椭圆轨道星座构型自稳定设计研究  

Study on Self-Stabilization Design of Configuration for Elliptical Orbit Satellite Constellation

作　　者：项军华[1] 张育林[2] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073 [2]清华大学宇航技术研究中心,北京100084

出　　处：《飞行力学》2008年第3期93-96,共4页Flight Dynamics

基　　金：国防预先研究基金资助项目(413200101)

摘　　要：椭圆轨道星座构型稳定性要求同时实现升交点赤经、近地点幅角和平近点角的稳定。通过初始偏差对椭圆轨道卫星的长期影响分析可知,轨道半长轴、倾角和偏心率的初始偏差对升交点赤经、近地点幅角和平近点角的长期摄动变化是线性的,因此通过主动偏置轨道半长轴、偏心率和倾角能够实现椭圆轨道星座构型的自稳定设计,从而提高其构型稳定性。对实例星座的设计结果表明,自稳定设计方法对提高椭圆轨道星座的构型稳定性是有效的。The configuration stability of the elliptical orbit satellite constellation requires the stabilization of the ascending node right ascension, the argument of perigee and the mean anomaly at the same time. Because of the secular perturbation variations of the ascending node right ascension, the argument of perigee and the mean angle caused by the initial deviations of the semi-major axis, the inclination and the eccentricity are linear time-variant, then the active biases of the semi-major axis, the inclination and the eccentricity can realize the self-stabilization design of the elliptical orbit satellite constellation, and so the configuration stability will be improved. The design results of the example constellation show that the self-stabilization design is effective to enhance the configuration stability of the elliptical orbit satellite constellation.

关 键 词：椭圆轨道 卫星星座 构型稳定性 自稳定设计 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]