摘要
研究近地轨道卫星编队构形在引力摄动作用下的长期演化机理。把用转移矩阵法得出的相对运动分析解表达成一般轨道根数形式,为研究摄动影响而进一步表达成无奇点轨道根数形式;根据各轨道根数的J2摄动解分别研究编队构形在轨道坐标系三个方向上的振幅与相位的长期变化情况,揭示了构形引力摄动的长期演化机理;给出编队构形的摄动表达式,并以仿真实例验证其可信性;最后给出构形长期引力摄动的相关结论,并对编队构形设计提出建议,这将为研究编队构形的规划技术带来方便。
The mechanism of Low earth orbit （LEO） satellite formation secular evolvement under the influence of gravitational perturbations is studied. The analytic solution of relative motion got from state-transition-matrix method is expressed with orbit elements. In order to explore the effect of J, perturbation, the non-singular orbit elements are imported. Based on the perturbing solutions of non-singular orbit elements, the secular motions of the amplitudes and the phases of satellite formation in the three axes of LVLH frame are discussed respectively, which discover the mechanism of formation secular evolvements. Then, the secular motion expressions of formation are presented and a simulation proves the creditability. At last, some conclusions of formation secular evolvements and some advises about formation design are provided, which can be of some help to the study of formation planning.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2007年第2期253-258,共6页
Journal of Astronautics
基金
国防预研基金项目资助(51421050203KG01)
关键词
近地轨道
卫星编队飞行
长期运动
J2摄动
构形规划
Low earth orbit
Satellite formation flying
Secular evolvement
J2 perturbation
Formation planning
