基于扩张状态观测器的导弹滑模制导律

张尧; 郭杰; 唐胜景; 马悦悦; 商巍

doi:10.13700/j.bh.1001-5965.2014.0127

基于扩张状态观测器的导弹滑模制导律

doi: 10.13700/j.bh.1001-5965.2014.0127

北京理工大学宇航学院, 飞行器动力学与控制教育部重点实验室, 北京 100081

基金项目: 国家自然科学基金资助项目(11202024); 航空科学基金资助项目(2012ZA720002)

详细信息

作者简介:
张尧(1991—), 男, 陕西西安人, 硕士生, 2220130035@bit.edu.cn

通讯作者:
郭杰(1981—), 男, 陕西渭南人, 讲师, guojie1981@bit.edu.cn, 主要研究方向为飞行动力学与控制.

中图分类号: TJ765.1
计量
- 文章访问数: 1200
- HTML全文浏览量: 38
- PDF下载量: 569
- 被引次数: 0
出版历程
- 收稿日期: 2014-03-17
- 网络出版日期: 2015-02-20

Missile sliding mode guidance law based on extended state observer

Key Laboratory of Dynamics and Control of Flight Vehicle of Ministry of Education, School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

摘要

摘要: 针对导弹拦截机动目标的问题,基于扩张状态观测器(ESO,Extended State Observer)设计了一种全新的导弹滑模制导律.考虑拦截时的弹目相对运动关系,通过ESO对目标加速度进行实时的观测和动态补偿,有效地解决了导弹拦截末端所需过载过大的问题,使导弹能够以更小的脱靶量拦截目标.同时在仿真中考虑自动驾驶仪的二阶动态特性,分别以不同的初始航迹角对周期性机动目标和非周期性机动目标进行拦截打击仿真,并与基于有限时间收敛理论提出的滑模制导律对迎击拦截、追击拦截和前向拦截3种方式进行仿真对比,仿真结果表明了基于ESO的滑模制导律在拦截末制导过程中的鲁棒性和优越性.
- 扩张状态观测器 /
- 滑模控制 /
- 观测 /
- 有限时间收敛 /
- 导弹制导 /
- 拦截
Abstract: Based on the technology of extended state observer (ESO), a novel missile sliding mode guidance law was derived to intercept maneuvering target. According to relative movement between missile and target in the process of interception, the difficult question was effectively settled that too large overload was required during terminal intercepting phase, which was addressed by currently estimating and dynamically compensating to target acceleration via ESO. Thus, the goal of precision against target was achieved. Moreover, accounting for the autopilot as second-order dynamics in simulation, three simulation experiments of different interception strategies, which included head-on interception, tail-chase interception and head-pursuit interception, were investigated in the two kinds of cases of intercepting periodic maneuvering target and aperiodic maneuvering target. Compared with sliding mode guidance law based on finite time convergence, the results show the strong robustness and validities of the proposed sliding mode guidance law based on ESO in the terminal interception guidance.
- extended state observer /
- sliding mode control /
- observation /
- finite time convergence /
- missile guidance /
- interception

HTML全文

参考文献(15)

[1]	Zhang Q Z, Wang Z B,Tao F.Optimal guidance law design for impact with terminal angle of attack constraint[J].Optik,2014,125(1):243-251.
[2]	Hexner G, Shima T.Stochastic optimal control guidance law with bounded acceleration[J].IEEE Transaction on Aerospace and Electronic Systems,2007,43(1):71-78.
[3]	张友安,黄诘, 孙阳平.带有落角约束的一般加权最优制导律[J].航空学报,2014, 35(3):848-856. Zhang Y A,Huang J,Sun Y P.Generalized weighted optimal guidance laws with impact angle constraint[J].Acta Aeronautica et Astronautica Sinica,2014,35(3):848-856(in Chinese).
[4]	Zhang Z X, Li S H,Luo S.Terminal guidance laws of missile based on ISMC and NDOB with impact angle constraint[J].Aerospace Science and Technology,2013,31(1):30-41.
[5]	朱凯,齐乃明. 基于滑模干扰观测器的垂直攻击末制导律研究[J].兵工学报,2011,32(12):1462-1467. Zhu K,Qi N M.Research on vertical impact terminal guidance law based on sliding mode disturbance observer[J].Acta Armamentrii,2011,32(12):1462-1467(in Chinese).
[6]	马克茂,马杰. 机动目标拦截的变结构制导律设计与实现[J].宇航学报,2010,31(6):1589-1595. Ma K M,Ma J.Design and implementation of variable structure guidance law for maneuvering target interception[J].Journal of Astronautics,2010,31(6):1589-1595(in Chinese).
[7]	窦荣斌,张科. 基于二阶滑模的再入飞行器末制导律研究[J].宇航学报,2011,32(10):2109-2114. Dou R B,Zhang K.Research on terminal guidance law for re-entry vehicle based on second-order sliding mode control[J].Journal of Astronautics,2011,32(10):2109-2114(in Chinese).
[8]	熊俊辉,唐胜景, 郭杰,等.基于模糊变系数策略的迎击拦截变结构制导律设计[J].兵工学报,2014,35(1):134-139. Xiong J H,Tang S J,Guo J,et al.Design of variable structure guidance law for head-on interception based on variable coefficient strategy[J].Acta Armamentarii,2014,35(1):134-139(in Chinese).
[9]	Moosapour S S, Alizadeh G,Khanmohammadi S,et al.A novel robust proportional navigation guidance law design for missile considering autopilot dynamic[J].Transactions of the Institute of Measurement and Control,2013,35(3):703-710.
[10]	王嘉鑫,林德福, 宋韬.引入参考目标的比例导引制导律研究[J].航天控制,2013,31(6):31-35. Wang J X,Lin D F,Song T.The proportional navigation guidance law with reference object[J].Aerospace Control,2013,31(6): 31-35(in Chinese).
[11]	Shtessel Y, Shkolnikov L,Levant A.Guidance and control of missile interceptor using second-order sliding modes[J].IEEE Transaction on Aerospace and Electronic Systems,2009,45(1): 110-124.
[12]	Zhou D, Sun S.Guidance laws with finite time convergence[J]. Journal of Guidance,Control,and Dynamics,2009,32(6): 1838-1846.
[13]	马悦悦,唐胜景, 郭杰,等.基于自抗扰和模糊逻辑的大攻角控制系统设计[J].系统工程与电子技术,2013,35(8):1711-1716. Ma Y Y,Tang S J,Guo J,et al.High angle of attack control system design based on ADRC and fuzzy[J].Systems Engineering and Electronics,2013,35(8):1711-1716(in Chinese).
[14]	Bhat S P, Bernstein D S.Finite-time stability of continuous autonomous systems[J].SIAM Journal of Control and Optimization,2000,38(8):751-766.
[15]	韩京清. 自抗扰控制技术——估计补偿不确定因素的控制技术[M].北京:国防工业出版社,2008:221-237. Han J Q.Active disturbance rejection control technique：the technique for estimating and compensating the uncertainties[M].Beijing:National Defence Industry Press,2008:221-237.