N2O4/MMH propellant rocket stage. Loaded/empty mass 36,360/34,380 kg. Thrust 6,834.30 kN. Vacuum specific impulse 313 seconds.
Cost $ : 9.570 million. No Engines: 2.
AKA: IHLLV; Interim Heavy Lift Launch Vehicle.
More... - Chronology...
Status: Study 1989.
Gross mass: 36,360 kg (80,160 lb).
Unfuelled mass: 34,380 kg (75,790 lb).
Height: 21.00 m (68.00 ft).
Diameter: 6.30 m (20.60 ft).
Span: 6.30 m (20.60 ft).
Thrust: 6,834.30 kN (1,536,412 lbf).
Specific impulse: 313 s.
Burn time: 120 s.
OME Aerojet N2O4/MMH rocket engine. 26.7 kN. Study 1972. Isp=316s. Engine used in Shuttle Orbiter Orbital Maneuvering System pods, for orbit insertion, maneuvering, and re-entry initiation. First flight 1981. More...
Associated Launch Vehicles
IHLLV American orbital launch vehicle. Same concept as Shuttle C. Shuttle orbiter replaced by recoverable pod with shuttle main engines and payload cannister. Quick way for US to obtain heavy payload capability and reduce shuttle cost per kg to orbit by 3 X. More...
Shuttle C American orbital launch vehicle. NASA Marshall design for a cargo version of the shuttle system. The shuttle orbiter would be replaced by an unmanned recoverable main engine pod. The same concept was studied earlier as the Interim Heavy Lift Launch Vehicle (IHLLV) and as the Class I Shuttle Derived Vehicle (SDV). The Phase I two-SSME configuration would have a payload of 45,000 kg to low earth orbit. Design carried to an advanced phase in 1987-1990, but then abandoned when it was found the concept had no cost advantage over existing expenable launch vehicles. More...
N2O4/MMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Monomethylhydrazine (CH3NHNH2) is a storable liquid fuel that found favour in the United States for use in orbital spacecraft engines. Its advantages in comparison to UDMH are higher density and slightly higher performance. More...
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