利用桨叶后缘小翼运动的旋翼桨毂振动载荷优化控制  

Optimal control of rotor hub vibration loads by using motion of trailing edge flap

作　　者：王荣[1] 夏品奇[1] 

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,江苏南京210016

出　　处：《振动工程学报》2013年第4期574-582,共9页Journal of Vibration Engineering

摘　　要：利用桨叶后缘小翼运动是控制旋翼桨毂振动载荷的一种有效方法。采用非定常气动力和弹性力耦合的气弹分析方法,对附加了桨叶后缘小翼的直升机旋翼系统的振动载荷进行了研究。采用弹性桨叶和后缘刚性小翼的结构动力学模型、翼型剖面气动力采用Leishman-Beddoes二维非定常动态失速模型、后缘小翼剖面气动力采用Hariharan-Leishman非定常气动力模型,建立了带后缘小翼的旋翼桨毂振动载荷分析模型。采用伽辽金和数值积分相结合的方法,求解旋翼系统在前飞状态下的气弹响应。分析了后缘小翼各运动参数对桨毂振动载荷的影响。针对桨毂4阶振动载荷,采用改进的主动控制方法,优化了小翼的运动,使桨毂振动载荷得到显著降低。It is an effective method to use trailing edge flap for control of helicopter rotor hub vibration loads.In this paper,the vibration loads of helicopter rotor hub with trailing edge flap have been investigated by using the aeroelastic analysis method of the coupled unsteady aerodynamics and elastic forces.By using the elastic blade and stiff trailing edge flap structural model,the Leishman Beddoes unsteady two-dimensional dynamic stall model for blade,and the Hariharan Leishman unsteady aerodynamic model for trailing edge flap,the analytical model of vibration loads of helicopter rotor hub with trailing edge flap was established.The aeroelastic responses of rotor system in forward flight were solved by jointly using the Galerkin method and the numerical integration method.The effects of each motion parameter of the trailing edge flap on the rotor hub vibration loads were analyzed.For the 4Ω vibration loads of rotor hub,the vibration loads have been reduced considerably through an improved active control method and the optimization of the motion of trailing edge flap.

关 键 词：直升机 旋翼桨毂 后缘小翼 振动载荷 优化控制 

分 类 号：V212.4[航空宇航科学与技术—航空宇航推进理论与工程]