弹道导弹关机点偏导数计算/校验的新算法  

New Algorithm for Partial Derivative Computation/Validation of Shutdown Point of Ballistic Missile

作　　者：苗育红[1] 周江华[1] 

机构地区：[1]第二炮兵工程学院,西安710025

出　　处：《航天控制》2005年第3期51-54,59,共5页Aerospace Control

基　　金：国家自然科学基金(70171029);第二炮兵工程学院创新人才工程项目资助

摘　　要：对摄动制导的弹道导弹而言,关机点偏导数和全导数计算及其校验是导弹诸元计算中的重要环节。本文利用相对系运动参数和绝对系运动参数之间的关系,推导了弹道导弹关机点偏导数计算的三组新的计算公式,这些公式均建立在严格证明的基础上,它们构成了完整的、高精度偏导数计算/校验算法。和定型的算法相比,文中的算法具有数学描述简洁,计算方便,校验可靠、精度高的优点。可满足弹道式导弹精确诸元解算/校验的要求。For the ballistic missile using perturbation guidance, the computation of partial derivative at shutdown point is very important for data calculation and validation. Three sets of formulae for computing partial derivative at shutdown point of ballistic missile are presented in this paper, which is based on the relationship between the movement parameters of relative coordinate system and that of absolute coordinate system. Through strictly proving, those formulae construct a complete and high-precision algorithm for shutdown point partial derivative computation and validation. Compared with the algorithm currently used, the algorithm presented in this paper has the advantage of simple mathematic description, easy computation, reliable validation and high precision. It can satisfy the requirements of precise data computation and validation of ballistic missile.

关 键 词：弹道导弹 诸元计算 射程 横向偏差 

分 类 号：TJ763.3[兵器科学与技术—武器系统与运用工程]