Thermal protection and drag reduction method and system for ultra high-speed aircraft |
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| 申请号 | US15550777 | 申请日 | 2016-02-06 | 公开(公告)号 | US20180057191A1 | 公开(公告)日 | 2018-03-01 |
| 申请人 | NINGBO INSTITUTE OF MATERIALS TECHNOLOGY & ENGINEERING, CHINESE ACADEMY OF SCIENCES; BEIJING INSTITUTE OF SPACECRAFT ENVIRONMENT ENGINEERING; | 发明人 | Wenwu ZHANG; Shuhong XIANG; Chunhai GUO; Jingyu TONG; Tianrun ZHANG; Yang YANG; Tao SONG; | ||||
| 摘要 | Disclosed are the thermal protection and drag reduction method and system for an ultra high-speed aircraft. A cold source is and a cold source driving device are arranged inside a cavity of the ultra high-speed aircraft. A plurality of micropores are arranged on a wall surface of the cavity. The cold source driving device comprises an air pump, a cold source reservoir and a buffer. The air pump supplies compressed air to a cold source reservoir during operation. The cold source enters the buffer and is vaporized under the action of air pressure. High-pressure gas is ejected from the micropores to form a gas film on the outer surface of the cavity. The gas film not only can perform thermal protection on the ultra high-speed aircraft, but also can effectively reduce viscous drag between the aircraft and the external gas, by virtue of which the thermal barrier phenomenon is alleviated or eliminated. Therefore, security of the ultra high-speed aircraft is improved and service life is prolonged. | ||||||
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