基于需要轨道的导弹最优迭代制导方法  

Optimal Iterative Guidance Method Based on Required Trajectory

作　　者：肖龙旭[1] 王继平[1,2] 王安民[1] 焦洋[3] 

机构地区：[1]第二炮兵装备研究院 [2]中国人民解放军96271部队 [3]第二炮兵工程学院

出　　处：《上海航天》2012年第3期1-5,共5页Aerospace Shanghai

摘　　要：提出了一种基于需要轨道的导弹最优迭代制导方法,以标准弹道上某点建立需要轨道并确定入轨点参数,通过弹上迭代制导实现最优入轨控制,给出了计算模型。该制导方法无需修正地球扁率和再入阻力的影响,可减小方法误差。仿真计算结果证明方法正确。One kind of optimal iterative guidance method based on required trajectory for missile was put forward in this paper. Some point in standard trajectory was adopted to establish the required trajectory and determine the parameters of the trajectory entering point. The optimal injection control was realized by the iterative explicit guidance when the missile was flying. The modelwas given out. The earth earth oblateness and reentry aerodynamic resistance influence were not be modified by using this method, which colud reduce the error. The method was proved by the simulation result.

关 键 词：需要轨道 入轨点 迭代制导 方法误差 

分 类 号：TJ765.1[兵器科学与技术—武器系统与运用工程]