A supersonic combustion rocket is described in which large turbopumps for fuel and oxidizers are eliminated by the use of a small rocket motor upstream of the mixing chamber. The exhaust from the small rocket motor creates a pressure differential between the storage tanks for the fuel and oxidizers and the mixing chamber which causes the propellant components to flow from the tanks to the chamber. As the propellant passes between the storage tanks for the fuel and oxidizers and the mixing chamber which causes the propellant components to flow from the tanks to the chamber. As the propellant passes the small rocket motor, it becomes entrained in the exhaust gases and may enter the mixing chamber at supersonic speeds. The proposed system results in a rocket motor having substantially greater efficiency than a motor of the same size using a turbopump feed system.
Supersonic Combustion Rocket
1972
8 pages
Report
No indication
English
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