摘要
大椭圆轨道航天器在较长轨道周期内运行于远地点上空,因而该轨道多应用于卫星通信、天体观测、空间磁场探测等。上述空间任务所需的多航天器协同运动理论亟待解决。利用运动学方法推导了大椭圆轨道编队的相对运动模型,简要证明了实现长期近距离编队的必要条件,分析了相对轨道根数对线性化模型精度及其动力学特性的影响。仿真结果表明,相对运动模型在轨道远地点处精度较高,适当选择相对轨道根数可设计出满足任务要求的编队轨道。
The spacecraft on highly elliptic orbits fly over their apogee in the most part of their cycles, so this kind of orbit is usually applied in the satellite communication, the observation of celestial bodies and the exploration of space magnetic fields. The kinematics of multi-spacecraft formation is required to deal with the above space missions. Formulations of the relative motion on highly elliptic orbits are presented by kinematic method. On the basis of them, the necessary condition is given to maintain the long-term and close formations. The influence of relative orbital elements on the precision of this linear simplified formulation is discussed and on the dynamic characteristics of relative trajectories. The simulation results show that the formulations are more precise at the orbit apogee. If the relative orbital elements were selected properly, the design formation orbit would satisfy the requirements of the aforementioned missions.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2005年第2期1-5,共5页
Journal of National University of Defense Technology
基金
国家863基金资助项目(2003AA769030)
关键词
大椭圆轨道
编队飞行
相对运动
运动学法
相对轨道根数
highly elliptic orbit
formation flying
relative mot ion
kinematic method
relative orbital elements
