航天器入轨状态与偏差传播分析
Analysis of orbital injection state and deviation propagation of spacecraft
彭祺擘 1刘将辉 2张海联 3周建平3
作者信息
- 1. 中国航天员科研训练中心,北京 100094
- 2. 中国航天员科研训练中心,北京 100094;中国载人航天工程办公室,北京 100071;北京航空航天大学宇航学院,北京 100083
- 3. 中国载人航天工程办公室,北京 100071
- 折叠
摘要
本文研究了航天器入轨状态和入轨偏差传播问题.推导了火箭熄火时的入轨速度平方比率及速度仰角与主要轨道参数之间的关系,从而分析航天器的入轨状态.建立了航天器转移轨道的偏差传播矩阵,得到入轨偏差对转移轨道的影响.将本文的偏差传播分析方法与传统轨道误差分析方法进行对比以验证本文方法的正确性.最后,通过仿真算例分析了航天器入轨状态和入轨偏差对转移轨道的影响.
Abstract
The problem of orbital injection state and deviation propagation of spacecraft is studied in this paper.This relationship between the velocity square ratio of orbital injection and the velocity elevation angle and the main orbital parameters when the rocket extinguishes is derived to analyze the orbital injection state of the spacecraft.The deviation propagation matrix of the spacecraft's transfer orbit is established,and the influence of the orbit inject deviation on the transfer orbit is obtained.The deviation propagation analysis method in this paper is compared with the traditional orbital error analysis method to verify the correctness of the proposed method.Finally,the influence of spacecraft's orbital injection state and orbit inject deviation on the transfer orbit is analyzed through simulation example.
关键词
轨道参数/入轨状态/入轨偏差/偏差传播矩阵Key words
orbital parameters/orbital injection state/orbit inject deviation/deviation propagation matrix引用本文复制引用
基金项目
载人航天工程科技创新团队()
中国博士后科学基金(2023M734249)
出版年
2024
NETL
NSTL
万方数据