机动发射下空间飞行器上升段弹道快速计算方法  

Fast calculation method of ascent trajectory for space vehicle under mobile launch condition

作　　者：任乐亮 鲜勇 郭玮林 张大巧 李冰 REN Leliang;XIAN Yong;GUO Weilin;ZHANG Daqiao;LI Bing(College of War Support,Rocket Force Engineering University,Xi'an 710025,China)

机构地区：[1]火箭军工程大学作战保障学院,陕西西安710025

出　　处：《飞行力学》2020年第3期57-62,共6页Flight Dynamics

摘　　要：机动发射条件下,为提高空间飞行器变射面横向机动模型的诸元计算速度,设计了基于牛顿迭代算法的诸元快速计算模型。以基准弹道诸元参数为迭代初值,选取了6个关键参数,在同一弹道模型基础上,采用牛顿迭代法对诸元进行快速求解。仿真结果表明,在一定范围内,迭代后的变射面横向机动弹道能够与飞行中段弹道高精度交班,且计算耗时不超过2 s,能够满足机动发射需求。In order to improve the calculation speed of the ballistic data of changeable-launching-plane transverse maneuvering model of the space vehicle in mobile launch condition,a fast calculation model of the ballistic data based on Newton’s method is designed.Based on the reference ballistic data as the initial value of the iteration,6 key parameters are selected,and the Newton’s method is used to solve the ballistic data on the basis of the same ballistic model.The simulation results show that,the high-precision shift with the mid-flight trajectory can be realized smoothly by iterated transverse maneuvering trajectory in a certain range,and the calculation takes no more than 2 s.Therefore,fast calculation model can meet the requirements of mobile launch.

关 键 词：机动发射 上升段弹道 变射面横向机动 诸元快速计算 牛顿迭代 

分 类 号：V412.1[航空宇航科学与技术—航空宇航推进理论与工程]