Fin Buffeting Alleviation in Disturbed Flow by Buffeting Principal Modal Control Method
Wang Wei1, Yang Zhichun1，Zhang Xinping2
1. Institute of Structural Dynamics and Control, School of Aeronautics, Northwestern Polytechnical University, Xi’an, 710072)2. AVIC Shaanxi Aircraft Industry (Group) Corporation Ltd. Hanzhong, 723213
摘 要：采用压电结构的热弹比拟建模方法，进行了垂尾模型一弯模态和一扭模态响应的压电主动控制仿真。设计制作了一个垂尾气动弹性抖振模型以及两种形式的气流干扰源，用于在风洞中进行垂尾抖振实验及产生扰流对垂尾模型实施抖振激励。采用自主研发的弓形压电作动器，根据垂尾抖振响应控制的主模态控制思想，设计了垂尾模型抖振压电主动控制系统，进行了垂尾模型抖振响应压电主动控制风洞实验。结果表明，采用抖振主模态响应控制思想设计的垂尾抖振压电主动控制系统，可使垂尾模型抖振响应功率谱密度函数峰值降低50%以上。 参 考 文 献 [1] R. A. Frazer , W. J. Duncan.The Accident Investigation Subcommittee on the Accident to the Airplane G-AAZK at Meopham Knet England on 21July 1930[R]，British Research Council ,London , Aug 1931 [2] S.Hanagud. F-15 Tail Buffet Alleviation: A Smart Structure Approach[R]. School of Aerospace Engineering Georgia Institute of Technology Atlanta, 1999 [3] Stephen C. Galea, Thomas G. Ryall, Douglas A. Henderson et al. Next generation active buffet suppression system[C]// Proceeding of AIAA/ICAS International Air & Space Symposium and Exposition. Dayton: AIAA, 2003, 14-17 [4] Hauch, R. M., Jacobs, J. H., Dima, C et al. Reduction of Vertical Tail Buffet Response Using Active Control[J]. Journal of Aircraft, 1996，33（3）：617-622 [5] R. W. Moses, Vertical Tail Buffeting Alleviation using Piezoelectric Actuators –Some Results of the Actively Controlled Response of Buffet-Affected Tails[C]// Proceeding of SPIE’s 4 th Annual International Symposium on Smart Structures and Materials. San Diego: SPIE, 1997,1-12 [6] Fred N , Zimcik D G, Ryall T G, et al . Closed-loop control for vertical fin buffeting alleviation using strain actuation.[J] . Journal of Guidance Control and Dynamics, 2001 , 24(4) : 855-857 [7] Hanagud, S., Bayon de Noyer, M., Luo, et al.Tail buffet alleviation of high-performance twin-tail aircraft using piezostack actuators[J]. AIAA Journal, 2002，40（4）: 619-627 [8] Andrew Rader, Aghil Younsefi-Koma, Fred Afagh, et al. Optimized Grouping of Piezoelectric Actuators on a Flexible Fin[C]// Proceedings of SPIE 5762. Bellingm: SPIE , 2005,123-131 [9] 吕志咏，李建强，秦燕华等.鸭翼布局中双立尾对全机气动及流场特性影响.北京航空航天大学学报,2001，27（6）：677-680 LV Zhiyong，LI Jianqiang，QIN Yanhua et al. Influence of the Twin Vertical Tails on the Aerodynamic Characteristics [J]. Journal of Beijing University of Aeronautics and Astronautics，2001，27(6): 677-680 (in Chinese) [10] 吕咏志，高为民.边条翼飞机气动特性改进研究.航空学报，2002，23（2）：170-172 LV Zhiyong, Gao Weimin. Improvement study on aerodynamic characteristics of a fighter configuration with strake wing[J]. Acta Aeronautica et Astronautica Sinica, 2002，23（2）：170-172 (in Chinese) [11] 高 杰,张明禄,吕志咏.双立尾和三角翼之间的气动干扰实验研究.实验流体力学，2005，Vol.19（3）：51-57 GAO Jie, ZHANG Minglu, LV Zhiyong. Investigation of aerodynamic interference between delta wings and twin fins[J]. Journal of Experiments in Fluid Mechanics.2005，19（3）：51-57（In Chinese） [12] 吕志咏,张明禄,高杰.双立尾/ 三角翼布局的立尾抖振研究.实验流体力学，2006，20（1）：13-16
Abstract：Abstract：Fin buffeting causes severe fatigue problem for modern fighter. In this paper, buffeting principal modal control (BPMC) method was described and demonstrated for fin buffeting alleviation. Simulation work for the first bending and torsion mode response alleviation of a fin model using two arching PZT actuator (APA) was implemented. A piezoelectric fin buffeting control system was designed using BPMC method. A fin model, a delta wing and a blunt body were designed and made as test model and flow disturbers, experiment of the fin model buffeting active control in the disturbed flow of the delta wing and blunt body was implemented in a wind tunnel with adoption of APA. Test results indicate that the peak value of the power spectrum density function of the fin model tip buffeting displacement response causing by either of the two flow disturbers can be suppressed by more than 50%.
王 巍;杨智春;张新平. 扰流激励下垂尾抖振响应主模态控制风洞试验研究[J]. , 2012, 31(16): 18-21.
Wang Wei;Yang Zhichun;Zhang Xinping. Fin Buffeting Alleviation in Disturbed Flow by Buffeting Principal Modal Control Method. , 2012, 31(16): 18-21.
2012, Vol. 31 
