The invention relates to a rolling wing aircraft blade with an active deformation leading edge, which comprises a symmetrical airfoil blade main body, the leading edge part of the symmetrical airfoil blade main body is composed of a leading edge flap covering 15% of a chord section and other parts of an airfoil section, and the leading edge flap and the other parts are in streamline connection; the leading edge flap is connected with the blade body through a movable connecting structure installed at the front end of the blade body and driven by the linear servo control system to rotate, and the included angle between the leading edge flap and the blade body is changed. According to the linear servo control system installed in the blade body, when the blade rotates, the leading edge flap part can actively rotate according to the conditions such as the position of the blade and the direction of incoming flow, the shape of the blade is changed, and the lift force of the blade is improved; through active rotation of the leading edge flap part, the camber of the blade at the leading edge is changed, the stall attack angle of the blade and the maximum lift coefficient of the blade are improved, the dynamic stall of the blade is improved, the lift force of the blade is improved, the aerodynamic efficiency is improved, and structural vibration and noise are reduced.
本发明涉及一种主动变形前缘的滚翼飞行器叶片,包括对称翼型的叶片主体,对称翼型的叶片主体的前缘部分由覆盖15%的弦截面的前缘襟翼和翼型截面的其他部分组成,并成流线衔接;前缘襟翼通过安装在叶片主体前端的可动连接结构与叶片主体连接,并由线性伺服控制系统驱动转动,改变与叶片主体之间的夹角。本发明通过在叶片主体内安装的线性伺服控制系统,使叶片旋转时,可根据叶片的位置以及来流的方向等条件,前缘襟翼部分主动旋转,改变叶片的形状,提高叶片升力;通过前缘襟翼部分主动旋转,使叶片在前缘处的弯度发生改变,提高了叶片的失速迎角,叶片最大升力系数,改善叶片的动态失速,提高叶片的升力,提到气动效率,降低了结构振动及噪声。
Roll-wing aircraft blade with actively deformed leading edge
一种主动变形前缘的滚翼飞行器叶片
2022-08-30
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |