N2O4/UDMH propellant rocket stage. Loaded/empty mass 1,995,800/199,600 kg. Thrust 28,553.00 kN. Vacuum specific impulse 267 seconds. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, HY-140 Hull
Status: Study 1967.
More... - Chronology...
Gross mass: 1,995,800 kg (4,399,900 lb).
Unfuelled mass: 199,600 kg (440,000 lb).
Height: 57.16 m (187.53 ft).
Diameter: 6.61 m (21.68 ft).
Span: 9.26 m (30.38 ft).
Thrust: 28,553.00 kN (6,418,969 lbf).
Specific impulse: 267 s.
Specific impulse sea level: 245 s.
Burn time: 162 s.
PF N204/UDMH-2912k Notional N2O4/UDMH rocket engine. 28,552 kN. Study 1967. Isp=267s. Used on Saturn LCB-Storable-140 launch vehicle. More...
Associated Launch Vehicles
Saturn LCB-Storable-140 American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, HY-140 Steel Hull. More...
N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...
Home - Browse - Contact
© / Conditions for Use