基于动态逆的BTT导弹自动驾驶仪设计

张艳; 段朝阳; 张平; 陈宗基

基于动态逆的BTT导弹自动驾驶仪设计

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

中图分类号: V 249
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出版历程
- 网络出版日期: 2007-04-30

BTT missile autopilot design based on dynamic inversion

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

摘要

摘要: 针对BTT(Bank-To-Turn)导弹的复杂非线性特性和冲压发动机带来的飞行姿态限制,在其自动驾驶仪设计问题上,指出了直接应用动态逆方法存在非最小相位特性,提出了基于动态逆的双阶段设计方法:第一阶段采用动态逆方法设计内环控制器实现攻角、侧滑角和滚转角的跟踪;第二阶段分别基于神经网络和动态逆构造攻角和滚转角速度指令生成器,实现外环对法向加速度、侧滑角和滚转角的良好跟踪效果.六自由度数学仿真验证了该方法的三通道的解耦控制能力和鲁棒性,为BTT导弹自动驾驶仪设计提供了一个可行的方案.
- 导弹 /
- 飞行动力学 /
- 非线性控制系统 /
- 神经网络
Abstract: Autopilot design for BTT (bank-to-turn) missile is difficult because of its complex nonlinear characteristics and strict flight states limit by ramjet engine. The non-minimum phase phenomenon was discussed while direct dynamic inversion method was adopted. New BTT missile control system framework was proposed using two-stage idea based on dynamic inversion. The first stage is inner loop design based on dynamic inversion to ensure the performance of attack angle, sideslip-angle and roll rate tracking. Command converters from normal acceleration to attack angle and roll angle to roll rate are the core of the outer loop on the second design stage. They are separately based on neural networks and dynamic inversion for normal acceleration and roll angle command tracking. 6 DOF (degree of freedom) simulation results show the ability of three channels- decoupling control and robustness of the proposed scheme, demonstrating its feasibility in engineering field.
- missiles /
- flight dynamics /
- nonlinear control /
- neural networks

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参考文献(1)

[1] Mracek Curtis P, Ridgely D Brett. Missile longitudinal autopilots:connections between optimal control and classical topologies AIAA Guidance, Navigation, and Control Conference and Exhibit. San Francisco:AIAA, 2005:6381 [2] Lee C H, Chung M J. Gain-scheduled state feedback control design technique for flight vehicles[J]. IEEE Transactions on Aerospace and Electronic Systems, 2001, 37(4):173-182 [3] Unnikrishnan Nishant, Balakrishnan S N. Dynamic reoptimization of a missile autopilot controller in presence of unmodeled dynamics AIAA Guidance, Navigation, and Control Conference and Exhibit. San Francisco:AIAA, 2005:6387 [4] Chris M M, Zhu J J. Bank-to-turn roll-yaw-pitch autopilot design using dynamic nonlinear inversion and PD-eigenvalue assignment Proceeding of the American Control Conference. Chicago:AIAA, 2000:1359-1364 [5] Lee S Y, Lee J I, Ha I J. Nonlinear autopilot for high maneuverability of bank-to-turn missiles[J]. IEEE Transactions on Aerospace and Electronic Systems, 2001, 37(4):1236-1253 [6] 张友安, 胡云安, 苏身榜. BTT导弹控制系统鲁棒动态逆设计[J]. 宇航学报, 2002, 23(2):89-91 Zhang Youan, Hu Yun′an, Su Shenbang. Robust dynamic inversion control for BTT missile[J]. Journal of Astronautics, 2002, 23(2):89-91(in Chinese) [7] 刘杰, 杨小良, 赵鹏. 固体冲压发动机+BTT导弹一体化设计问题讨论[J]. 航空兵器, 2002, 6:17-20 Liu Jie, Yang Xiaoliang, Zhao Peng. Solid propellant ramjet motor and BTT missile integrative design[J]. Aero Weaponry, 2002(6):17-20(in Chinese) [8] Sastry S. Nonlinear systems:analysis, stability, and control[M]. New York:Springer-Verlag, 1999:398-402

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