Design of Three-loop Autopilot with Singular Perturbation Margin

doi:10.3969/j.issn.1000-1093.2018.12.012

Abstract

Abstract: A new three-loop autopilot with singular perturbation margin is designed for the problem that the traditional three-loop autopilot can not insufficiently restrain the open-loop crossover frequency in engineering application. The proposed design method is used to introduce the singular perturbation margin information into three-loop autopilot. The densign and predictor-corrector of pole open-loop crossover frequency is made for three-loop autopilot, enabling the three-loop autopilot system to restrain the open-loop crossover frequency effectively without depending on the close-loop auto-oscillation frequency of control system. The calculated singular perturbation margin value can show the performance of control system. The experimental result shows that the three-loop autopilot system with singular perturbation margin can overcome the disadvantages of the traditional three-loop autopilot. The improved autopilot can restrain the interferential information effectively and quickly, and the work efficiency of control system can be shown from singular perturbation value. Key

Key words: three-loopautopilot, singularperturbationmargin, open-loopcrossoverfrequency, predictor-corrector

CLC Number:

TJ765.2⁺32

ZHANG Heng-hao. Design of Three-loop Autopilot with Singular Perturbation Margin[J]. Acta Armamentarii, 2018, 39(12): 2380-2388.

References

［1］杨靖, 王旭刚, 王中原，等. 考虑自动驾驶仪动态特性和攻击角约束的鲁棒末制导律［J］. 兵工学报, 2017, 38(5): 900-909.
YANG Jing, WANG Xu-gang, WANG Zhong-yuan, et al. Robust terminal guidance law with autopilot lag and impact angle constraints［J］. Acta Armamentarii, 2017, 38(5): 900-909. (in Chinese)
［2］ Song T, Lin D F, Wang J. Dynamic stability of rolling missiles with angle-of-attack feedback three-loop autopilot considering parasitic effect［J］. Aerospace Science and Technology, 2017,71(5): 592-602.
［3］张凯, 杨锁昌, 张宽桥，等. 考虑导弹自动驾驶仪动态特性的新型制导律［J］. 北京航空航天大学学报, 2017, 43(8): 1693- 1704.
ZHANG Kai, YANG Suo-chang, ZHANG Kuan-qiao, et al. Novel guidance law accounting for dynamics of missile autopilot ［J］. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(8): 1693-1704. (in Chinese)
［4］刘昕戈, 刘藻珍, 单家元. 导弹系统的复合分层抗干扰自动驾驶仪设计［J］. 控制工程, 2017, 24(3): 500-504.
LIU Xin-ge, LIU Zao-zhen, SHAN Jia-yuan. Composite hierarchical anti-disturbance autopilot design for missile systems［J］. Control Engineering of China, 2017, 24(3): 500-504. (in Chinese)
［5］ Han T, Hu Q L. Robust autopilot design for STT missiles with multiple disturbances using twisting control［J］. Aerospace Science and Technology, 2017, 70(4): 428-434.
［6］ Ramesh H, Anshul T, Nandan K S. Design and simulation of autopilot control system for stratospheric airship［J］. IFAC PapersOnLine, 2016, 49(1): 712-717.
［7］ Abd-Elatif M A, Qian L J, Bo Y M. Optimization of three-loop missile autopilot gain under crossover frequency constraint［J］. Defence Technology,2016, 12(1): 32-38.
［8］李蒙, 石泳, 刘莉. 基于鲁棒H_∞的无人机飞行控制系统设计及实现［J］. 北京理工大学学报, 2016, 38(8): 807-812.
LI Meng, SHI Yong, LIU Li. Development of UAV autopilot based on robust H_∞ theory［J］. Transactions of Beijing Institute of Technology， 2016, 38(8): 807-812. (in Chinese)

［9］ Feng Z X, Guo J G, Zhou J. Robust constrained autopilot control for a generic missile in the presence of state and input constraints［J］. Optik-International Journal for Light and Electron Optics, 2017, 149(1): 49-58.

