带落角约束的导弹制导控制一体化最优控制律设计  

Integrated Optimal Control Law Design for Missile Guidance and Control with Terminal Impact Angle Constraint

作　　者：付主木[1] 赵晨东 孙兴龙[1] FU Zhu-mu ZHAO Chen-dong SUN Xing-long(Information Engineering College, Henan University of Science and Technology, Luoyang 471023, China)

机构地区：[1]河南科技大学信息工程学院,河南洛阳471023

出　　处：《电光与控制》2017年第8期5-8,43,共5页Electronics Optics & Control

基　　金：国家自然科学基金(61473115);国家航空科学基金(20110142003);河南省科技创新人才杰出青年计划资助项目(144100510004)

摘　　要：带有落角约束的空地导弹制导控制一体化设计,可有效提高导弹的制导精度和毁伤效果,已成为当今研究的热点之一。针对小型空地导弹建立俯仰平面导弹一体化模型,同时为实现落角约束,将其转化为含有落角约束项的线性系统;继而采用线性二次型最优控制方法设计带落角约束的导弹一体化最优控制律;最后对所设计的控制律与一种滑模变结构控制律做仿真对比,结果表明导弹在所提设计控制律作用下,既可以保证导弹的制导精度,实现落角约束,同时也可以保证弹道的平滑,缩短制导时间,体现出了良好的性能。The integrated guidance and control design of ground missiles with angular constraints can effectively improve the guidance precision and destructive effect of missiles, which has become a hot topic in recent researches. Firstly, the integrated model of small air-to-ground missiles in pitch plane was established. It was transformed into a linear system containing angular constrain in order to achieve the angular constraint. Then, the linear quadratic optimal control method was used to design the integrated optimal control law of missiles with angle constraint. Finally, simulation was made to compare the designed control law with the sliding mode variable structure control law. The simulation results show that the optimal control law can not only ensure the accuracy of the missile guidance with angular constraint, but also can guarantee smooth trajectory and shorten the time of guidance, which shows good performance for missiles.

关 键 词：导弹制导 落角约束 最优控制 一体化 线性二次型 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]