宇宙機フォーメーションの2インパルスによる相対位置の変更 : 第3報,主宇宙機の軌道が離心率を持つ場合(機械力学,計測,自動制御)

概要

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This paper proposes a basic method for constructing a formation flight based on a transition matrix of orbital element differences. It proposes a trajectory design of minimum fuel consumption for spacecraft relative position change by two impulses. We consider here a problem to obtain the phase of the second impulse when the phase of the first impulse is given. As is different from the case of a circular orbit of a chief satellite, the mathematical model of the relative motion becomes more complicated, while the transition time is determined by the phases when the first and second impulses are given. Moreover there is no difference between the case when formation size is enlarged and the case when formation size is reduced. Analytical solutions are derived for the first and second impulses, and based on the solutions, the optimal impulses to minimize the fuel consumption are considered. And the results show that the optimality condition in this report covers the large part of the optimal cases in the simulation studies.
2009-02-25