多片后缘小翼对直升机旋翼桨叶动态失速及桨毂振动载荷的控制

Control of Helicopter Rotor Blade Dynamic Stall and Hub Vibration Loads by Multiple Trailing Edge Flaps

减缓直升机后行桨叶动态失速发生、降低直升机桨毂振动载荷是提高直升机飞行速度、改进直升机飞行性能的重要途径。本文研究了直升机在高速高载情况下利用多片受控的桨叶后缘小翼对直升机的后行桨叶动态失速和桨毂振动载荷同时进行控制的有效方法。建立了弹性桨叶和后缘刚性小翼的结构动力学模型。桨叶剖面气动载荷采用Leish-man-Beddoes二维非定常动态失速模型计算,后缘小翼剖面气动载荷采用Hariharan-Leishman二维亚声速非定常气动模型计算。采用伽辽金和数值积分相结合的方法求解旋翼系统的气弹响应。建立了有效的多片后缘小翼控制策略和控制方法,分析了3片后缘小翼的运动规律及对后行桨叶动态失速和桨毂振动载荷的控制效果,结果表明利用多片小翼的运动是控制桨叶动态失速和桨毂振动载荷的有效方法。

Delaying dynamic stall and reducing rotor-hub vibration loads are important ways to increase the forward speed and improve the flight performances of a helicopter. This paper investigate effective methods for the simultaneous control of the dynamic stall of retreating blade and rotor-hub vibration loads in the high-speed and high load conditions of a helicopter by using multiple trailing edge flaps. Structural dynamic models of the elastic blade and the rigid trailing edge flap are estab- lished. The blade section aerodynamic loads are calculated by using the Leishman-Beddoes two-dimensional unsteady dy- namic stall model and the trailing edge flap section aerodynamic loads are calculated by using the Hariharan-Leishman two- dimensional subsonic unsteady aerodynamic model. The aeroelastic responses of the rotor system are solved by combining the Galerkin and numerical integration methods. The effective control strategies and control methods of multiple trailing edge flaps are established. The motion laws of the three trailing edge flaps and their control effects on the retreating blade dynam- ic stall and rotor hub vibration loads are analyzed. The analytical results show that application of the motion of the multiple trailing edge flaps is an effective way to control the retreating blade dynamic stall and the rotor hub vibration loads.