Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Josiane M Labatut

Georges Mazeaud

Francois J Mirville

Francois M Marlin

A propulsion system for a reusable spacecraft is disclosed having turbojet, amjet and rocket modes of operation. Hydrogen or exhaust gases from a gas generator drives a gas turbine which powers an air compressor in the turbojet mode. An injection device injects hydrogen and exhaust from the gas driven turbine in the combustion chamber in the turbojet mode. In the ramjet mode, only hydrogen is injected into the combustion chamber. In the ramjet mode, hydrogen and oxygen are supplied to the rocket motor. An adjustable nozzle is provided to form a variable throat convergent-divergent nozzle in the turbojet and ramjet modes and to form a divergent nozzle in the rocket mode.

Growing community of inventors

Yerres, France

Josiane M Labatut