科研之友
微信
新浪微博
Facebook
分享链接
摘要
In this paper, formation flying between a chief spacecraft moving in an elliptic orbit and a deputy spacecraft is studied. First, by using a state transition matrix (STM) of the Tschauner-Hempel equations, which describe the relative motion between the chief and deputy spacecraft, two formation trajectories that suppress relative distance variations are obtained. These trajectories are extensions of an along-track formation and a general circular orbit wherein the chief spacecraft moves in a circular orbit. The effects of the J(2) perturbation on the trajectories are considered in the initial conditions. Further, the solution of the formation reconfiguration that minimizes the L-2-norm of the deputy control forces is derived. A control law that realizes the reconfiguration trajectory by using a finite number of impulses is also derived. Finally, numerical examples of the construction of the formation trajectories are shown.
- 出版日期2011-6
