Design and verification of double-loop control electromechanical actuator system

ZHANG Yue; HAN Xue-feng

doi:10.3788/OPE.20152311.3138

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Design and verification of double-loop control electromechanical actuator system

更新时间：2020-08-13

- Design and verification of double-loop control electromechanical actuator system
- Optics and Precision Engineering Vol. 23, Issue 11, Pages: 3138-3146(2015)
- 作者机构：
  
  中国科学院长春光学精密机械与物理研究所,吉林长春,中国,130033
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20152311.3138
  CLC： V472.13;V241
- Received：09 December 2014，
  
  Revised：07 February 2015，
  
  Published：25 November 2015
- 稿件说明：
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张跃, 韩雪峰,. 双环控制电动舵机系统的设计验证[J]. 光学精密工程, 2015,23(11): 3138-3146

ZHANG Yue, HAN Xue-feng,. Design and verification of double-loop control electromechanical actuator system[J]. Editorial Office of Optics and Precision Engineering, 2015,23(11): 3138-3146
张跃, 韩雪峰,. 双环控制电动舵机系统的设计验证[J]. 光学精密工程, 2015,23(11): 3138-3146 DOI： 10.3788/OPE.20152311.3138.

ZHANG Yue, HAN Xue-feng,. Design and verification of double-loop control electromechanical actuator system[J]. Editorial Office of Optics and Precision Engineering, 2015,23(11): 3138-3146 DOI： 10.3788/OPE.20152311.3138.

摘要

针对空空导弹的电动舵机系统

提出了基于传动机构主模态的控制方案

并利用机构动态特性匹配和主模态法设计了双环控制系统。对曲柄滑块机构中的连杆进行分析

利用机构动态特性匹配和主模态方法将高阶多自由度动力学模型简化为二自由度自由转子模型。对二自由度模型与控制系统联合建模

分析机构在有无阻尼状态时谐振主频对系统开环截止频率的影响

确定了按照无阻尼状态进行系统设计更为可靠。最后

对传动机构进行了模态测试

确定了机构动态特性匹配设计方法的可行性。结合风洞测试数据在全弹道飞行平台上对含机构主模态的舵机系统进行了性能验证。模态测试结果表明:固支舵面第一阶扭转频率为1210.47 rad/s

传动机构(含舵面)第一阶扭转频率为1148.17 rad/s

与理论1180.0 rad/s结果一致。全弹道飞行平台外载荷验证显示:最大铰链力矩为6.8 Nm时

舵面弹性转角为1.1

舵机跟踪自驾仪指令最大误差为0.1

这些结果满足舵机系统对性能指标的要求。

Abstract

A control scheme for the electromechanical actuator systems in air-to-air missiles was propose based on main modal of a transmission mechanism. and a double-loop control system was designed by matching mechanism dynamic characteristics and main modal method. Firstly

a connecting rod from crank slider mechanism was analyzed and the high order multi-degree-of-freedom dynamic model was simplified into two-degree-of-freedom free rotor model by matching mechanism dynamic characteristics and the main modal method. Then

the two-degree-of-freedom model and control system were modeled jointly to analyze the influence of main resonator model on the cutoff frequency of open-loop system with or without damping states. By which it makes sure that it is more reliable when the system is analyzed at the undamped state. Finally

a modal test was performed for the transmission mechanism and the feasibility of modal dynamic characteristic matching method was confirmed. A performance verification test was done for the electromechanical actuator system containing main model on a whole trajectory flying platform according to the data from wind tunnel measurement. The results show that the first order torsional frequency of clamped support control surface is 1210.47 rad/s

and that of the transmission modal(consist of the control surface) is 1148.17 rad/s

which is consistent with the theoretical result of 1180.0 rad/s. The external loading verification of whole trajectory flying platform indicates that the actuator system meets the demand of performance index when the maximum hinge moment is 6.8 Nm

the elastic angle of control surface is 1.1and the actuator maximum error of instruction from a tracking autopilot is 0.1.

