任意大地高约束下的弹道飞行器自由段解析解

发布时间：2018-03-23 00:13

  本文选题：大地高约束　切入点：解析解　出处：《导弹与航天运载技术》2016年05期 　论文类型：期刊论文

【摘要】：在正交分解法的基础上,导出了弹下点大地纬度的迭代计算公式,进而将再入点或落点大地高引入到地心距的计算中,提出了一种弹道飞行器自由段的大地高约束解析解。数值仿真分析表明,该解析方法计算效率较高,位置偏差小于50 m,满足弹道计算、制导及轨道预测等应用需求。
[Abstract]:On the basis of orthogonal decomposition method, the iterative calculation formula of geodetic latitude at the point below the missile is derived, and then the geodetic height of the reentry point or the landing point is introduced into the calculation of the geocentric distance. An analytical solution of geodetic height constraint for free section of ballistic vehicle is presented. Numerical simulation results show that the analytical method is efficient and the position deviation is less than 50 m, which meets the requirements of trajectory calculation, guidance and orbit prediction.
【作者单位】： 北京宇航系统工程研究所;
【分类号】：V412;TJ760
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本文编号：1651032