Optimum Low-Thrust Multiple Rendezvous

概要

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The problem of multiple rendezvous with low-thrust propulsion systems is discussed. The motivation of this problem is given by the necessity of the space sweep mission in future which will aim to revover or deorbit several mission completed orbiting bodies in succession. Optimization parameter is the fuel consumption required to complete a multiple rendezvous in a given mission time. Optimum targeting sequence and time allocation to each rendezvous are determined by a simple method developed on the basis of a linear theory. Solutions are obtainable not only for the case of variable thrust mode but for the case of constant thrust mode of low-thrust propulsion systems. Some numerical examples for the verification of the developed methods are presented and the feasibility of low-thrust propelled space sweeper is discussed.
宇宙航空研究開発機構の論文