［10］孟克子, 周荻. 考虑导弹自动驾驶仪动态特性的H_∞导引律［J］. 兵工学报, 2016, 37(7): 1194-1202.
MENG Ke-zi, ZHOU Di. H_∞ guidance law accounting for dynamics of missile autopilot［J］. Acta Armamentarii, 2016, 37(7): 1194-1202. (in Chinese)

［11］ Lee J. Guidance law to control impact time and angle ［J］. IEEE Transaction on Aerospace and Electronic Systems, 2007, 43（1）:301-310.
［12］ Siddhardha K. Novel two phase algorithm to design three loop autopilot using parameter plane technique and particle swarm optimization［J］. IFAC PapersOnLine, 2016, 49(1): 830-835.
［13］ Lee L, Kim Y, Moon G. Adaptive backstepping autopilot design for missiles of fast time-varying velocity［J］. IFAC PapersOnLine, 2016, 49(17): 474-479.
［14］刁兆师. 导弹精确高效末制导与控制若干关键技术研究［D］. 北京：北京理工大学, 2015.
DIAO Zhao-shi. Research on high-precision and high-efficiency terminal guidance and control key technologies for missile ［D］. Beijing: Beijing Institute of Technology, 2015. (in Chinese)
［15］ Xu B, Yuan Y. Two performance enhanced control of flexible-link manipulator with system uncertainty and disturbances［J］.
Science China:Information Sciences, 2017, 60 (5) : 050202-1-050202-11.
［16］ Guo Z Y, Zhou J, Guo J G. Robust autopilot design for bank-to-turn missiles using adaptive dual-layer sliding mode control［J］. Optik-International Journal for Light and Electron Optics, 2017, 131: 383-398.
［17］ Lyu S, Yan X D, Tang T. Prescribed performance interceptor guidance with terminal line of sight angle constraint accounting for missile autopilot lag［J］. Aerospace Science and Technology, 2017, 69: 171-180.
［18］马悦悦. 敏捷导弹大攻角高机动飞行控制方法研究［D］. 北京：北京理工大学, 2015.
MA Yue-yue. Research on flight control design under high angle of attack maneuvering for agile missiles［D］. Beijing: Beijing Institute of Technology, 2015. (in Chinese)

［19］熊少锋, 王卫红, 刘晓东. 考虑导弹自动驾驶仪动态特性的带攻击角度约束制导律［J］. 控制与决策, 2015, 30(4): 585- 592.
XIONG Shao-feng,WANG Wei-hong,LIU Xiao-dong. Impact angle guidance law considering missile's dynamics of autopilot［J］. Control and Decision, 2015, 30(4): 585-592.(in Chinese)
［20］
商巍, 唐胜景, 郭杰. 考虑自动驾驶仪特性的自适应模糊动态面滑模制导律设计［J］. 兵工学报, 2015,36(4): 660-667.

SHANG Wei, TANG Sheng-jing, GUO Jie. Design of adaptive fuzzy dynamic surface sliding-mode guidance law considering autopilot lag［J］. Acta Armamentarii, 2015,36(4): 660-667.(in Chinese)
［21］ Davad A, Wang H P. Roll-pitch-yaw autopilot design for nonli-
near time-varying missile using partial state observer based global fast terminal sliding mode control［J］. Chinese Journal of Aeronautics, 2016, 29(5): 1302-1312.
［22］ Kedarisetty S, Vignesh N, Pulak H. Autopilot design for flexible tactical aerospace vehicle using parameter plane technique［J］. IFAC Proceedings, 2014, 47(1): 211-218.
［23］ Zhou D, Shao C T. Dynamics and autopilot design for endoatmospheric interceptors with dual control systems［J］. Aerospace Science and Technology, 2014, 13(6): 291-300.

第39卷第12期
2018 年12月兵工学报ACTA
ARMAMENTARIIVol.39No.12Dec. 2018

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