基于动态逆和分散控制的导弹控制系统设计

曾宪法; 张磊; 申功璋

基于动态逆和分散控制的导弹控制系统设计

北京航空航天大学自动化科学与电气工程学院, 北京 100083

详细信息

作者简介:
曾宪法(1982－),男,湖南怀化人,硕士生,xianfa110@163.com.

中图分类号: TP 273
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- 文章访问数: 3234
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- PDF下载量: 1110
- 被引次数: 0
出版历程
- 收稿日期: 2006-11-20
- 网络出版日期: 2007-11-30

Design of control systems for missiles based on dynamic inversion and decentralized control

School of Automation Science and Electrical Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 针对导弹六自由度非线性模型,根据时标分离原理将导弹系统分为快慢不同的4个回路.以快回路和较慢回路为例,提出在快回路和较慢回路中设计动态逆控制器以实现非线性解耦控制,并在较慢回路中设计鲁棒分散控制器以补偿整个控制系统的不确定性及干扰.鲁棒分散控制器结构简单,且不依赖于被控对象精确的数学模型.仿真结果表明,按照该方法设计的导弹闭环控制系统具有良好的稳态性能和动态性能,鲁棒性强.
- 动态逆 /
- 鲁棒分散控制 /
- 导弹
Abstract: Based on the nonlinear six degree-of-freedom missile model, the missile system was separated into four loops according to time-scale separation principle. Taking account of the fast loop and the relatively slow loop, the dynamic inversion controllers were designed in both of the two loops for decoupling control, and the robust decentralized controller was designed in the relatively slow loop to compensate the uncertainty and disturbances of the whole system. The robust decentralized controller has a simple structure and does not rely on the accurate mathematical model. Finally, the simulation results show that the closed-loop control system which is designed according to the approach achieves both good steady performance and dynamic performance, and its robust performance is also excellent.
- dynamic inversion /
- robust decentralized control /
- missile

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参考文献(1)

[1] Snell S A. Nonlinear inversion flight control for a superma- neuverable aircraft[J]. Journal of Guidance,Control and Dynamics,1992,15(4):976-984 [2] 李扬,陈万春. 高超声速飞行器BTT非线性控制器设计与仿真[J]. 北京航空航天大学学报,2006,32(3):249-253 Li Yang,Chen Wanchun. Design and simulation of BTT nonlinear controller for hypersonic vehicle[J]. Journal of Beijing University of Aeronautics and Astronautics,2006,32(3):249-253(in Chinese) [3] McFarland M B. Augmentation of gain-scheduled missile autopilot using adaptive neural networks. AIAA-98-4491,1998 [4] Lin C F,Yu T J,Ge J H,et al. Nonlinear H_∞ flight control system design for aircraft. AIAA-97-3697,1997 [5] Tornambe A. A decentralized controller for the robust stabilization of a class of MIMO dynamic systems[J]. Journal of Dynamic Systems,Measurement and Control,1994,116:293-304 [6] 陈金莉,李东海,孙先仿. 航天器姿态的非线性鲁棒分散控制器设计[J]. 宇航学报,2006, 27(1):6-11 Chen Jinli,Li Donghai,Sun Xianfang. Nonlinear robust decentralized controller design for spacecraft attitude control system[J]. Journal of Astronautics,2006,27(1):6-11(in Chinese) [7] 钱杏芳,林瑞雄,赵亚男.导弹飞行力学[M].北京:北京理工大学出版社,2006:2-80 Qian Xingfang, Lin Ruixiong, Zhao Yanan. Missile flight dynamics[M]. Beijing:Beijing Institute of Technology Press, 2006:2-80(in Chinese) [8] 吴天宝,黄显林,卢鸿谦,等. 基于非线性动态逆方法的TF/TA控制器设计[J]. 宇航学报,2004,25(3):289-294 Wu Tianbao,Huang Xianlin,Lu Hongqian,et al. Design of a TF/TA controller for cruise missile using nonlinear dynamic inversion[J]. Journal of Astronautics,2004,25(3):289-294(in Chinese) [9] Menon P K,Iragavarapu V R, Ohlmeyer E J. Nonlinear missile autopilot design using time-scale separation. AIAA-97-3765, 1997 [10] 张友安,胡云安. 导弹控制和制导的非线性设计方法[M]. 北京:国防工业出版社,2003:9-77 Zhang Youan,Hu Yunan. Nonlinear design approaches for missile control and guidance[M]. Beijing:National Defence Industry Press, 2003:9-77(in Chinese)

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