后缘襟翼偏转规律对智能旋翼减振的影响

doi:10.7527/S1000-6893.2025.32628

Abstract

Abstract:

A computational analysis was conducted to address the vibration reduction problem in the trailing-edge flap smart rotor system. First， a geometrically exact beam model based on Hamilton’s principle was employed to establish the aeroelastic coupling model of the system. Following validation through case studies， the effects of single- and combined-frequency deflection parameters on the rotor hub vibration components were analyzed. The influence of rotor blade stiffness characteristics on the vibration reduction effectiveness was further investigated. The calculation analysis results demonstrate that when the flap was deflected at single frequencies of 3/rev， 4/rev， 5/rev， and 6/rev， over 60% vibration reduction could be achieved for specific 4/rev hub load. However， simultaneous suppression of multiple 4/rev hub force and moment components proved challenging. For combined-frequency deflections， the hub vibration components exhibited combined influences from the corresponding single-frequency components as the control phase shifted. Variations in the trailing-edge flap deflection amplitude revealed that the optimal and worst vibration reduction initial phase values did not change obviously. Furthermore， the bending-torsion coupling of elastic blade dominated the actuation effectiveness of the trailing-edge flap while introducing additional system nonlinearities.

Key words: smart rotor, trailing-edge flap, geometrically exact beam, aerodynamic surrogate model, rotor free wake, vibration control

CLC Number:

V211.47

Wei WANG, Zhihao YU, Weidong YANG, Shanji YE. Influence of trailing-edge flap deflection patterns on vibration reduction of a smart rotor[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(6): 232628.

