초록 ▼

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

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 vaporation 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.

대표청구항 ▼

In combination with a missile adapted to travel through a fluent medium at velocities during which aerodynamic heating thereof occurs, said missile including a nose cone shell made of a solid material having a geometry altering temperature, cooling means for preventing geometric alteration of the no

In combination with a missile adapted to travel through a fluent medium at velocities during which aerodynamic heating thereof occurs, said missile including a nose cone shell made of a solid material having a geometry altering temperature, cooling means for preventing geometric alteration of the nose cone shell by said aerodynamic heating thereof in response to said travel of the missile, including a body of coolant having a melting temperature lower than the geometry altering temperature of the shell to accommodate melting of the coolant in response to said aerodynamic heating of the shell, porous means formed in the shell for inflow of the melted coolant into a protective boundary layer established externally on the shell during said travel of the missile, said coolant having a difference between heats of vaporization and fusion resulting in withdrawal of heat from the coolant at a predetermined rate during travel of the missile, and means storing the body of coolant in operative relation to the porous means for automatically regulating said inflow of the coolant into the boundary layer by formation of a solidified coating of the coolant adhering to the porous means in response to said withdrawal of heat from the coolant at the predetermined rate, the porous means including a tip section and an annular band section of the shell spaced downstream of the tip section.