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Optimization of an orbital long-duration rendezvous mission

机译：轨道长时间持续交会任务的优化

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The phasing segment of the rendezvous mission between a cargo spacecraft and a space station usually lasts for several weeks, and actually presents an orbital long-duration problem. In this study, this orbital long-duration problem is formulated as a mixed integer nonlinear programming (MINLP) problem in which the maneuver revolution numbers (integers), maneuver arguments of latitude and impulse magnitude are used as design variables at the same time. A hybrid approach is then proposed to solve this MINLP problem. First, a linear dynamics model considering the J(2) term of the Earth non-spherical gravity is employed to formulate an approximate phasing problem, which is optimized using a genetic algorithm. Second, a shooting iteration process considering the coupling effect between the in-plane and out-of-plane maneuvers is proposed to improve the approximate solution to satisfy the terminal conditions of the high-precision problem. The proposed approach is demonstrated for a typical two-week rendezvous phasing mission. The results show that the proposed approach can stably obtain the near optimal high-precision solution by integrating the perturbed trajectory only a few times. Furthermore, a long-duration rendezvous phasing plan is compatible with any initial phase angles that the in-plane velocity increment remains almost unchanged when the initial phase angle changes. However, under the same conditions, the out-of-plane velocity increment has considerable variations. Compared with a two-day rendezvous phasing plan, a two-week plan could have several successive coplanar launch opportunities for the chaser by aiming different terminal revolution numbers. (C) 2016 Elsevier Masson SAS. All rights reserved.
机译：货运飞船和空间站之间的交会任务的调相部分通常持续数周，实际上会带来轨道的持续时间长的问题。在这项研究中，该轨道长时间持续时间被表述为混合整数非线性规划（MINLP）问题，其中机动转数（整数），纬度机动参数和脉冲幅度同时用作设计变量。然后提出了一种混合方法来解决这个MINLP问题。首先，采用考虑地球非球面重力的J（2）项的线性动力学模型来制定近似相位问题，并使用遗传算法对其进行优化。其次，提出一种考虑面内和面外操纵耦合效应的射击迭代过程，以提高近似解的精度，以满足高精度问题的最终条件。所建议的方法已针对典型的两周交会调相任务进行了演示。结果表明，该方法仅需对轨迹进行几次积分即可稳定地获得接近最优的高精度解。此外，长时间的会合相计划与任何初始相位角都兼容，即当初始相位角改变时，平面内速度增量几乎保持不变。然而，在相同条件下，面外速度增量具有相当大的变化。与为期两天的相交阶段计划相比，为期两周的计划可以通过针对不同的终端旋转数来为追赶者提供多个连续的共面发射机会。 （C）2016 Elsevier Masson SAS。版权所有。

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