Japan Aerospace Exploration Agency(JAXA)
Japan Aerospace Exploration Agency(JAXA)
Japan Aerospace Exploration Agency(JAXA)
Japan Aerospace Exploration Agency(JAXA)
Japan Aerospace Exploration Agency(JAXA)
出版者（英）
Elsevier
雑誌名
Acta Astronautica
巻
94
号
2
ページ
718 - 724
発行年
2014-02
抄録（英）
This paper describes a concept study of an optional kick stage system named “PLUS (for Planetary mission, Long-duration small-thrust Upper Stage)” equipped with a relatively small-thrust engine for interplanetary missions. The thrust force of PLUS assumed in this study is a maximum 29.4 kN, which is relatively small, used to inject a payload into interplanetary orbit with sufficiently low gravity loss i.e. less than 2%, although two split delta-Vs such as the Russian Proton/Breeze-M will improve performance efficiency (Proton Launch System Mission Planner's Guide, 2009 [1]). The orbital maneuvering capability of PLUS system is evaluated through Mars orbital maneuvering simulations. In this study, two types of PLUS systems are assumed. First, a 29.4 kN thrust force kicks stage system designated as “PLUS1” to inject the 3000 kg main payload into Mars transfer orbit. Second, a 9.8 kN thrust force small PLUS system designated as “PLUS2” to inject a 500 kg secondary payload into Mars transfer orbit. In the first case, the above-mentioned split delta-Vs are conducted to inject the main payload into Mars transfer orbit with sufficiently low gravity loss. In the second case, on the other hand, PLUS2 attached to the secondary payload is dual launched together with a primary payload into a geostationary transfer orbit, GTO, whereupon PLUS2 is initiated slightly before perigee to inject the secondary payload into Mars transfer orbit utilizing Electric delta-V Earth Gravity Assist, EDVEGA scheme via the on-board Ion Electric propulsion System, IES (Kawaguchi, 2001 2 and 3). Throughout the simulations, some optimized configurations of PLUS system covering a wide variety of space missions are suggested in this paper.
(C) 2014 Elsevier Ltd. NOTICE: This is the author's version of a work that was accepted for publication in Acta Astronautica. Changes resultingfrom the publishing process, such as peer review, editing,corrections, structural formatting, and other quality controlmechanisms, may not be reflected in this document. Changesmay have been made to this work since it was submitted forpublication. A definitive version was subsequently publishedin Acta Astronautica, VOLUME94, ISSUE2, 2014-02, DOI:10.1016/j.actaastro.2013.08.019
Study on the orbital maneuvering capability of H-2A kick stage
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