摘要
本文给出了人造地球卫星轨道计算的一种解析方法,定轨方案中摄动计算考虑了地球引力场非球形摄动的J2,J3,J4的长期项,长周期项,J2短周期项,大气阻力,太阳光压及日月引力摄动的长期项。初始根数改正量估计采用微分轨道改进算法。在定轨迭代收敛后,残差的均方根误差在5″左右,资料使用率超过80%。
An analytical method of the orbit improvement for artificial satellits is presented. In the perturbation calculation, the perturbations including long periodical terms of J2, J3 and J4 due to non - spherical gravity field on Earth , the short term of J2, the long term of atmospheric drag, the solar radiation pressure and lunisolar effects are considered. The arithmetic of differential orbit improvement is used in the corrections estimated of initial elements. After constringency, the root-mean square error is about 5＂ and more than 80% data are used.
出处
《天文研究与技术》
CSCD
北大核心
2007年第4期337-342,共6页
Astronomical Research & Technology
关键词
解析定轨
摄动计算
轨道改进
analytical orbit determination
perturbation calculation
orbit improvement
