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

王荣; 夏品奇

doi:10.7527/S1000-6893.2013.0197

航空学报 >

2013 , Vol. 34 >Issue 5: 1083 - 1091

DOI: https://doi.org/10.7527/S1000-6893.2013.0197

固体力学与飞行器总体设计

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

王荣 ,
夏品奇

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南京航空航天大学航空宇航学院, 江苏南京 210016

王荣男, 博士研究生。主要研究方向: 直升机旋翼气弹。 E-mail: wang@nuaa.edu.cn;夏品奇男, 博士, 教授, 博士生导师。主要研究方向: 直升机旋翼气弹, 直升机振动及其控制等。 Tel: 025-84895795 E-mail: xiapq@nuaa.edu.cn

收稿日期: 2012-06-11

修回日期: 2012-08-21

网络出版日期: 2012-09-18

基金资助

国家自然科学基金(51075208)

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

WANG Rong ,
XIA Pinqi

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College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received date: 2012-06-11

Revised date: 2012-08-21

Online published: 2012-09-18

Supported by

National Natural Science Foundation of China (51075208)

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摘要

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Leishman-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。

关键词： 直升机旋翼; 动态失速; 桨毂振动; 多后缘小翼; 控制

本文引用格式

王荣 , 夏品奇 . 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[J]. 航空学报, 2013 , 34(5) : 1083 -1091 . DOI: 10.7527/S1000-6893.2013.0197

Abstract

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 established. The blade section aerodynamic loads are calculated by using the Leishman-Beddoes two-dimensional unsteady dynamic 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 dynamic 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.

Key words： helicopter rotors; dynamic stall; hub vibration load; multiple trailing edge flaps; control

参考文献

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