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Interplanetary Mission Designs by Multiple Earth-Venus-Jupiter Swingbys
https://jaxa.repo.nii.ac.jp/records/31173
https://jaxa.repo.nii.ac.jp/records/3117340e507cd-9ec2-4c26-a1bc-b0e24fd15fab
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
SA0033406.pdf (796.0 kB)
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| Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||||||
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| 公開日 | 2015-03-26 | |||||||||
| タイトル | ||||||||||
| タイトル | Interplanetary Mission Designs by Multiple Earth-Venus-Jupiter Swingbys | |||||||||
| 言語 | en | |||||||||
| 言語 | ||||||||||
| 言語 | eng | |||||||||
| 資源タイプ | ||||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||||||
| 資源タイプ | departmental bulletin paper | |||||||||
| 著者 |
YOKOTA, Hiroki
× YOKOTA, Hiroki
× TANABE, Toru
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| 著者所属（英） | ||||||||||
| en | ||||||||||
| Department of Aeronautics, University of Tokyo | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| Department of Aeronautics, University of Tokyo | ||||||||||
| 出版者 | ||||||||||
| 出版者 | 宇宙科学研究所 | |||||||||
| 出版者（英） | ||||||||||
| 出版者 | Institute of Space and Astronautical Science | |||||||||
| 書誌情報 |
en : The Institute of Space and Astronautical Science report. S.P. : Proceedings of the Symposium on Mechanics for Space Flight 巻 1, p. 73-85, 発行日 1983-03 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | This paper presents a possible usage of a multiple swingby technique which makes use of at most three gravity-assist planets (Earth, Venus, and Jupiter). Various combinations are considered (e.g., a multiple Venus swingby, a multiple Earth-Venus swingby, etc.), and each of te energy exchange mechanisms between a spacecraft and planet (s) is investigated as well as the angular momentum exchange mechanisms. Focusing on attainable orbital elements, the capability of each swingby technique is also investigated. The major purpose of this technique is to reduce the launch velocity increment while maintaining a reasonable flight time. When only one planet is involved, a forward dynamic programming approach is successfully applied to determine the optimal swingby sequence. However, when more than two planets are used, computations become quite time consuming so that a simplified control strategy is proposed. This strategy is built up with several subsequences, in which a forward dynamic programming approach is partially applied. Four specific interplanetary mission designs (M1 through M4) are presented : M1 : escaping from the solar system; M2 : falling into the sun; M3 : out-of-the-ecliptic mission; and M4 : retrograde mission; by using a multiple Earth-Venus swingby and a multiple Earth-Venus-Jupiter swingby with as small as 3.0km/sec launch velocity increment. Results are compared with a conventional direct launch technique in terms of the Earth launch velocity increment, flight time, and available launch window. Computations are based on a patched conics method, and orbits of Earth, Venus, and Jupiter are assumed to be circular and coplanar unless otherwise specified. | |||||||||
| ISSN | ||||||||||
| 収録物識別子タイプ | ISSN | |||||||||
| 収録物識別子 | 0288-433X | |||||||||
| 書誌レコードID | ||||||||||
| 収録物識別子タイプ | NCID | |||||||||
| 収録物識別子 | AA10455137 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: SA0033406000 | |||||||||
