制导控制一体化有限时间收敛控制算法  

A Study of Finite Time Convergent Control Algorithm on Integrated Missile Guidance and Control

作　　者：张旭[1] 雷虎民[1] 董飞垚 邵雷[1] 翟岱亮[1] 

机构地区：[1]空军工程大学防空反导学院 [2]93995部队

出　　处：《空军工程大学学报（自然科学版）》2015年第5期5-10,共6页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：国家自然科学基金资助项目(61573374;61503408);航空科学基金资助项目(20140196004;20130196004)

摘　　要：针对拦截高速机动目标的需求,研究了一种完全制导控制一体化有限时间收敛控制算法。首先,根据传统完全制导控制一体化模型,推导了导弹完全制导控制一体化视线角速率有限时间收敛模型;其次,构造了带补偿函数的非线性滑模切换函数,根据有限时间收敛终端滑模控制理论,设计了基于完全制导控制一体化的有限时间收敛控制算法,并通过自适应方法对系统不确定性的最大值进行了估计、运用高阶滑模微分器对视线角速率和弹目相对距离的高阶导数进行了解算;最后,仿真结果表明,与一般的控制算法相比,论文所设计的有限时间收敛控制算法能够达到视线角速率有限时间收敛,且具有更小的脱靶量和更短的飞行时间。A finite time convergent control algorithm on integrated missile guidance and control is proposed to meet the needs of intercepting maneuvering targets at high speed. Firstly, a finite-time convergent line- of-sight rate model is derived based on total integrated missile guidance and control according to the tradi- tional total integrated missile guidance and control model. Secondly, a nonlinear sliding mode switching function with compensating factor is construct, and a finite time convergent control algorithm of integrated missile guidance and control is designed based on finite-time convergent theory. Besides, an adaptive meth- od is adopted to estimate the maximum value of the system＇s uncertainty, and the higher-order sliding mode differentiators are adopted to solve the higher-order derivatives of line-of-sight rate and the distance between the missile and the target. Finally, the simulation results show that the proposed finite time con- vergent control algorithm can achieve the finite time convergence of the line-of-sight rate, and has less miss distance and shorter intercepting time, compared to the general control algorithms.

关 键 词：导弹完全制导控制一体化 视线角速率 有限时间收敛 控制算法 

分 类 号：V448[航空宇航科学与技术—飞行器设计] TJ765.3[兵器科学与技术—武器系统与运用工程]