带角度约束的倾斜转弯飞行器制导律设计

Terminal Guidance Law With Impact Angle Constraint for BTT Vehicle

针对倾斜转弯飞行器以给定角度攻击目标的要求,考虑控制回路动态特性对制导的影响,研究了带角度约束的制导律设计方法。以倾侧角和法向过载指令为控制量,建立了含控制回路动态特性的设计模型;基于该模型和多通道解耦的思想,提出带角度约束的滑模变结构制导律,通过调整趋近律参数消除抖振。理论分析表明:在初始阶段,该制导律较最优制导律对过载的需求小;通过优化制导律参数,当系统进入滑模面后,飞行器能按最优制导律命中目标。仿真表明,该制导律在满足落点和落角要求的同时,具有对过载需求分配合理、速度损失小的优点。

Aiming at the requirements of bank-to-turn（BTT）vehicle attacking target with desired angle,a sliding-mode variable-structure guidance law with impact angle constraint was proposed in view of the dynamic characteristics of the control loop.Choosing bank angle command and normal overload command as control variables,a model with control loop dynamic characteristics for designing guidance law was established.Based on the model,a sliding mode variable-structure guidance law with terminal angular constraint was designed.An adaptive reaching law was designed to alleviate chattering.Through theoretical analysis,this guidance law needs lower normal overload than optimal guidance law in the initial stage.In addition,when system reaches sliding mode surface,the vehicle can impact on the target with the same effect as optimal guidance law does.Simulation results show that the proposed guidance law not only ensures the vehicle impact the target accurately with desired angle,but also distributes normal overload requirement reasonably and requires less velocity loss.