基于自适应幂次切换增益的动能拦截滑模制导律  

Adaptive Power Switching Gain based Sliding-Mode Guidance Law for Kinetic Energy Intercept

作　　者：李元凯[1] 敬忠良[1] 胡士强[1] 

机构地区：[1]上海交通大学空天科学技术研究院,上海200240

出　　处：《宇航学报》2008年第6期1792-1797,共6页Journal of Astronautics

基　　金：国家863项目(2006AA704314);国家自然科学基金项目(60775022);国家自然科学基金项目(60674107)

摘　　要：抖振问题限制了非线性变结构制导的应用。运用幂函数作为切换增益函数并设计全局鲁棒的滑模,构成自适应趋近律,实现切换线平滑趋近,形成基于自适应幂次切换增益的滑模制导律AP-SMG。给出其存在可达与稳定条件,并对空间目标的非机动和脉冲/连续机动环境作了仿真比较与参数分析。结果表明该制导律在动能拦截中可以有效削弱甚至消除视线角速率和控制律抖振,降低所需控制能量的同时能够保证制导精度,构造简单,无需智能结构辅助,总体性能优于基于常值切换增益的系列制导方法C-SMG。Chattering restricts the application of nonlinear variable structure guidance law. Through designed an adaptive trending law, consisted of a switching gain with power function and a global robust sliding mode, to smoothly approach switching surfaces, here provided a new sliding-mode method with adaptive power switching gain （AP-SMG）. Sliding mode existence, reachability and system stability were analyzed. SIMULINK simulation and parameter analysis were also made under exo-atmosphere intercept conditions with non-maneuvering and impulse/continuous maneuvering target. As a result, chattering of LOS velocity and control law can be effectively decreased even disappeared in kinetic energy intercept. Simultaneously, guidance precision is desired and control energy needed is declined. Without any assisted intelligent structure, the overall performances of APSMG are better than constant switching gain based guidance method （C-SMG）.

关 键 词：变结构 自适应 切换增益 制导律 动能拦截 

分 类 号：V448.133[航空宇航科学与技术—飞行器设计]