| [1] Hoffmann F, Konstanzer P, Priems M. Active cabin vibration reduction for jet-smooth helicopter ride[C]//Proceedings of the 35th European Rotorcraft Forum, 2009.[2] Lu Y, Gu Z Q, Ling A M. Flight test of active control of structure response for helicopter[J]. Journal of Vibration Engineering, 2012, 25(1): 24-29. (in Chinese) 陆洋, 顾仲权, 凌爱民. 直升机结构响应主动控制飞行试验[J]. 振动工程学报, 2012, 25(1): 24-29.[3] Teal R S, Mccorvey D L, Mailoy D. Active vibration suppression for the CH-47D[C]//Proceedings of the 53rd Annual Forum of American Helicopter Society, 1997.[4] Prouty R. Should we consider variable rotor speeds[J]. Vertiflite, 2004, 50(4): 24-27.[5] Preumont A. Vibration control of active structures, an introduction[M]. Norwell, MA: Kluwer, 1997.[6] Wang X, Ehlers C, Neitzel M. Electro-mechanical dynamic analysis of the piezoelectric stack[J]. Smart Materials and Structures, 1996, 5(4): 492-500.[7] Flint E, Liang C, Rogers C A. Electromechanical analysis of piezoelectric stack active member power consumption[J]. Journal of Intelligent Material Systems and Structures, 1995, 6(1): 117-124.[8] Redmond J, Barney P. Vibration control of stiff beams and plates using structurally integrated PZT stack actuators[J]. Journal of Intelligent Material Systems and Structures, 1997, 8(6): 525-635.[9] Young A J, Hansen C H. Control of flexural vibration in a beam using a piezoceramic actuator and an angle stiffener[J]. Journal of Intelligent Material Systems and Structures, 1994, 5(4): 536-549.[10] Kermani M R, Patel R V. Flexure control using piezostack actuators: design and implementation[J]. IEEE/ASME Transactions on Mechatronics, 2005, 10(2): 181-188.[11] Yang Z C, Wang W, Gu Y S, et al. Smart structure vibration control using a new bending type of piezoelectric stack actuator[J]. Journal of Vibration and Shock, 2009, 28(9): 130-134. (in Chinese) 杨智春, 王巍, 谷迎松, 等. 一种弯曲型压电堆作动的设计及在振动控制中的应用[J]. 振动与冲击, 2009, 28(9): 130-134.[12] Hanagud S, Babu G L. Smart structures in the control of airframe vibrations[J]. Journal of the American Helicopter Society, 1994, 39(2): 69-72.[13] Singhvi R, Vennkatesan C. Vibration control of an idealized helicopter model using piezo stack sensor-actuator[C]//Proceedings of the 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics & Materials Conference, 2005.[14] Heverly D. Optimal actuator placement and active structure design for control of helicopter airframe vibrations[D]. Pennsylvania: Department of Mechanical and Nuclear Engineering, Pennsylvania State University, 2002.[15] Walchko J C, Kim J S, Wang K W. Hybrid feedforward-feedback control for active helicopter vibration suppression[C]//Proceedings of the 63rd Annual Forum of American Helicopter Society, 2007.[16] Song L S, Xia P Q. Coupled fuselage/piezoelectric stack actuator optimization method for active vibration control of helicopter[J]. Acta Aeronautica et Astronautica Sinica, 2011, 32(10): 1835-1841. (in Chinese) 宋来收, 夏品奇. 直升机振动主动控制的机身/压电叠层作动器耦合优化法[J]. 航空学报, 2011, 32(10): 1835-1841.[17] Bauchau O A, Rodriguez J, Chen S Y. Coupled rotor-fuselage analysis with finite motions using component mode synthesis[J]. Journal of the American Helicopter Society, 2004, 49(2): 201-211.[18] Yeo H, Chopra I. Coupled rotor/fuselage vibration analysis for teetering rotor and test data comparison[J]. Journal of Aircraft, 2001, 38(1): 111-121.[19] Chandrasekar J, Liu L, Patt D. Adaptive harmonic steady state control for disturbance rejection[J]. IEEE Transactions on Control System Technology, 2006, 14(6): 993-1007.[20] Veres S M. Adaptive harmonic control[J]. International Journal of Control, 2001, 74(12): 1219-1225. |
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