N2O4/MMH propellant rocket stage. Loaded/empty mass 1,578/275 kg. Thrust 0.98 kN. Vacuum specific impulse 312 seconds.
Cost $ : 15.000 million. No Engines: 2.
AKA: Integrated Apogee Boost Subsystem.
More... - Chronology...
Status: Out of production.
Gross mass: 1,578 kg (3,478 lb).
Unfuelled mass: 275 kg (606 lb).
Height: 0.68 m (2.23 ft).
Diameter: 2.90 m (9.50 ft).
Span: 2.90 m (9.50 ft).
Thrust: 980 N (220 lbf).
Specific impulse: 312 s.
Burn time: 60 s.
Number: 10 .
R-4D Marquardt N2O4/MMH rocket engine. 0.490 kN. Isp=312s. Developed as attitude control thruster for the Apollo Service and Lunar Modules in 1960s. In production for numerous satellites for apogee / perigee maneuvers, orbit adjustment, and attitude control. More...
Associated Launch Vehicles
Atlas II American orbital launch vehicle. The Atlas II booster was 2.7-meters longer than an Atlas I and included uprated Rocketdyne MA-5A engines. The Atlas I vernier engines were replaced with a hydrazine roll control system. The Centaur stage was stretched 0.9-meters compared to the Centaur I stage. Fixed foam insulation replaced Atlas I's jettisonable insulation panels. The original Atlas II model was developed to support the United States Air Force Medium Launch Vehicle II program. Its Centaur used RL10A-3-3A engines operating at an increased mixture ratio. The first Atlas II flew on 7 December 1991, successfully delivering AC-102/Eutelsat II F3 to orbit. 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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