摘要
研究导弹的制导优化性能,中远程导弹中末交接班时导弹飞行速度,是影响脱靶量的重要因素。为使导弹在中末交接班点的速度达到最大,同时使导弹的弹道倾角满足约束条件,提出采用一种使末速最大的最优中制导律。制导律是法向加速度指令,控制增益是一个关于速度、位置等飞行状态以及弹道约束条件的函数,并且变化范围很小。为便于工程应用,控制增益取为固定值。进行仿真的结果显示,导弹在中末交接班时速度达到最大,同时弹道倾角也能够满足弹道约束条件,提出的最优中制导律达到了设计要求,可为设计应用提供依据。
Performance optimization for missile guidance is researched.For the long-rang missiles,the speed is an important factor that affects the missile missing distance at the handover point.An explicit acceleration command is derived analytically in which the trajectory-dependent optimal control gains are written in terms of speed,location,and intercept boundary condition.To implement engineering project easily,fixed control gains are taken,which can also meet the requirments and need only a few guidance information.It is shown that the final speed is maximized and the expected flight path angle is met at the handover point,which means the optimal midcourse guidance law is well designed.
出处
《计算机仿真》
CSCD
北大核心
2011年第7期71-74,共4页
Computer Simulation
关键词
最优中制导
控制增益
脱靶量
Optimal midcourse guidance
Optimal control gain
Miss distance
