椭圆轨道星座构型自稳定设计研究

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。

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

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.