Power plants – Reaction motor – Motive fluid from diverse generators alternatively ejected...
Patent
1984-07-02
1986-12-30
Croyle, Carlton R.
Power plants
Reaction motor
Motive fluid from diverse generators alternatively ejected...
60251, 60262, 602701, 60253, F02K 300, F02K 700, F02K 900
Patent
active
046319166
ABSTRACT:
A missile drive is provided comprising a single combustion chamber shared by a first, acceleration stage and a second, ramjet cruising stage, said chamber housing the solid propellant to be consumed during acceleration. At least one air inlet is opened at the end of the acceleration stage to allow an air flow to be introduced into the combustion chamber. Moreover, at least one additional exhaust outlet forming an additional nozzle is provided in the back of the combustion chamber and means are provided to seal off said additional exhaust outlet or outlets throughout the initial acceleration stage, such that said additional exhaust outlet or outlets contribute, together with the converging-diverging nozzle, to ejecting the exhaust gas during the ramjet cruising stage.
REFERENCES:
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patent: 3094072 (1963-06-01), Polk
patent: 3182447 (1965-05-01), Bell et al.
patent: 3221497 (1965-12-01), Forbes, Jr.
patent: 3319424 (1967-05-01), Haake
patent: 3482403 (1969-12-01), Polk, Jr.
patent: 3807170 (1974-04-01), Kesting
patent: 4109867 (1978-08-01), Ebeling
patent: 4277940 (1981-07-01), Harner et al.
patent: 4327886 (1982-05-01), Bell et al.
Webster, F., "Integral Rocket/Ramjet Propulsion Flight Data Correlation and Analysis Techniques", Journal of Aircraft and Rockets, vol. 19, No. 4, pp. 326-336 (May 1982).
Le Tanter Gerard
Luscan Bernard
Croyle Carlton R.
Societe Europeenne de Propulsion
Thorpe Timothy S.
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