Influence factors analysis for smart vibration control of a rotor wing with trailing edge flaps
LIU Shiming1,YANG Weidong1,YU Zhihao1,WU Jie2
1. National Key Laboratory of Rotorcraft Aeromechanics, College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics, Nanjing 210000, China;
2. School of Naval Architecture & Ocean Engineering,Jiangsu University of Science and Technology, Zhenjiang 212000, China
Abstract：An aeroelastic load computation model and the optimization method of vibration control for a smart rotor wing with trailing edge flags were developed. The influences of aerodynamic forces and inertial forces of rigid body trailing edge flaps on its elastic blades system were considered. The viscous vortex particle method with the airfoil look-up table was used to compute the aerodynamic load of the rotor wing. The vibratory blade and hub loads were predicted with the force integration method. An optimal algorithm combining the steepest decent method and the golden section algorithm was derived for the defined objective function including the blade torsion and hub vibration loads. It was demonstrated that the proposed model can effectively control the vibratory loads, and the objective function can be reduced by about 70%; the torsion of elastic blades ensures the trailing edge flaps can effectively reduce vibration, while it amplifies the aerodynamic pitch moment of the trailing edge flaps, the latter brings additional blade torsional moment.
刘士明 1 杨卫东 1 虞志浩 1 吴杰 2. 后缘小翼智能旋翼减振效果影响因素分析[J]. 振动与冲击, 2017, 36(3): 138-144.
LIU Shi-ming 1 YANG Wei-dong1 YU Zhi-hao1 WU Jie2. Influence factors analysis for smart vibration control of a rotor wing with trailing edge flaps. JOURNAL OF VIBRATION AND SHOCK, 2017, 36(3): 138-144.
[1] Friedmann P P. On-blade control of rotor vibration, noise, and performance: Just around the corner? The 33rd Alexander Nikolsky Honorary Lecture[J]. Journal of the American Helicopter Society, 2014, 59(4): 1-37.
[2] Falls J, Datta A, Chopra I. Integrated trailing-edge flaps and servotabs for helicopter primary control[J]. Journal of the American Helicopter Society, 2010, 55(3): 1-15.
[3] Patt D, Liu L, Friedmann P P. Rotorcraft vibration reduction and noise prediction using a unified aeroelastic response simulation[J]. Journal of the American Helicopter Society, 2005, 50(1):95-106.
[4] Datta A. Fundamental understanding, prediction and validation of rotor vibratory loads in steady-level flight[D]. College Park: University of Maryland, 2004.
[5] Datta A, Chopra I. Validation and understanding of UH-60A vibratory loads in steady level flight[J]. Journal of the American Helicopter Society, 2004, 49(3): 271-287.
[6] Kim J S, Smith E C, Wang K W. Helicopter blade loads control via multiple trailing-edge flaps[C]//AHS 62nd Annual Forum. Phoenix AZ: AHS International, 2006: 1000-1010.
[7] 虞志浩, 杨卫东, 张呈林. 基于Broyden法的旋翼多体系统气动弹性分析[J]. 航空学报, 2012, 33(12): 2171-2182.
YU Zhi-hao, YANG Wei-dong, ZHANG Cheng-lin. Aeroelasticity analysis of rotor multibody system based on Broyden method[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(12): 2171-2182.
[8] Theodorsen T, Garrick I E. Nonstationary flow about a wing-aileron-tab combination including aerodynamic balance[R]. NACA Report 736, 1942.
[9] 谭剑锋, 王浩文, 吴超, 等. 基于非定常面元/黏性涡粒子混合法的旋翼/平尾非定常气动干扰[J]. 航空学报，2014，35(3): 643-656.
TAN Jian-feng, WANG Hao-wen, WU Chao, et al. Rotor/Empennage Un-steady Aerodynamic Interaction with Unsteady Pan-el/Viscous Vortex Particle Hybrid Method[J]. Acta Aero-nautica et Astronautica Sinica, 2014, 35(3): 643-656.
[10] 吴杰, 杨卫东, 虞志浩. 旋翼桨叶结构载荷计算方法比较研究[J]. 振动与冲击, 2014, 33(7): 210-214.
WU Jie, YANG Wei-dong, YU Zhi-hao. Comparison among rotor blade structural load calculation methods[J]. Journal of Vibration and Shock, 2014, 33(7): 210-214.
[11] Koratkar N A, Chopra I. Analysis and testing of mach-scaled rotor with trailing edge flaps[J]. AIAA Journal, 2000, 38(7): 1113-1124.
[12] 张柱，黄文俊，杨卫东. 后缘小翼型智能旋翼桨叶模型设计分析与试验研究[J]. 南京航空航天大学学报, 2011, 43(3): 296-301.
ZHANG Zhu, HUANG Wen-jun, YANG Wei-dong. Design analysis and test of smart rotor blades model with trailing edge flaps[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2011, 43(3): 296-301.
[13] Staley J A. Validation of rotorcraft flight simulation program through correlation with flight data for soft-in-plane hingeless rotors[R]. AMRDL-TR-75-50, 1976.
[14] Harris T A, Lowry J G. Pressure distribution over an NACA 23012 airfoil with a fixed slot and a slotted flap[R]. NACA-TR-633, 1942.
[15] Peterson R L, Maier T. Correlation of wind tunnel and flight test results of a full-scale hingeless rotor[C]//AHS Aeromechanics Specialists Conference. Washington DC: AHS International, 1994.
[16] 张晓谷. 直升机动力学设计[M]. 北京: 航空工业出版社, 1995.
