带多约束条件的次最优中制导律设计  

The Design of Suboptimal Midcourse Guidance Law with Multi-Constraints

作　　者：窦磊[1] 窦骄[2] 

机构地区：[1]南京理工大学弹道国防科技重点实验室,南京210094 [2]中国空间技术研究院,北京100094

出　　处：《宇航学报》2011年第12期2505-2509,共5页Journal of Astronautics

基　　金：国家自然科学基金(60904085);教育部博士点新教师基金(200802881012);南京理工大学卓越计划"紫金之星"基金;弹道国防科技重点实验室基金

摘　　要：针对使用捷联式导引头的制导弹药,设计了次最优中制导律,以满足卫星制导与激光制导两种模式的交接要求。由于涉及到时变系统的解析求解,一般情况下,带多约束条件最优制导律的设计非常困难。利用以下的方法来解决这一问题:首先根据最优控制理论确定次最优中制导律的结构框架,然后根据该框架反向推导出变参数的合理常数替代值。利用设计的次最优中制导律,在交接段,导引头量测视线偏差角远小于视场角,并考虑了控制能量和落地时脱靶量等方面的约束要求,具有非常简单的形式,仅较比例导引律多出一项,减少了制导指令计算对弹载计算资源的占用。For guided munitions with strapdown seeker, a suboptimal midcourse guidance law is designed to meet the hand-over requirements from satellite-guided mode to laser-guided mode. In general, the time-varying differential equations can not be analytically solved. Therefore, the design of optimal guidance law with multi-constraints is very difficuh for time- varying systems. A new method is presented for the problem. First, the framework of suboptimal midcourse guidance law is determined based on optimal control theory; then, according to the framework, the constant replacement values are derived for time-varying parameters. Using the proposed guidance law, the measured line-of-sight （LOS） deviation angle of seeker is much smaller than the field-of-view angle in the hand-over section, and it considers the constraints of the control energy consumption and the miss distance at landing time. Compared with proportional guidance law, the proposed guidance law has only one term more. Little onboard computational resources are required for the simple form.

关 键 词：中制导律 次最优 多约束 交接 视线偏差角 

分 类 号：TJ413.6[兵器科学与技术—火炮、自动武器与弹药工程]