Optimal spacecraft swarm reconfiguration through chief orbit refinement
Optimal spacecraft swarm reconfiguration through chief orbit refinement
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DOI：
10.1016/j.actaastro.2021.03.011
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发表时间：
2021-03-30
影响因子：
3.5
通讯作者：
D'Amico, Simone
中科院分区：
文献类型：
--
作者：
Lippe, Corinne;D'Amico, Simone
这项工作提出了一种新颖的方法，可以通过细化真实或虚拟的首席航天器轨道来最大程度地减少飞船群重新配置的Delta-V，这是一个任意偏心率的封闭轨道。给定所需的相对运动配置，群体的最佳目标终端是为提供最小的Delta-V支出。相对运动的相对轨道元素（ROE）表示，以产生两个四二次约束线性程序（QCLP）。一个程序可以最大程度地减少整个群体中的Delta-V使用总和，而第二个程序则最大程度地减少了群或共绕线飞船之间的最大delta-V使用。这两个目标旨在平衡整个群体中的增量使用量，以最大程度地提高任务寿命。此外，可以使用内部点方法有效地解决这两个优化程序。虽然最小化适用于任何ROE集合，但在本工作中利用了准非词性ROE，以生成用于非供位轨道中任意群体几何重构的分析解决方案。如果没有分析解决方案，则提供指导，以最大程度地减少凸优化求解器在查找解决方案中所需的努力。使用最先进的求解器证明了通过群体参考轨道的细化来启用的Delta-V节省，该求解器可为给定的重新配置生成最小可触及的Delta-V。因此，利用QCLP的参考轨道上的小改进来重新配置可以提供大量的Delta-V节省，从而延长任务寿命。
This work presents a novel approach to minimizing delta-v for spacecraft swarm reconfiguration through refinement of the real or virtual chief spacecraft orbit, which is a closed orbit of arbitrary eccentricity. Given a desired relative motion configuration, the optimal target end-state of the swarm is solved for to provide minimum delta-v expenditure. The relative orbital elements (ROE) representation of relative motion is leveraged to produce two quadratically constrained linear programs (QCLPs). One program minimizes the sum of delta-v usage across the swarm, and the second minimizes the maximum delta-v usage among the swarm or co-orbiting spacecraft. The two objectives are designed to balance delta-v usage across the swarm to maximize mission lifetime. Furthermore, both optimization programs can be solved efficiently with interior point methods. While the minimization is applicable to any ROE set, the quasi-nonsingular ROE are exploited in this work to produce analytical solutions for arbitrary swarm geometry reconfigurations in non-equatorial orbits. If analytical solutions are not available, guidance is provided to minimize the effort required by convex optimization solvers in finding solutions. The delta-v savings enabled by the refinement of the swarm's reference orbit are demonstrated using a state-of-the-art solver that produces the minimum reachable delta-v for a given reconfiguration. Therefore, leveraging a small refinement in the reference orbit for swarm reconfiguration through a QCLP can provide significant delta-v savings, extending mission lifetime.