基于自适应反演法的导弹直/气复合制导

张天宇; 董长虹

基于自适应反演法的导弹直/气复合制导

北京航空航天大学宇航学院, 北京 100191

详细信息

中图分类号: V 448
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- 被引次数: 0
出版历程
- 收稿日期: 2012-07-13
- 网络出版日期: 2013-07-30

Compound control system design based on adaptive backstepping theory

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 防空导弹要求能够应对高速、高机动性等复杂对抗环境,直接力/气动力复合制导是防空导弹制导系统设计的关键技术.主要研究了直接力/气动力复合控制导弹的控制律、操纵律以及制导律,针对非线性系统,提出了一种基于自适应反演理论的控制方法;直/气复合切换逻辑采用模糊方法;末制导段应用变结构制导律.以某防空导弹为例进行仿真,结果表明该复合制导方法易于实现,对于高机动目标具有良好的制导精度,显示了该方法的有效性.
- 复合制导 /
- 非线性 /
- 自适应反演理论 /
- 变结构制导律
Abstract: Combat environment for air-defense missile is very complex, for example, high-speed and high- maneuverability. Reaction-jet and aerodynamics compound control and guidance technology is the crucial problem of air-defense missile control and guidance system design. The control law and guidance laws for reaction-jet and aerodynamics compound guidance missile were investigated. A control method based on adaptive backstepping theory was put forward for the non-linear system. Fuzzy logic was applied to the design of compound steering law. A variable structure guidance law was proposed for 3-D terminal interception. Taking an anti-air missile as an example, simulation results show that the guidance and control system is easy to realize and has fine guidance precision for a high-speed maneuvering target, and it proves the effectiveness of the method.
- compound guidance /
- nonlinear system /
- adaptive backstepping theory /
- variable structure guidance law

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参考文献(8)

[1]	Shtessel Y B,Shkolnikov I A,Levant A.Guidance and control of missile intercaptor using second-order sliding modes[J].Aerospace and Electronic Systems,2009,45(1):110-124
[2]	Jin Y C,Dongkyoung C.Adaptive control based on a parametric affine model for tail-controlled missiles[J].Aerospace and Electronic Systems,2006,42(2):659-669
[3]	杨志峰,雷虎民,李庆良,等.基于动态逆和鲁棒轨迹跟踪控制的导弹控制系统设计[J].宇航学报,2011,32(2):317-322 Yang Zhifeng,Lei Humin,Li Qingliang,et al.A missile control system design approach based on dynamic inverse and robust trajectory tracking control [J].Journal of Astronautics,2011,32(2):317-322(in Chinese)
[4]	朱隆魁,汤国建,余梦伦.防空导弹直接力/气动力复合控制系统设计[J].宇航学报,2008,29(6):1895-1900 Zhu Longkui,Tang Guojian,Yu Menglun.Compound control system design with direct thrust and aerodynamic force for air defence missile [J].Journal of Astronautics,2008,29(6):1895-1900(in Chinese)
[5]	Zhong L,Jia X H.Novel backstepping design for blended aero and reaction-jet missile autopilot[J].System Engineering and Electronics,2008,19(1):148-153
[6]	展建超,杨军,谭震.基于变结构控制的气动力/直接力切换控制设计[J].弹箭与制导学报,2009,29(2):83-86 Zhan Jianchao,Yang Jun,Tan Zhen. Aerodynamic/reaction-jet switching-controller design based on variable structure control[J].Journal of Projectiles,Rockets,Missiles and Guidance,2009,29(2):83-86(in Chinese)
[7]	任义元,袁建平,方群.空空导弹变结构末制导律研究[J].计算机仿真,2009,26(10):25-29 Ren Yiyuan,Yuan Jianping,Fang Qun.A study of terminal variable structure guidance law of air-to-air missile [J].Computer Simulation,2009,26(10):25-29(in Chinese)
[8]	Yeh F K.Adaptive-sliding-mode guidance law design for missiles with thrust vector control and divert control system[J].Control Theory & Application,2012,6(4):552-559