Lox/LH2 propellant rocket stage. Loaded/empty mass 142,184/24,943 kg. Thrust 2,150.00 kN. Vacuum specific impulse 405 seconds.
Cost $ : 18.000 million.
Status: Study 1968.
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Gross mass: 142,184 kg (313,462 lb).
Unfuelled mass: 24,943 kg (54,989 lb).
Height: 30.00 m (98.00 ft).
Diameter: 4.00 m (13.10 ft).
Span: 20.00 m (65.00 ft).
Thrust: 2,150.00 kN (483,330 lbf).
Specific impulse: 405 s.
Specific impulse sea level: 300 s.
Burn time: 216 s.
Mustard Notional lox/lh2 rocket engine. 2157.4 kN. Study 1968. Isp=405s. Used on Mustard launch vehicle. More...
Associated Launch Vehicles
Mustard The British Aircraft Corporation "Multi-Unit Space Transport And Recovery Device" design of 1964-1965 was a winged two-stage-to-orbit reuseable space shuttle using the 'triamese' concept. The three components of the design were lifting bodies with a configuration similar to the American HL-10 vehicle. BAC sought to reduce development cost by use of two boosters nearly identical to the orbiter vehicle. 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...
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