摘要
针对实际导弹过载受限问题,基于到达条件,分析和确定了三维变结构制导律中滑动模态的稳定域。根据末端三维弹目相对运动学关系,建立了三维制导系统的数学模型,并以纵向平面模型和变结构控制中到达条件为基础,引入分段光滑连续函数,以三维平面间的耦合关系为出发点,从两个方面分析并确定了过载受限变结构制导律的滑动模态吸引区,证明其制导系统的稳定性。最后,针对零化视线角速率而设计的变结构制导律,确定了它的滑动模态吸引区,验证了理论分析方法的有效性。
The stability region of sliding mode in variable structure guidance design method is analyzed and determined based on reaching conditions, considering the restrained overload problem of missile control. The guidance system is built according to the relative relationship in three dimensions. For longitudinal plane, by introducing the subsidiary smooth function, the attraction domain of sliding mode are analyzed and determined, and the stability of the guidance system is proven, considering from the coupling relations of two planes in three dimensions. Finally the attraction domain of a kind of variable structure guidance, which is designed by zeroing sight angle rate, is shown that the valid of the analysis method is verified.
出处
《飞行力学》
CSCD
北大核心
2009年第3期58-61,共4页
Flight Dynamics
基金
国家973计划资助项目(2007DC020001)
关键词
过载受限
到达条件
滑动模态吸引区
restrained overload
reaching conditions
attraction domain of sliding mode
