THERMAL PROTECTION AND DRAG REDUCTION METHOD AND SYSTEM FOR ULTRA HIGH-SPEED AIRCRAFT

WIPO Patent Application WO/2016/127932

A1

Disclosed are thermal protection and drag reduction method and system for an ultra high-speed aircraft. A cold source (200) is and a cold source driving device (100) are arranged inside a cavity of the ultra high-speed aircraft. A plurality of micropores (300) are arranged on a wall surface (310) of the cavity. The cold source driving device (100) comprises an air pump (110), a cold source reservoir (210) and a buffer (150). The air pump (110) supplies compressed air to a cold source reservoir (210) during operating. The cold source (200) enters the buffer (150) and is vaporized under the action of air pressure. High-pressure gas is ejected from the micropores (300) 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.

ZHANG WENWU (CN)
XIANG SHUHONG (CN)
GUO CHUNHAI (CN)
TONG JINGYU (CN)
ZHANG TIANRUN (CN)
YANG YANG (CN)
SONG TAO (CN)

PCT/CN2016/073710

August 18, 2016

February 06, 2016

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NINGBO INST OF MAT TECH & ENG CHINESE ACAD OF SCIENCES (CN)
BEIJING INST SPACECRAFT ENVIRONMENT ENGINEERING (CN)

B64G1/58

CN104608942A	2015-05-13
CN204623858U	2015-09-09
CN102145745A	2011-08-10
US4991797A	1991-02-12
CN102152849A	2011-08-17
CN2744599Y	2005-12-07
US5299762A	1994-04-05

See also references of EP 3257756A4

BEIJING GRANDER IP LAW FIRM (CN)
北京鸿元知识产权代理有限公司 (CN)

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