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建立了利用桨叶后缘小翼的受控运动对直升机后行桨叶动态失速进行控制的有效方法.桨叶剖面气动载荷采用Leishman-Beddoes二维非定常动态失速模型,后缘小翼剖面气动载荷采用Hariharan-Leishman二维亚音速非定常模型,建立了带后缘刚性小翼的弹性桨叶动态失速分析模型.采用气弹分析方法以及伽辽金和数值积分相合的方法,在高载高速的情况下,求旋翼系统的气弹响应.给出了后缘小翼用于控制桨叶动态失速的机理.数值分析表明,在相同的飞行条件下,后缘小翼的合理偏转,可延迟后行桨叶动态失速的发生.
An effective method to control the dynamic stall of the helicopter’s rear blade is established by using the controlled movement of the blade’s trailing edge winglet.The aerodynamic load on the blade section adopts the Leishman-Beddoes two-dimensional unsteady dynamic stall model, Based on Hariharan-Leishman two-dimensional subsonic unsteady model, a dynamic blade model of elastic blade with a trailing-edge rigid winglet is established. By using the method of aeroelastic analysis and the method of combining Galerkin and numerical integral, , The aeroelastic response of the rotor system is obtained.The mechanism of the trailing edge winglet to control the dynamic stall of the blade is given.The numerical analysis shows that the reasonable deflection of the trailing edge winglet can be delayed under the same flight conditions After the occurrence of dynamic stall paddle.