Ablative Cooling of Aerodynamically Heated Radomes.
Patent, Filed 14 Dec 89, patented 21 Aug 90,
DEPARTMENT OF THE NAVY WASHINGTON DC
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A radome type nose cone shell subjected to aerodynamic heating during projectile travel, is ablatively cooled by evaporation of metal coolant from a solidified coating thereof adhering to the external surface of a porous section of the cone shell through which the coolant seeps from internal storage at a rate regulated by formation of the solidified coating. The evaporating coolant from the coating mixes with the air in the flow stream to form a protective a boundary layer extending downstream from the porous section of the nose cone shell. The coolant is melted by said aerodynamic heating during internal storage within the nose cone shell for seepage outflow from the porous section and has the requisite heats of vaporization and fusion to effect alternate freezing and thawing thereof in response to withdrawal of heat by the cooling process for establishment and maintenance of the flow regulating coating.
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