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Trajectory Optimization for Missions to Small Bodies with a Focus on Scientific Merit
Computing in Science & Engineering ( IF 2.1 ) Pub Date : 2017-01-01 , DOI: 10.1109/mcse.2017.3151246
Jacob A Englander 1 , Matthew A Vavrina 2 , Lucy F Lim 1 , Lucy A McFadden 1 , Alyssa R Rhoden 3 , Keith S Noll 1
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Trajectory design for missions to small bodies is tightly coupled both with the selection of targets for the mission and with the choice of spacecraft power, propulsion, and other hardware. Traditional methods of trajectory optimization have focused on finding the optimal trajectory for an a priori selection of destinations and spacecraft parameters. Recent research has expanded the field to multidisciplinary systems optimization that includes spacecraft parameters. The logical next step is to extend the optimization process to include target selection based not only on engineering figures of merit but also scientific value. This article presents a new technique to solve the multidisciplinary mission optimization problem for small-body missions, including classical trajectory design, the choice of spacecraft power and propulsion systems, and the scientific value of the targets. This technique, when combined with modern parallel computers, enables a holistic view of the small-body mission design process that previously required iteration among several different design processes.

中文翻译:

以科学价值为重点的小型天体任务的轨迹优化

小型天体任务的轨迹设计与任务目标的选择以及航天器动力、推进和其他硬件的选择紧密相关。传统的轨迹优化方法侧重于为目的地和航天器参数的先验选择寻找最佳轨迹。最近的研究已将该领域扩展到包括航天器参数在内的多学科系统优化。合乎逻辑的下一步是扩展优化过程,以包括不仅基于工程性能指标而且基于科学价值的目标选择。本文提出了一种解决小天体任务多学科任务优化问题的新技术,包括经典轨迹设计、航天器动力和推进系统的选择、以及目标的科学价值。这种技术与现代并行计算机相结合,可以全面了解小体任务设计过程,而该过程以前需要在几个不同的设计过程中进行迭代。
更新日期:2017-01-01
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