Notional lox/lh2 rocket engine. 1778 kN. Study 1967. Isp=447s. Used on Saturn V-3B launch vehicle.
Status: Study 1967.
More... - Chronology...
Thrust: 1,778.00 kN (399,710 lbf).
Specific impulse: 447 s.
Specific impulse sea level: 200 s.
Burn time: 385 s.
Saturn MS-IVB-3B American space tug. Study 1967. Upper stage / space tug - Boeing study, 1967. Launched by Saturn V. S-IVB with 16.5 foot stretch, 350,000 pounds propellant, 1 x 400,000 pound thrust toroidal engine. More...
Associated Launch Vehicles
Saturn V-3B American orbital launch vehicle. Boeing study, 1967. Variation on MSFC 1965 study Saturn MLV-V-3 but with toroidal engines. Saturn IC stretched 240 inches with 5.6 million pounds propellant (but only 4.99 million pounds usable without solid rocket boosters) and 5 F-1A engines; S-II stretched 186 inches with 1.29 million lbs propellant and 5 J-2T-400 engines; S-IVB stretched 198 inches with 350,000 lbs propellant, 1 J-2T-400 engine. 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...
Saturn MS-IVB-3B Lox/LH2 propellant rocket stage. Loaded/empty mass 179,200/20,400 kg. Thrust 1,778.90 kN. Vacuum specific impulse 447 seconds. S-IVB with 16.5 foot stretch, 350,000 pounds propellant, 1 400,000 pound thrust toroidal engine. More...
Saturn MS-II-3B Lox/LH2 propellant rocket stage. Loaded/empty mass 643,200/53,500 kg. Thrust 12,455.40 kN. Vacuum specific impulse 447 seconds. S-II with 15.5 foot stretch, 1.29 million pounds propellant, 7 x 400,000 lb thrust toroidal engines. More...
Home - Browse - Contact
© / Conditions for Use