基于自适应滤波的电控旋翼桨距控制试验

陆洋; 董维生; 洪亮; 冯剑波

基于自适应滤波的电控旋翼桨距控制试验

南京航空航天大学直升机旋翼动力学国家级重点实验室,南京 210016

基金项目: 国家自然科学基金(50805074); 航空科技创新基金(08A52001)

计量
- 文章访问数: 1712
- HTML浏览量: 102
- PDF量: 1392
- 被引次数: 0
出版历程
- 收稿日期: 2011-12-05
- 刊出日期: 2012-12-28

Experiment on blade pitch control of electrically controlled rotor based on adaptive filter control algorithm

National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 提出了基于自适应滤波的电控旋翼桨距控制方法,并基于此开发了双闭环电控旋翼桨距控制系统,利用模型电控旋翼试验台进行了悬停状态下的桨距控制试验.试验结果表明:所研制的双闭环电控旋翼桨距控制系统能够有效、可靠地实现襟翼操纵和桨距控制.基于自适应滤波的桨距控制律可以很好地实现电控旋翼的总距、周期变距以及总距耦合周期变距操纵;桨距响应幅值满足要求,相位滞后约在10°～15°之间;从襟翼偏转到桨叶变距响应的滞后约20°～30°.不同桨叶/襟翼自身的结构及气动特性差异,会一定程度的影响桨距控制的实际效果.
- 电控旋翼 /
- 襟翼 /
- 桨距 /
- 自适应滤波 /
- 桨距控制试验
Abstract: A new control algorithm based on the adaptive filter in time domain was brought forward.Based on this, the control system of electrically controlled rotor (ECR) blade pitch with double closed-loop was developed.Then, utilizing the test rig of model ECR, the pitch control experiments were performed in hover state.The experiments show that the developed control system of ECR blade pitch can work reliably through the tests.The control law based on the adaptive filter is successful in ECR collective pitch control, cyclic pitch control and collective pitch mixing with cyclic pitch control.The amplitude of the blade pitch was fitted well with the expected value, and the phase lag was about 10°～15°.The phase lag between the servo flap deflection and the response of blade pitch was about 20°～30°.Because of the structural and aerodynamic differences among different blades and servo flaps, the effect of blade pitch control will be reduced to some extent.
- electrically controlled rotor(ECR) /
- servo flap /
- blade pitch /
- adaptive filter /
- blade pitch control experiment

HTML

参考文献(16)

[1]	陆洋.电控旋翼系统研究[D].南京:南京航空航天大学,2004.LU Yang.Research on the electrically controller rotor system[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2004.(in Chinese)
[2]	Ormiston R A.Aeroelastic considerations for rotorcraft primary control with on-blade elevons[C]//American Helicopter Society 57th Annual Forum.Washington:AHS,2001:464-481.
[3]	Shen J,Chopra I.Aeroelastic stability of trailing-edge flap helicopter rotors[J].Journal of American Helicopter Society,2003,48(4):236-243.
[4]	Bao J,Allen K,Chopra I.Design and test of a Mach scale swashplateless rotor using smart trailing-edge flaps[C]//American Helicopter Society 62th Annual Forum.Phoenix:AHS,2006:622-631.
[5]	Copp P,Chopra I.Continued development of a Mach scale swashplateless rotor with integrated trailing edge flaps[C]//American Helicopter Society 64th Annual Forum.Montréal:AHS,2008:327-335.
[6]	Falls J,Datta A,Chopra I.Design and analysis of trailing-edge flaps and servotabs for primary control[J].Journal of American Helicopter Society,2010,55(3):5-15.
[7]	Lorber P F,Oneill J O,Isbella B.Whirl test of a large scale high authority active flap rotor[C]//American Helicopter Society 66th Annual Forum.Phoenix:AHS,2010:218-236.
[8]	陆洋,王浩文,高正.电控旋翼气弹设计参数研究[J].南京航空航天大学学报,2004,36(6):697-702.LU Yang,WANG Haowen,GAO Zheng.Aeroelastic parameter design for electrical controlled rotor[J].Journal of Nanjing University of Aeronautics & Astronautics,2004,36(6):697-702.(in Chinese)
[9]	陆洋,王浩文,高正.原理性电控旋翼系统试验研究[J].空气动力学报,2006,24(2):250-255.LU Yang,WANG Haowen,GAO Zheng.Experimental research on the testing electrically controlled rotor system[J].Acta Aerodynamica Sinica,2006,24(2):250-255.(in Chinese)
[10]	陆洋,王浩文,高正.电控旋翼气弹动力学建模研究[J].航空动力学报,2006,21(6):1022-1026.LU Yang,WANG Haowen,GAO Zheng.Aeroelastic dynamic modeling of the electrically controlled rotor[J].Journal of Aerospace Power,2006,21(6):1022-1026.(in Chinese)
[11]	夏鹤鸣,陆洋.悬停状态电控旋翼桨距控制[J].航空动力学报,2009,24(10):2213-2220.XIA Heming,LU Yang.Study on the blade pitch control of electrically controlled rotor in hover[J].Journal of Aerospace Power,2009,24(10):2213-2220.(in Chinese)
[12]	Roget B,Chopra I.Wind-tunnle testing of rotor with individually controlled traling-edge flaps for vibtation reduction[J].Journal of Aircraft,2008,45(3):868-879.
[13]	杨铁军,顾仲权,鲁明月.基于误差通道在线辨识的直升机结构振动主动控制研究[J].航空学报,2004,25(1):36-40.YANG Tiejun,GU Zhongquan,LU Mingyue.Investigation of the active control of helicopter structural vibration with online secondary path modeling[J].Acta Aeronautica et Astronautica Sinica,2004,25(1):36-40.(in Chinese)
[14]	Hong L,Lu Y.Simulation of adaptive blade pitch control for electrically controlled rotor[C]//International Conference on Intelligent System Design and Engineering Application.Changsha:Hunan University of Technology,2010:374-377.
[15]	Dong W,Lu Y.Improved algorithm simulation of adaptive blade pitch control for electrically controlled rotor[C]//International Conference on Intelligent System Design and Engineering Application.Sanya:Hunan University of Technology,2012:691-695.
[16]	Lan H,Zhang M,Ser W.A weight-constrained Fx-LMS algorithm for feed forward active noise control systems[J].IEEE Signal Processing Letters,2003,9(1):1-4.