Control of dynamic stall of helicopter rotor blades

被引:4
作者
Wang Rong [1 ]
Xia PinQi [1 ]
机构
[1] Nanjing Univ Aeronaut & Astronaut, Natl Key Lab Helicopter Rotor Aeromech, Nanjing 210016, Peoples R China
基金
中国国家自然科学基金;
关键词
helicopter blade; trailing edge flap; dynamic stall; control;
D O I
10.1007/s11431-012-5022-3
中图分类号
T [工业技术];
学科分类号
08 ;
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
收藏
页码:171 / 180
页数:10
相关论文
共 16 条
[1]  
Beddoes TS, 1985, P 2 INT C ROT BAS RE, P24
[2]  
Bousman WG, 1998, J AHS, V43, P4
[3]  
CARR L, 1983, 832533 AIAA
[4]  
Chandrasekhara M, 2004, P 10 AS C FLUID MECH, P1
[5]  
Geiselmann W, 2004, 2004 IEEE INTERNATIONAL SYMPOSIUM ON INFORMATION THEORY, PROCEEDINGS, P14
[6]   Dynamic stall flow control via a trailing-edge flap [J].
Gerontakos, P ;
Lee, T .
AIAA JOURNAL, 2006, 44 (03) :469-480
[7]  
Hariharn N, 1995, 951228 AIAA
[8]  
Johson W, 1970, 1301 ASRL, P130
[9]  
Leishman J.G., 1986, Proceedings of the 42nd Annual Forum of the American Helicopter Society, Washington, DC, USA, 2-5 June 1986, P243
[10]  
Leishman JG, 2007, HELICOPTER, P112