摘要
随着全球卫星组网编队飞行技术成熟应用,通过卫星之间基本运动方程进行相对运动求解,各种编队构型设计已经成为一种发展趋势.建立了基于相对轨道根数偏差的相对运动模型,理论推导了二阶近似条件下的适用于大偏心率椭圆轨道的相对运动方程,并进一步分析了二阶项的精度.在二体假设下,使用近地点真近点角差取代平近点角差作为编队构型设计输入,对多种不同初始轨道根数差条件下的典型编队构型进行了设计以及构型特征分析.对编队构型设计的正确性进行了仿真验证,并分析了从二体假设推广到含摄动情况的适用性,结果表明本文推导的椭圆轨道相对运动方程和编队构型设计正确有效.
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.
作者
刘笑
梁巨平
张宏兴
王禹
周泽亚
尹俊雄
LIU Xiao;LIANG Juping;ZHANG Hongxing;WANG Yu;ZHOU Zeya;YIN Junxiong(Shanghai Aerospace Control Technology Institute,Shanghai 201109,China;Shanghai Key Laboratory of Aerospace Intelligent Control Technology,Shanghai 201109,China)
出处
《空间控制技术与应用》
CSCD
北大核心
2024年第4期75-86,共12页
Aerospace Control and Application
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
elliptical orbits
the true anomaly difference
second-order relative error
formation configuration de-sign
