基于预测控制的角度约束制导律设计  

Guidance with impact angle constraint based on predictive control

作　　者：水尊师[1] 周军[1] 葛致磊[1] 郭建国[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,陕西西安710072

出　　处：《飞行力学》2011年第3期56-59,共4页Flight Dynamics

摘　　要：针对低高度、大倾角末端姿态约束问题,提出了一种弹道跟踪制导律。离线优化得到满足终端约束的基准弹道。为了避免出现奇异,将对位置的跟踪转换为对视线角及视线角速度的跟踪。根据当前状态,利用连续时间非线性预测控制,以弹道跟踪误差和控制能量的组合为性能指标,在线滚动优化得到制导指令,分析了制导律的参数选取,最后对该制导律进行了全弹道数学仿真。与文献[2-3]中的导引律相比的结果表明,该制导律能实现干扰作用下对参考轨迹的精确跟踪,命中点姿态角控制精度高、脱靶量小,具有一定的鲁棒性。A guidance law with angle constraint was developed for an air-to-ground missile, which met the requirements of the low height and large impact angle. The reference trajectory was generated by the off-line optimizing. A continue predictive control law was designed to track the reference trajectory, it predicted trajectory by appropriate expansions, the optimal slide control was obtained through minimizing the predicted errors in the actual response, the desired response and current control expenditure. The trajectory mathematical simulation under all kinds of disturbing has been implemented. Simulation results show proposed guidance law can track reference trajectory precisely and the requirement of both precision and angle constraint is also met.

关 键 词：预测控制 角度约束 末制导 基准弹道 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]