Orbital Design for Multiple Flyby Missions

Mai Bando, Hiroshi Yamakawa

Research output: Contribution to journalArticlepeer-review

Abstract

This paper presents a procedure to design multiple flyby missions. When the missions to observe space debris or near Earth asteroids (NEAs) are considered, it is more efficient to achieve many observations by a single spacecraft during the flight. Using the generating functions of canonical system, two-point boundary-value problem can be solved by function evaluations. Using this property, a strategy to optimize the multiple flyby sequence is proposed. This enables us to choose an optimal sequence among a long list of targets in which minimum fuel consumption is achieved. This paper focuses on the selection of sequence with pre-fixed interval time. The illustrated example using Hill two-body problem is shown.
Original languageEnglish
Pages (from-to)Pd_9-Pd_13
JournalTRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN
Volume8
Issue number27
DOIs
Publication statusPublished - 2010

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