基于空间流形动力学的行星际任务设计与制导

U. Rajeev
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引用次数: 0

摘要

利用受限三体问题的流形结构对行星际旅行任务设计和制导进行了研究。行星际飞行器同时受到多个天体引力的影响。耦合多体动力学的经典求解方法是将其近似为一系列两体问题。基于近年来对多体动力学在空间任务设计中的应用的兴趣,研究了地月系统从L1李雅普诺夫轨道到L2李雅普诺夫轨道转移的任务段。具有流形结构的任务设计不一定总是产生连续的轨迹。此外,任务的初始条件可能不在歧管上。提出了一种基于反馈线性化的闭环制导方案,以保证航天器在不考虑初始偏差和轨迹不连续的情况下对流形结构进行跟踪。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Interplanetary Mission Design and Guidance Based on Space Manifold Dynamics
Mission design and guidance for interplanetary travel utilizing the manifold structure of restricted three-body problem is investigated. Interplanetary space vehicle is simultaneously influenced by the gravitational attraction of multiple celestial bodies. Coupled, multi-body dynamics is classically solved by approximating it as a sequence of two-body problems. Based on the recent interest in the application of multi-body dynamics in the space mission design, a mission segment for transfer from an L1 Lyapunov orbit to L2 Lyapunov orbit is studied for the Earth-Moon system. Mission designs with manifold structure may not always yield continuous trajectories. Moreover, initial condition of the mission may not lie on the manifold. A closed loop guidance scheme based on feedback linearization is developed to ensure that the spacecraft tracks the manifold structure irrespective of the initial deviations and trajectory discontinuities.
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