Lox/LH2 propellant rocket stage. Loaded/empty mass 521,447/49,877 kg. Thrust 4,446.65 kN. Vacuum specific impulse 435 seconds. Basic Saturn II with 41 inch stretch of hydrogen tank, uprated J-2T 200k engines with 10 second increase in specific impulse.
No Engines: 5.
Status: Study 1965.
More... - Chronology...
Gross mass: 521,447 kg (1,149,593 lb).
Unfuelled mass: 49,877 kg (109,959 lb).
Height: 25.88 m (84.90 ft).
Diameter: 10.06 m (33.00 ft).
Span: 10.06 m (33.00 ft).
Thrust: 4,446.65 kN (999,646 lbf).
Specific impulse: 435 s.
Specific impulse sea level: 300 s.
Burn time: 429 s.
J-2T-200K Rocketdyne lox/lh2 rocket engine. 889.3 kN. Study 1965. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2. Isp=435s. More...
Associated Launch Vehicles
Saturn MLV-V-1/J-2T/200K American orbital launch vehicle. MSFC study, 1965. Improved Saturn V configuration studied under contract NAS8-11359. Variant of MLV-V-1 with toroidal J-2T-200K engines replacing standard J-2 engines in upper stages. 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