空间控制技术与应用2024，Vol.50Issue(4)：75-86,12.DOI:10.3969/j.issn.1674-1579.2024.04.009
HEO轨道卫星相对运动建模与编队构形设计
Relative Motion Equation and Formation Flying Between HEO Satellites
刘笑 1梁巨平 1张宏兴 2王禹 1周泽亚 1尹俊雄1
作者信息
- 1. 上海航天控制技术研究所,上海 201109||上海空间智能控制技术重点实验室,上海 201109
- 折叠
摘要
Abstract
With the maturation and application of global satellite constellation flying technology,solving relative motion through the fundamental equations of satellite motion and designing various formation configurations have be-come a development trend.This paper establishes a relative motion model based on deviations in relative orbital el-ements,first theoretically derives the relative motion equations suitable for high eccentricity elliptical orbits under second-order approximation conditions,and further analyzes the accuracy of the second-order terms.Additionally,under the two-body assumption,the true anomaly difference at perigee is used instead of the mean anomaly differ-ence as the input for formation configuration design.Various typical formation configurations are designed and ana-lyzed under different initial orbital element difference conditions.Finally,simulations are conducted to verify the correctness of the formation configuration design and analyze its applicability from the two-body assumption to sce-narios involving perturbations,the results show that the formation configuration design and the relative motion equa-tions suitable for high eccentricity elliptical orbits are correct and effective.关键词
椭圆轨道/真近点角差/二阶相对运动误差/编队构型设计Key words
elliptical orbits/the true anomaly difference/second-order relative error/formation configuration de-sign分类
航空航天引用本文复制引用
刘笑,梁巨平,张宏兴,王禹,周泽亚,尹俊雄..HEO轨道卫星相对运动建模与编队构形设计[J].空间控制技术与应用,2024,50(4):75-86,12.
