Maneuvering Spacecraft Formations Using a Dynamically Adapted Finite Element Methodology

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The formation reconfiguration or the deployment of multiple spacecraft is a key issue that demands a robust methodology safely avoiding collision hazards. In this paper we present a systematic procedure to perform proximity maneuvering that could also be applied to other general situations such as for loose confinements of spacecraft clusters inside a particular region. The problem is formulated and solved using a finite element approach with optimal control. Although the methodology is quite general and suits many different types of problems, the examples that have been considered focus on some basic orbital maneuvers for libration point mission concepts in the sun– Earth system.