The invention discloses a non-stall floating wing mechanism and an adjusting method thereof. The non-stall floating wing mechanism comprises a fuselage and wings, the two ends of the wing main beam respectively extend out of the fuselage, penetrate through the floating connecting plates and are rotationally connected with the wing main beam shaft holes; the force transmission main beam is located in the fuselage, the two ends of the force transmission main beam extend out of the fuselage respectively, and the force transmission main beam is rotationally connected with force transmission main beam shaft holes in the floating connecting plates; one end of the linear steering engine is hinged to the floating connecting plates, and the other end of the linear steering engine is hinged to the wings; wherein the included angle between the rotating center connecting line of the wing main beam shaft hole and the force transmission main beam shaft hole and the vertical line of the chord line of the wing is theta, and the theta angle is changed by adjusting the length of the linear steering engine. The wing attack angle can be separated from the pitching attitude angle of the fuselage, and the wing trim attack angle is adjustable during flight, so that wing stall-free flight and high-aerodynamic-efficiency flight of the aircraft are realized.
本发明公开了一种不失速浮动机翼机构及其调节方法,包括机身和机翼,其特征在于:还包括位于机身内且两端分别伸出机身并穿过浮动连接板与机翼主梁轴孔相转动连接的机翼主梁、位于机身内且两端分别伸出机身并与浮动连接板上的传力主梁轴孔相转动连接的传力主梁以及一端与浮动连接板相铰接且另一端与机翼相铰接的直线舵机,其中机翼主梁轴孔和传力主梁轴孔的转动中心连线与机翼弦线垂线的夹角为θ角,调节直线舵机的长度改变θ角大小。本发明可实现机翼攻角与机身俯仰姿态角分离,且在飞行中机翼配平攻角可调,从而实现飞行器机翼不失速飞行以及高气动效率飞行。
Non-stall floating wing mechanism and adjusting method thereof
一种不失速浮动机翼机构及其调节方法
25.04.2025
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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