The invention relates generally to a novel cooling system and fuel preheating system for use in an advanced, high speed aerospace vehicle. A hydrocarbon fluid, such as fuel is accelerated to supersonic conditions within a cooling channel located proximate a high-temperature flight surface. The hydrocarbon fuel absorbs a heat load as it passes through the cooling channel in the flight control surface prior to the fuel being directed into the aircraft engine.
COOLING OF AEROSPACE FLIGHT SYSTEMS
2017-07-13
Patent
Elektronische Ressource
Englisch
Aerospace vehicle flight control systems
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