Figures/Tables 23

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References 28

[1]	刘孝辉，徐新喜，白松，等. 军用直升机振动与噪声控制技术［J］. 直升机技术， 2013（1）： 67-72.
	LIU X H， XU X X， BAI S， et al. Vibration and noise control technology on military helicopters［J］. Helicopter Technique， 2013（1）： 67-72 （in Chinese）.
[2]	邓景辉，余智豪，周云，等. 复杂三维外形旋翼气弹稳定性分析［J］. 西北工业大学学报， 2023， 41（1）： 209-215.
	DENG J H， YU Z H， ZHOU Y， et al. Aeroelastic stability analysis of rotor with complex three-dimensional shape［J］. Journal of Northwestern Polytechnical University， 2023， 41（1）： 209-215 （in Chinese）.
[3]	CHOPRA I. Status of application of smart structures technology to rotorcraft systems［J］. Journal of the American Helicopter Society， 2000， 45（4）： 228-252.
[4]	MILGRAM J， CHOPRA I. Helicopter vibration reduction with trailing edge flaps［C］∥36th Structures， Structural Dynamics and Materials Conference. Reston： AIAA， 1995.
[5]	FRIEDMANN P P， DE TERLIZZI M， MYRTLE T F. New developments in vibration reduction with actively controlled trailing edge flaps［J］. Mathematical and Computer Modelling， 2001， 33（10-11）： 1055-1083.
[6]	ROGET B， CHOPRA I. Wind-tunnel testing of rotor with individually controlled trailing-edge flaps for vibration reduction［J］. Journal of Aircraft， 2008， 45（3）： 868-879.
[7]	KODAKKATTU S K， JOY M L， PRABHAKARAN NAIR K. Vibration reduction of helicopter with trailing-edge flaps at various flying conditions［J］. Proceedings of the Institution of Mechanical Engineers， Part G： Journal of Aerospace Engineering， 2017， 231（4）： 770-784.
[8]	FRIEDMANN P P， MILLOTT T A. Vibration reduction in rotorcraft using active control-A comparison of various approaches［J］. Journal of Guidance， Control， and Dynamics， 1995， 18（4）： 664-673.
[9]	WALZ C， CHOPRA I. Design and testing of a helicopter rotor model with smart trailing edge flaps［C］∥Adaptive Structures Forum. Reston： AIAA， 1994.
[10]	SPENCER B T， CHOPRA I. Design and testing of a helicopter trailing edge flap with piezoelectric stack actuators［C］∥Smart Structures and Materials 1996： Smart Structures and Integrated Systems. 1996， 2717： 120-131.
[11]	LEE T， CHOPRA I. Design of piezostack-driven trailing-edge flap actuator for helicopter rotors［J］. Smart Materials and Structures， 2001， 10（1）： 15-24.
[12]	FULTON M V， ORMISTON R A. Hover testing of a small-scale rotor with on-blade elevons［J］. Journal of the American Helicopter Society， 2001， 46： 96-106.
[13]	FULTON M V， ORMISTON R A. Small-scale rotor experiments with on-blade elevons to reduce blade vibratory loads in forward flight［C］∥Proceedings of the 54th Annual Forum of the American Helicopter Society. 1998： 433-451.
[14]	HALL S R， TZIANETOPOULOU T， STRAUB F K， et al. Design and testing of a double X-frame piezoelectric actuator［J］. Smart Structures and Materials 2000： Smart Structures and Integrated Systems， 2000， 3985： 26.
[15]	STRAUB F K， KENNEDY D K， STEMPLE A D， et al. Development and whirl tower test of the SMART active flap rotor［C］∥Smart Structures and Materials 2004： Industrial and Commercial Applications of Smart Structures Technologies. 2004， 5388： 202.
[16]	LAU B H， STRAUB F， ANAND V R， et al. SMART rotor development and wind-tunnel test［C］∥35th European Rotorcraft Forum. 2009.
[17]	JÄNKER P， HERMLE F， LORKOWSKI T， et al. Development and evaluation of advanced flap control technology utilizing piezoelectric actuators［C］∥25th European Rotorcraft Forum. 1999： 14-16.
[18]	ENENKL B， KLÖPPEL V， PREIßLER D， et al. Full scale rotor with piezoelectric actuated blade flaps［C］∥28th European Rotorcraft Forum. 2002： 17-19.
[19]	ROTH D， ENENKL B， DIETERICH O. Active rotor control by flaps for vibration reduction-full scale demonstrator and first flight test results［C］∥32th European Rotorcraft Forum. 2006： 12-14.
[20]	DIETERICH O， ENENKL B， ROTH D. Trailing edge flaps for active rotor control aeroelastic characteristics of the ADASYS rotor system［C］∥62th Annual Forum of the American Helicopter Society. 2006.
[21]	张柱，杨卫东.基于双X驱动机构的智能旋翼模型试验［J］.直升机技术， 2007（3）： 88-91.
	ZHANG Z， YANG W D. Test of smart rotor model based on the double-X actuator［J］. Helicopter Tech- nique， 2007（3）：88-91 （in Chinese）.
[22]	周金龙，董凌华，杨卫东，等. 基于加权最小二乘法辨识的后缘襟翼智能旋翼振动载荷闭环控制仿真研究［J］. 振动与冲击， 2019， 38（4）： 237-244.
	ZHOU J L， DONG L H， et al. Closed-loop vibration control simulation of a helicopter active rotor with trailing-edge flaps based on the weighted-least-squares-error identification method ［J］. Journal of Vibration and Shock， 2019， 38（4）： 237-244 （in Chinese）.
[23]	周子宣，田嘉劲，唐敏，等. 主动后缘襟翼对旋翼桨毂振动载荷控制的机理与风洞试验［J］. 机械工程学报， 2023， 59（14）： 254-263.
	ZHOU Z X， TIAN J J， TANG M， et al. Mechanism and wind tunnel experiment of active controlled flap on vibration load control of rotor hub［J］. Journal of Mechanical Engineering， 2023， 59（14）： 254-263 （in Chinese）.
[24]	朱棣文，胡和平. ACF旋翼主动控制技术的现状与发展［J］. 科技与创新， 2024（1）： 15-18.
	ZHU D W， HU H P. State of the art and prospectives of active control technology for smart rotor ［J］. Science and Technology & Innovation， 2024（1）： 15-18 （in Chinese）.
[25]	王华龙，张夏阳，赵国庆，等. 基于CFD/CSD耦合的TEF旋翼气弹特性高精度模拟［J］. 航空学报， 2024， 45（18）： 229904.
	WANG H L， ZHANG X Y， ZHAO G Q， et al. High-precision simulation of aeroelastic characteristics of TEF rotor based on CFD/CSD coupling［J］. Acta Aeronautica et Astronautica Sinica， 2024， 45（18）： 229904 （in Chinese）.
[26]	谭剑锋，孙义鸣，王浩文，等.共轴刚性双旋翼非定常气动干扰载荷分析［J］.北京航空航天大学学报， 2018， 44（1）： 50-62.
	TAN J F， SUN Y M， WANG H W， et al. Analysis of rigid coaxial rotor unsteady interactional aerodynamic loads［J］. Journal of Beijing University of Aeronautics and Astronautics， 2018， 44（1）： 50-62 （in Chinese）.
[27]	KRZYSIAK A， NARKIEWICZ J. Aerodynamic loads on airfoil with trailing-edge flap pitching with different frequencies［J］. Journal of Aircraft， 2006， 43（2）： 407-418.
[28]	PETERSON， RANDALL L. Full-scale hingeless rotor performance and loads： NASA-TM-110356［R］. Washington， D.C.： NASA， 1995.

参数	数值
翼型	NACA0012
弦长c/m	0.18
主翼俯仰轴到前缘	0.35c
襟翼偏转轴到前缘	0.8c
主翼与襟翼间缝隙/mm	0.5

参数	数值
翼型	NACA23012
桨叶半径R/m	4.91
桨叶片数	4
翼型弦长c/m	0.27
转速/（r·min^-1）	425
扭转/（°）	-8
桨叶根切	0.22R

参数	数值
旋翼直径D/m	6
桨叶片数	3
弦长c/m	0.18
转速/（r·min^-1）	662
扭转/（°）	-8
预锥角/（°）	1.5

参数	数值
前进比	0.197
旋翼轴前倾角/（°）	4.80
总距/（°）	8.23
横向周期变距/（°）	1.37
纵向周期变距/（°）	-1.55

工况	偏转频率/rev	偏转幅值/（°）
1	3	2，4，6
2	4	2，4，6
3	5	2，4，6
4	6	2，4，6

Influence of trailing-edge flap deflection patterns on vibration reduction of a smart rotor

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工况	偏转频率/rev	偏转幅值/（°）
5	3+4	2，4
6	4+5	2，4
7	5+6	2，4