American space tug. Study 1965. Upper stage / space tug - Douglas study, 1965. Launched by Saturn V. S-IVB with 315 k high pressure 3000 psia engine, 350,000 pounds propellant
Designation for high-performance high-pressure chamber Lox/LH2 engine developed from J-2. Considered for upgrades to Saturn V launch vehicle upper stages. Technology led to Space Shuttle Main Engines.
Gross mass: 176,600 kg (389,300 lb).
More... - Chronology...
Unfuelled mass: 17,800 kg (39,200 lb).
Height: 23.12 m (75.85 ft).
Diameter: 6.61 m (21.68 ft).
Span: 6.61 m (21.68 ft).
Thrust: 1,401.30 kN (315,025 lbf).
Specific impulse: 447 s.
HG-3 Rocketdyne lox/lh2 rocket engine. 1400.7 kN. Study 1967. Isp=451s. High-performance high-pressure chamber engine developed from J-2. Considered for upgrades to Saturn V launch vehicle upper stages. Technology led to Space Shuttle Main Engines. More...
Lox/LH2 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. Liquid hydrogen was identified by all the leading rocket visionaries as the theoretically ideal rocket fuel. It had big drawbacks, however - it was highly cryogenic, and it had a very low density, making for large tanks. The United States mastered hydrogen technology for the highly classified Lockheed CL-400 Suntan reconnaissance aircraft in the mid-1950's. The technology was transferred to the Centaur rocket stage program, and by the mid-1960's the United States was flying the Centaur and Saturn upper stages using the fuel. It was adopted for the core of the space shuttle, and Centaur stages still fly today. More...
Home - Browse - Contact
© / Conditions for Use