摘要
根据LL-SST重力场测量改进对编队构型设计的要求,基于平均轨道根数描述的编队运动学方程,对自然轨道的编队构型进行了地球扁率二阶摄动下的修正,设计了在J2长期项和J3长周期项影响下相对稳定的类空间圆编队构型,并得到卫星的初始轨道根数.仿真表明,30天的仿真时间内,设计所得构型满足重力场测量下编队的约束,且在J2长期项和J3长周期项摄动影响下,与考虑J2半长轴修正设计的空间圆构型相比,在径向和迹向上的漂移量分别减少了99.980%,99.976%,法向振幅发散减少了99.710%.
The tremendous advances made by GRACE have led to an interest in launching a follow-up mission with better performance.To improve the ranging performance,a new formation is developed for gravity measurement from low-low satellite to satellite tracking.Firstly,orbit element is used to describe the relative motion between two satellites and give a formation parameter.Then, in order to keep formation stable under Earth oblateness,a formation design method is given which has taken into account of J2 and J3 perturbation.The initial orbit element is computed for the two satellites.At last,a numerical simulation is proposed.The result indicates that the formation meets the demand of improvement for gravity measurement,which can be more stable than the formation designed by reckoning on only J2 perturbation,and there are 99.980%,99.976%,99.710% less excursion in three directions.
出处
《空间科学学报》
CAS
CSCD
北大核心
2010年第6期547-553,共7页
Chinese Journal of Space Science
