Volume 33 Issue 04
Apr.  2007
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Zhang Yan, Duan Chaoyang, Zhang Ping, et al. BTT missile autopilot design based on dynamic inversion[J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(04): 422-426. (in Chinese)
Citation: Zhang Yan, Duan Chaoyang, Zhang Ping, et al. BTT missile autopilot design based on dynamic inversion[J]. Journal of Beijing University of Aeronautics and Astronautics, 2007, 33(04): 422-426. (in Chinese)

BTT missile autopilot design based on dynamic inversion

  • Publish Date: 30 Apr 2007
  • 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.

     

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  • [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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