The invention relates to a hypersonic aircraft head cone based on a composite cooling mode, which is characterized by comprising a head cone body which is made of a high temperature resistance alloy or ceramic material and is of a multi-micropore structure, wherein the inside of the head cone body is divided into a front chamber and a rear chamber by a separation sheet; the rear of the head cone body is fixedly connected with a center coolant pipeline and at least one periphery coolant pipeline; the at least one periphery coolant pipeline is communicated with the rear chamber; the center coolant pipeline penetrates through the rear chamber and stretches into the front chamber; a center spray orifice is formed in the center of the head of the head cone body, and is located in an extension line of the center coolant pipeline; and a plurality of side spray orifices which are uniformly distributed and are communicated with the rear chamber are formed in the side wall of the head cone body.
Hypersonic aircraft head cone based on composite cooling mode
2015-08-26
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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