SYSTEM AND METHOD FOR COOLING A LEADING EDGE OF A HIGH SPEED VEHICLE

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point....

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Bibliographic Details
Main Authors Natsui, Gregory Alexander, Rush, Brian Magann, Rathay, Nicholas William
Format Patent
LanguageEnglish
Published 09.06.2022
Subjects
AEROPLANES
AIRCRAFT
AVIATION
BLASTING
COSMONAUTICS
HEAT EXCHANGE IN GENERAL
HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS,IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
HEATING
HELICOPTERS
LIGHTING
MECHANICAL ENGINEERING
PERFORMING OPERATIONS
TRANSPORTING
WEAPONS
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Summary:A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal enhancement feature can enhance a heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.
Bibliography:Application Number: US202017114908