@inproceedings{oai:jaxa.repo.nii.ac.jp:00007572,
 author = {松本, 道弘 and 川口, 淳一郎 and Matsumoto, Michihiro and Kawaguchi, Junichiro},
 book = {第15回アストロダイナミクスシンポジウム講演後刷り集　2005, Proceedings of 15th Workshop on JAXA Astrodynamics and Flight Mechanics},
 month = {Mar},
 note = {今日の電気推進機関の技術進歩により、高比推力の推進機関が実用化されるようになり、さまざまな惑星探査が可能となった。そして今後も、火星や木星をはじめとする、深宇宙の惑星を探査する機会が増えていくと考えられている。宇宙航空研究開発機構・宇宙科学研究本部では、地球近傍ではなく地球引力圏界に、中継拠点として深宇宙港を建設しようという検討を行っている。本研究では、太陽-地球系L2点に深宇宙港を設置することを想定し、低推力推進機関を搭載した宇宙機によるL2点を発着地とした深宇宙往還システムを考え、その脱出軌道を論じる。, Recently, various kinds of planetary explorations have become more feasible, taking the advantage of low thrust propulsion means such as ion engines that have come into practical use. The field of space activity has now been expanded even to the rim of the outer solar system. In this context, the Japan Aerospace Exploration Agency (JAXA) has started investigating a Deep Space Port built at the L2 Lagrange point in the Sun-Earth system. For the purpose of making the deep space port practically useful, there is a need to establish a method to making spaceship depart and return from/to the port. This paper first discusses the escape maneuvers originating from the L2 point under the restricted three-body problem. Impulsive maneuvers from the L2 point are extensively studied here, and using the results, optimal low-thrust escape strategies are synthesized. The paper presents, as the major results, the optimal escape and acceleration maneuvers schemes using Electric Delta-V Earth Gravity Assist (EDVEGA) technique, in which the comprehensive delta-V evaluation method is presented. The results obtained are highly useful, ushering the future solar system exploration era., 資料番号: AA0063480007},
 pages = {35--40},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)},
 title = {Escape trajectory from the Sun-Earth L2 point},
 year = {2006}
}