电光与控制, 2014, 21 (3): 66, 网络出版: 2014-03-14  

高超声速滑翔式BTT导弹鲁棒反演控制器设计

Robust Backstepping Controller Design for the Supersonic Gliding BTT Missile
作者单位
1 空军工程大学航空航天工程学院,西安710038
2 陕西飞机工业(集团)有限公司军事代表室,陕西 汉中723213
摘要
综合考虑高超声速滑翔式BTT导弹各种干扰的影响,建立了具有非匹配不确定性的非线性、强耦合姿态运动方程,并转化为标准形式。针对模型中的未知不确定性,提出了鲁棒估计函数,利用反演控制和自适应控制设计了高超声速导弹的自动驾驶仪,解决了由于对期望虚拟控制量进行求导产生的“计算膨胀”问题,证明了每一步反演设计的Lyapunov稳定性,并进行了数字仿真。仿真结果表明,所设计的自适应反演控制器能够精确跟踪姿态角指令,并对大范围气动参数摄动具有很强的鲁棒性。
Abstract
Considering the impact of various interferences, the attitude motion equations of the supersonic gliding BTT missile were built up, which are nonlinear, high coupling and comprising many non-matching uncertainties.And the pneumatic parameters are fit using nonlinear method.To the unknown uncertainties, a robust estimating function was put forward, and an autopilot was designed for the supersonic missile by using adaptive control and backstepping control.The problem of “calculation expansion”, caused by derivation to the virtual expectation controlled variable, was solved.The Lyapunov stability for each step backstepping design was proved.Finally, the approach was applied to the simulation of the design of the control system of BTT-missile.The results turn out that the robust adaptive backstepping design approach has good tracking ability and strong robustness for the aerodynamic parameters perturbation.
参考文献

[1] 王坚浩.非线性系统Backstepping滑模变结构控制及其应用研究[D].西安:空军工程大学,2011.

    WANG J H.The research of the backstepping slide vari-structure control and applications for the nonlinear system[D].Xian:Air Force Engineering University, 2011.

[2] KIM S H, KIM Y S, SONG C H.A robust adaptive nonlinear control approach to missile autopilot design[J].Control Engineering Practice, 2004, 12:149-154.

[3] ZHANG Y, WANG Q, CHEN Y, et al.Decentralized sliding mode control for bank-to-turn missile with backstepping technique[C]// The 2nd International Asia Conference on Informatics in Control, Automation and Robotics, 2010:537-540.

[4] HUANG S J, ZHAO Z W, LUO Q.Design for BTT missile controller base on the RBF neural networks[C]//Proceedings of the 26th Chinese Control Conference,Zhangjiajie, 2007:91-95.

[5] ZHAO H C, GU W J, HU Y M, et al.Second-order sliding mode control for aerodynamic missiles using backstepping design[C]//Proceedings of the 5th World Congress on Intelligent Control and Automation,Hangzhou, 2004:5471- 5474.

[6] ZHU K, QI N M, GUAN Y Z, et al.A simplified backstepping sliding mode controller based on adaptive control for BTT missiles[C]//Proceedings of the 2009 IEEE International Conference on Mechatronics and Automation, Changchun, 2009:4583-4588.

[7] 朱凯,齐乃明,秦昌茂.BTT导弹的自适应滑模反演控制设计[J].宇航学报,2010,31(3):769-773.

    ZHU K, QI N M, QIN C M.Adaptive sliding mode controller design for missile based on backstepping control[J].Journal of Astronautics, 2010, 31(3):769-773.

[8] KESHMIRI S, COLGREN R.Six DOF nonlinear equations of motion for a generic hypersonic vehicle[C]//AIAA Atmospheric Flight Mechanics Conference and Exhibit, South Carolina, US, 2007.

[9] 彭冠一.防空导弹制导控制系统设计[M].北京: 宇航出版社,1996.

    PENG G Y.The design of the guidance and control system for air defense missile[M].Beijing:Astronautic Publishing House, 1996.

[10] BOLLINO K P, ROSS I M, DOMAN D D.Optimal nonlinear feedback guidance for reentry vehicles[C]//Proceeding of AIAA Guidance, Navigation, and Control Confe-rence and Exhibit, 2006:563-582.(上接第65页)

    MEI X S, TAO T, TSUTSUMI M, et al.Study on friction error of high-speed high-precision NC servo table [J].Chinese Journal of Mechanical Engineering, 2001,37(6):76-81.

[11] 吴俊清.相位差的数字化测量研究[J].应用基础与工程科学学报,2005,13(1):99-104.

    WU J Q.Research of digital measurement for phase difference [J].Journal of Basic Science and Engineering, 2005,13(1):99-104.

[12] 陈连华,赵娜,王奕博,等.一种快速单步的频率特性测试方法[J].电子测量技术,2011,34(2):77-79.

    CHEN L H, ZHAO N, WANG Y B, et al.Fast frequency response testing method with one step [J].ElectronicMeasurement Technology, 2011,34(2):77-79.

[13] 朱萌,曹国武,张志伟,等.基于Levy法的气动舵机系统辨识[J].弹箭与制导学报,2011,31(6):69-72.

    ZHU M,CAO G W, ZHANG Z W, et al.The system identification of pneumatic actuator based on levy method [J].Journal of Projectiles,Rockets, Missiles and Gui-dance, 2011,31(6):69-72.

[14] 阂跃军,薛旭.基于频域的挠性摆式加速度计表头参数辨识方法[J].中国惯性技术学报,2008,16(1):94-98.

    MIN Y J,XUE X.Parameter identification method based on frequency domain of flexure hinged pendulum acce-lerometer [J].Journal of Chinese Inertial Technology, 2008,16(1):94-98.

国海峰, 黄长强, 丁达理, 肖红, 张强. 高超声速滑翔式BTT导弹鲁棒反演控制器设计[J]. 电光与控制, 2014, 21(3): 66. GUO Hai-feng, HUANG Chang-qiang, DING Da-li, XIAO Hong, ZHANG Qiang. Robust Backstepping Controller Design for the Supersonic Gliding BTT Missile[J]. Electronics Optics & Control, 2014, 21(3): 66.

关于本站 Cookie 的使用提示

中国光学期刊网使用基于 cookie 的技术来更好地为您提供各项服务,点击此处了解我们的隐私策略。 如您需继续使用本网站,请您授权我们使用本地 cookie 来保存部分信息。
全站搜索
您最值得信赖的光电行业旗舰网络服务平台!