Combination turbojet-ramjet-rocket propulsion system

Details Combination turbojet-ramjet-rocket propulsion system Combination turbojet-ramjet-rocket propulsion system

1989-09-27

1991-10-01

Casaregola, Louis J.

Power plants

Reaction motor

Interrelated reaction motors

60257, 60261, 60267, 60268, F02K 900, F02K 310

Patent

active

050521764

ABSTRACT:
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.

REFERENCES:
patent: 3046742 (1962-07-01), Egbert
patent: 3237400 (1957-04-01), Kuhrt
patent: 3261571 (1966-07-01), Pinnes
patent: 4185457 (1980-01-01), Parker
patent: 4224790 (1980-09-01), Christensen
patent: 4817892 (1989-04-01), Janeke
patent: 4909031 (1990-03-01), Grieb
patent: 4930309 (1988-11-01), Hartman
patent: 4934632 (1990-06-01), Kim

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