带落角约束的导弹滑模制导控制一体化设计  

Integrated Design of Missile Guidance and Control with Terminal Impact Angle Constraint Based on Sliding-mode Control

作　　者：赵晨东 宋书中[1] 付主木[1] 

机构地区：[1]河南科技大学信息工程学院,河南洛阳471023

出　　处：《计算机测量与控制》2016年第1期128-131,共4页Computer Measurement &Control

基　　金：国家自然科学基金资助(61473115);国家航空科学基金资助(20110142003);河南省高校科技创新人才支持计划资助(13HASTIT038)

摘　　要：为了提高导弹的制导精度和毁伤效果,研究了带有落角约束的空地导弹制导控制一体化设计问题;在俯仰平面内,将弹—目相对运动方程和导弹力学方程相结合,建立了导弹一体化模型;在此基础上,采用反演递推方法,设计了带有落角约束的导弹自适应滑模制导控制一体化算法,并对其进行了稳定性分析;针对所设计的控制律,在不同的机动目标下进行了仿真和对比分析;结果表明,导弹的脱靶量均小于1m,落角接近-90°,满足制导精度和末端落角约束条件。In order to improve the guidance precision and the damage effect, the problem of integrated guidance and control design of air-to-ground missile with impact angle constraint was studied. In pitch plane, the integrated model was established by combining the relative motion equation for missile and target with the dynamical equation of missile. Based on the integrated model, an adaptive sliding-mode integrated guidance and control law with terminal impact angle constraint was designed using the methods of playback design, and the system stability was analyzed. The simulation results of the missile with different maneuvering targets demonstrate that the miss distance of missile is less than 1m and the impact angle is closing to -90°,it meets the requirements of the guidance precision and the terminal impact angle constraint.

关 键 词：落角约束 一体化 反演 自适应滑模控制 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]