The invention relates to the technical field of aircrafts, and discloses a supersonic speed blowing circular rector trailing edge device and an aircraft, the supersonic speed blowing circular rector trailing edge device comprises an airfoil main body and a jet flow assembly; the jet assembly comprises two jet devices which are symmetrically arranged up and down relative to the rear edge of the airfoil-shaped main body; the jet device comprises a nozzle, a flow channel and an air compression chamber which are arranged on the airfoil-shaped main body; the nozzle is arranged at the joint of the wing surface and the rear edge of the wing-shaped main body, the air compression chamber is positioned on the inner side of the nozzle, and the runner is used for connecting the nozzle and the air compression chamber; wherein the flow channel is of a Laval structure. The problem that an existing common circular rector control device cannot be suitable for high-speed aircraft lift augmentation is solved.
本发明涉及飞行器技术领域,公开了一种超声速吹气环量后缘装置和飞行器,所述超声速吹气环量后缘装置,包括翼型主体和射流组件;射流组件包括两个相对于翼型主体的后缘上下对称布置的射流装置;射流装置包括设置于翼型主体上的喷口、流道和压气室;喷口设置在翼型主体的翼面与后缘连接处,压气室位于喷口内侧,流道用于连接喷口和压气室;其中,流道为拉瓦尔构型。本发明解决了现有普通环量控制装置不能适用于高速飞行器增升的问题。
Supersonic blowing circular rector trailing edge device and aircraft
超声速吹气环量后缘装置和飞行器
16.08.2022
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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