关键词

Keywords

references

汪军林,谢付强,刘玉浩. 导弹电动舵机的研究现状及发展趋势[J]. 飞航导弹,2008(3):42-46. WANG J L, XIE F Q, LIU Y H. The reasearch status and development of missileelectromechanical actuator[J].Winged Missile Journal,2008(3):42-46.(in Chinese)

林忠万. 基于 DSP 的导弹舵机伺服控制系统的研究[D]. 西安:西北工业大学,2004. LIN ZH W.Study on actuation DC servo system based on DSP[D]. Xi'an:Northwestern Polytechnical University, 2011.(in Chinese)

VACULIK S A. A framework for electromechanical actuator design[D]. State of Texas:The University of Texas at Austin,2008.

李永锋. 电动舵机控制器的研究[D]. 北京:北京理工大学, 2006. LI Y F.Study on the controller of electromechanical actuator[D].Beijing:Beijing Institute of Technology,2006.(in Chinese)

HABIBI S S, ROACH J, LUECKE G. Inner-loop control for electromechanical(EMA) flight surface actuation systems[J]. Journal of dynamic systems, measurement,and control,2008, 130:0510021-13.

HEWSON R. Air-to-air missiles beyond visual range, United States AIM-120 AMRAAM[C]. Jane's Air Launched Weapons, 2005.

韩雪峰. 含间隙刚柔耦合电动舵机关键技术研究[D]. 长春:中国科学院长春光学精密机械与物理研究所,2011. HAN X F.Research on the Key Technology of Rigid-flexible Coupling Electric Actuator Servo System with Clearance[D].Changchun:Chang-chun Institute of Optics,Fine Mechanics and Physics,Chinese Academy of Science,2011.(in Chinese)

肖前进. 电动舵机伺服系统非线性辨识及补偿[J]. 光学精密工程,2013,8(21):2038-2047. XIAO Q J. Identification and compensation of nonlinearity for electromechanical actuator servo system[J].Opt. Precision Eng.. 2013,8(21):2038-2047.(in Chinese)

张明月. 改进自抗扰控制谐波式电动舵机伺服系统[J]. 光学精密工程,2014,1(22):99-108. ZHANG M Y. Servo system of harmonic drive electromechanical actuator using improvedADRC[J].Opt. Precision Eng., 2014,1(22):99-108.(in Chinese)

崔业兵. 一种高带宽四舵翼电动舵机的可行性研究[J]. 电机与控制学报,2012,12(16):87-93. CUI Y B. Feasibility of bandwidth four rudder wings electromechanical actuator[J].ELECTRIC MACHINES AND CONTROL, 2012,12(16):87-93.(in Chinese)

王乐. 高速飞行器电动舵机伺服系统动力学仿真[D]. 哈尔滨:哈尔滨工业大学,2013. WANG L.Dynamic Simulation for Electromechanical Actuator Servo System of High-speed Vehicle[D].Harbin:Harbin Institute of Technology,2013.(in Chinese)

王广雄,何朕. 控制系统设计[M]. 北京:清华大学出版社,2008. WANG G X,HE ZH. Control System Design[M]. Beijing:Tsinghua University Press,2008.(in Chinese)

章家保. 电动舵机伺服系统的模型辨识及其校正[J]. 光学精密工程,2008,10(16):1971-1976. ZHANG J B, et al..Model identification and corrector design for servo system ofelectromechanical actuator[J].Opt. Precision Eng.,2008,10(16):1971-1976.(in Chinese)

章家保. 电动舵机的参数平衡设计[J]. 弹箭与制导学报,2013,5(33):29-34. ZHANG J B.Parameter balance design of electromechanical actuator[J].Journal of Projectiles'Rockets' Missiles and Guidance,2013,5(33):29-34.(in Chinese)

HAN X F,LIU B.Design and analysis of power system of micro-electromechanical actuator[C].IEEE 2010 2nd International Conference on Industrial Mechatronics and Automation, 2010,298-302.

HAN X F,GE M.The effect of backlash nonlinear on resonance frequency of actuator transmission system[C].IEEE 2011 3rd International Conference on Advanced Computer Control, 2011,586-590.

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