Control of dynamic stall of helicopter rotor blades

被引：0

作者：

WANG Rong ^{[1
]}

XIA PinQi ^{[1
]}

机构：

[1] National Key Laboratory of Helicopter Rotor Aeromechanics,Nanjing University of Aeronautics and Astronautics

来源：

Science China(Technological Sciences) | 2013年 / 01期

基金：

中国国家自然科学基金; 中央高校基本科研业务费专项资金资助;

关键词：

helicopter blade; trailing edge flap; dynamic stall; control;

D O I：

暂无

中图分类号：

V275.1 [];

学科分类号：

082503 ;

摘要：

An effective method for delaying the dynamic stall of helicopter retreating blade by using the trailing edge flap has been established in this paper.The aerodynamic loads of blade section are calculated by using the Leishman-Beddoes unsteady two-dimensional dynamic stall model and the aerodynamic loads of the trailing edge flap section are calculated by using the Hariharan-Leishman unsteady two-dimensional subsonic model.The analytical model for dynamic stall of elastic blade with the stiff trailing edge flap has been established.Adopting the aeroelastic analytical method and the Galerkin’s method combined with numerical integration,the aeroelastic responses of rotor system in high-speed and high-load forward flight are solved.The mechanism for control of dynamic stall of retreating blade by using trailing edge flap has been presented.The numerical results indicate that the reasonably controlled swing of trailing edge flap can delay the dynamic stall of retreating blade under the same flight conditions.

引用

页码：171 / 180

页数：10

共 16 条

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