TRW N2O4/UDMH rocket engine. 9793 kN. Study 1968. 1960's designs for 'big dumb booster'. Isp=300s. Used on LCLV launch vehicle.
Thrust (sl): 7,834.500 kN (1,761,266 lbf). Thrust (sl): 798,911 kgf. Chamber Pressure: 17.01 bar. Area Ratio: 31. Thrust to Weight Ratio: 0. Coefficient of Thrust vacuum: 10.7215909769459. Coefficient of Thrust sea level: 8.89879097694586.
Status: Study 1968.
More... - Chronology...
Diameter: 4.58 m (15.01 ft).
Thrust: 9,793.20 kN (2,201,599 lbf).
Specific impulse: 300 s.
Specific impulse sea level: 240 s.
Associated Launch Vehicles
LCLV American low cost orbital launch vehicle. As a result of TRW's review of the Truax/Aerojet Sea Dragon, TRW became so interested in the concept that they undertook studies of their own, which resulted in a design that became known as the 'Big Dumb Booster'. They proposed structural approaches that were even more conservative than Aerojet's, e.g., the use of T-180 steel instead of maraging steel, which would result in even heavier and cheaper tankage. TRW finally obtained USAF funding for fabrication of stage sections and demonstration of scaled-up versions of the TRW pump-fed Apollo Lunar Module ascent engine. The design promised low cost access to space using low technology (steel stages built to low tolerances in shipyards, pressure-fed engines, and low cost storable propellants). But yet again neither NASA or USAF showed interest in true cheap access to space. More...
Associated Manufacturers and Agencies
TRW American manufacturer of rockets, spacecraft, and rocket engines. TRW Corporation, Redondo Beach, CA, USA. 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...
LCLV-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 798,389/95,092 kg. Thrust 9,793.30 kN. Vacuum specific impulse 300 seconds. More...
Home - Browse - Contact
© / Conditions for Use