SYSTEM AND METHOD FOR COOLING A LEADING EDGE OF A HIGH SPEED VEHICLE
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United States of America Patent
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Issued Date -
Jun 16, 2022
app pub date -
Dec 14, 2020
filing date -
Dec 14, 2020
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Abstract
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 dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.
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