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
13.07.2017
Patent
Elektronische Ressource
Englisch
Aerospace vehicle flight control systems
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