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OPTIMAL LIBRATION POINT ORBITAL MANEUVERS

机译：最佳解放点轨道机动

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摘要

This paper studies the control of a single spacecraft as well as a formation of three spacecraft in the vicinity of the sun-Earth libration points. In particular, the design of a controlled halo orbit at the L_1 and L_4 points is considered. These types of orbits have many important and useful applications, as has been demonstrated recently by the Genesis mission, which employed a halo orbit at the L_1 point in the sun-Earth system. Minimum fuel trajectories are determined by solving a nonlinear programming problem which parameterizes the continuous problem into a discrete parameter optimization problem. Periodic orbits are determined within a common framework by constraining the initial position and velocity of the spacecraft to be equal to the final position and velocity (both of which are free), and allowing the period to be free. For certain initial guesses and constraints, globally optimal solutions (i.e., zero thrust/fuel) periodic orbits have been determined. Numerical solutions are obtained within the context of a restricted elliptic three-body problem. Furthermore, the design of repeating orbits for a three spacecraft formation is undertaken at L_1 and L_4. Finally, an orbit transfer of the formation between L_1 and L_4 is also demonstrated.
机译：本文研究了单个航天器的控制以及在太阳地球解放点附近的三个航天器的编队。特别地，考虑了在L_1和L_4点处的受控晕圈的设计。这些类型的轨道具有许多重要和有用的应用，正如最近发生的创世纪飞行任务所证明的那样，该任务在太阳地球系统的L_1点采用了晕圈轨道。通过解决非线性编程问题来确定最小燃料轨迹，该非线性编程问题将连续问题参数化为离散参数优化问题。通过将航天器的初始位置和速度限制为等于最终位置和速度（两者均是自由的）并允许周期是自由的，可以在一个公共框架内确定周期性轨道。对于某些初始猜测和约束，已经确定了全局最优解（即，零推力/燃料）周期轨道。在有限的椭圆三体问题的背景下获得了数值解。此外，在L_1和L_4进行了三个航天器编队的重复轨道设计。最后，还证明了L_1和L_4之间的编队轨道转移。

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  • 来源
    《Space technology》 |2006年第2期|p.1-11|共11页
  • 作者

    Paul Williams;

  • 作者单位

    RMIT University, School of Aerospace, Mechanical, and Manufacturing Engineering, PO Box 71, Bundoora VIC 3083, Australia;

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  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 航天（宇宙航行）;
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