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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。
It is an important way to improve the helicopter flight speed and improve the helicopter flight performance by reducing the dynamic stall of the blade after the helicopter is slowed down and reducing the vibration load of the helicopter hub. This paper studies the helicopter’s effective method of controlling the helicopter’s rear blade dynamic stall and the hub vibration load simultaneously by using a plurality of controlled blade trailing edges under high-speed and high-load conditions. The structural dynamics model of elastic blade and trailing edge rigid winglets is established. The aerodynamic loads on the blade profile are calculated using the Leish-man-Beddoes two-dimensional unsteady dynamic stall model. The aerodynamic loads on the trailing winglet are calculated using Hariharan-Leishman two-dimensional subsonic unsteady aerodynamic model. Aeroelastic response of rotor system is solved by a combination of Galerkin and numerical integration. The control strategy and control method of multi-blade trailing-edge winglets are established. The movement regulation of 3 trailing-edge winglets and the control effect on the dynamic stall of rear blades and the vibration load of hub are analyzed. The results show that the multi- Wing motion is an effective way to control blade dynamic stall and hub vibration loads.