A combined cycle propulsion system for a flight vehicle includes a compressor-fed combustion engine, and a multi-mode supersonic engine. The multi-mode supersonic engine includes an adjustable inlet section, a combustion section arranged downstream of the adjustable inlet section and including a first combustor portion having at least one rotating detonation combustor and a second combustor portion having a supersonic combustion type combustor, and an adjustable exhaust nozzle section arranged downstream of the combustion section. The at least one rotating detonation combustor functions as a pilot for the supersonic combustion type combustor.
COMBINED CYCLE PROPULSION SYSTEM FOR HYPERSONIC FLIGHT
2023-10-12
Patent
Elektronische Ressource
Englisch
Hypersonic Combined Cycle Propulsion
NTIS | 1990
Hypersonic combined cycle propulsion : papers
TIBKAT | 1990
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Engineering Index Backfile | 1963
|Hypersonic and Combined Cycle Propulsion for Civil Applications
British Library Conference Proceedings | 1995
|Terrestrial hypersonic flight propulsion
AIAA | 1963
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