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首页> 外文期刊>The Journal of the Astronautical Sciences >Spacecraft Formation Design and Control in Keplerian Elliptic Orbits
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Spacecraft Formation Design and Control in Keplerian Elliptic Orbits

机译：开普勒椭圆轨道上的航天器编队设计与控制

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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.
机译：本文研究了在椭圆轨道上运动的主要航天器与副航天器之间的编队飞行。首先，通过使用描述主要航天器和副航天器之间的相对运动的Tschauner-Hempel方程的状态转移矩阵（STM），获得了抑制相对距离变化的两个编队轨迹。这些轨迹是沿轨道形成和一般圆形轨道的延伸，其中主要航天器沿圆形轨道运动。在初始条件下考虑了J_2扰动对轨迹的影响。此外，得出了最小化副控制力的L_2范数的地层重构方案。还推导了通过使用有限数量的脉冲来实现重构轨迹的控制定律。最后，示出了构造轨迹的构造的数值示例。

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