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- W2079658517 abstract "The problem is addressed of transferring a spacecraft from a low Earth to a low lunar orbit in a planar circular restricted three-body framework. A closed-form approximate expression for the total velocity variation is developed under the assumption of minimum ∆V biimpulsive maneuvers. This approximation quantifies the link between the transfer orbit energy and the minimum ∆V needed to complete the maneuver, but it gives no information on the corresponding mission time. This last problem is addressed in a systematic framework using an optimization process, and the total ∆V is minimized with the constraint that a maximum transfer time is not exceeded. Using a set of mission data taken from the literature, it is found that almost equivalent ∆V and transfer times (compared to a weak stability boundary approach) are obtained without the use of solar perturbations. More important, a consistent methodology is proposed to exploit fully the fundamental tradeoff between the time of flight and the required ∆V." @default.
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- W2079658517 date "2005-03-01" @default.
- W2079658517 modified "2023-09-24" @default.
- W2079658517 title "Optimization of Biimpulsive Trajectories in the Earth-Moon Restricted Three-Body System" @default.
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- W2079658517 doi "https://doi.org/10.2514/1.7702" @default.
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