. Thrust 13,700.00 kN. Vacuum specific impulse 457 seconds. More...
Hyperion Sustainer Nuclear/LH2 propellant rocket stage. Loaded/empty mass 453,592/110,000 kg. Thrust 5,782.68 kN. Vacuum specific impulse 800 seconds. More...
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