Credit: Lockheed Martin
Pratt and Whitney lox/lh2 rocket engine. 66.7 kN. Isp=410s. Early version as proposed for Nova A, Nova B, Saturn B-1, Saturn C-2, Saturn C-3, Saturn I. First flight 1961.
Engine: 131 kg (288 lb). Chamber Pressure: 24.00 bar. Area Ratio: 40. Thrust to Weight Ratio: 44.6280746395249. Coefficient of Thrust vacuum: 1.76072522245361. Coefficient of Thrust sea level: 9.40585557869385E-02.
Unfuelled mass: 131 kg (288 lb).
More... - Chronology...
Diameter: 0.92 m (3.00 ft).
Thrust: 66.70 kN (14,995 lbf).
Specific impulse: 410 s.
Specific impulse sea level: 10 s.
Burn time: 482 s.
Number: 60 .
CEV SAIC American manned spacecraft. Study 2012. SAIC's notional CEV was a Soyuz-shaped aeroshell, enclosing a common pressurized module, and accommodating a crew of four. More...
Associated Launch Vehicles
Saturn C-2 American orbital launch vehicle. The launch vehicle initially considered for realizing the Apollo lunar landing at the earliest possible date. 15 launches and rendezvous required to assemble direct landing spacecraft in earth orbit. More...
Saturn B-1 American orbital launch vehicle. Most powerful version of Saturn I considered. New low energy second stage with four H-1 engines, S-IV third stage, Centaur fourth stage. Masses, payload estimated. More...
Nova B American heavy-lift orbital launch vehicle. Convair/Ehricke Nova design using standard tank/engine modules of 4.9 m diameter in both first and second stages; 6 F-1 engine/modules in first stage, 6 J-2 engine/modules in second stage. More...
Nova A American heavy-lift orbital launch vehicle. Convair/Ehricke Nova design using standard tank/engine modules of 4.9 m diameter in both first and second stages; 4 F-1 engine/modules in first stage, 4 J-2 engine/modules in second stage. More...
Saturn C-3 The launch vehicle concept considered for a time as the leading contender for the Earth Orbit Rendezvous approach to an American lunar landing. More...
Saturn I American orbital launch vehicle. Von Braun launch vehicle known as 'Cluster's Last Stand' - 8 Redstone tanks around a Jupiter tank core,powered by eight Jupiter engines. Originally intended as the launch vehicle for Apollo manned circumlunar flights. However it was developed so early, no payloads were available for it. More...
Associated Manufacturers and Agencies
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...
Nova A-3 Lox/LH2 propellant rocket stage. Loaded/empty mass 40,000/4,000 kg. Thrust 313.00 kN. Vacuum specific impulse 427 seconds. More...
Nova B-3 Lox/LH2 propellant rocket stage. Loaded/empty mass 63,000/5,000 kg. Thrust 451.00 kN. Vacuum specific impulse 427 seconds. More...
Saturn IV Lox/LH2 propellant rocket stage. Loaded/empty mass 50,576/5,217 kg. Thrust 400.35 kN. Vacuum specific impulse 410 seconds. Configuration as flown. More...
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