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Trajectory design for rendezvous in lunar Distant Retrograde Orbit
https://jaxa.repo.nii.ac.jp/records/39544
https://jaxa.repo.nii.ac.jp/records/3954421d5b0cc-db70-40d8-80e1-1736d895ecd5
| Item type | 会議発表論文 / Conference Paper(1) | |||||||||
|---|---|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-07-14 | |||||||||
| タイトル | ||||||||||
| タイトル | Trajectory design for rendezvous in lunar Distant Retrograde Orbit | |||||||||
| 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_5794 | |||||||||
| 資源タイプ | conference paper | |||||||||
| アクセス権 | ||||||||||
| アクセス権 | metadata only access | |||||||||
| アクセス権URI | http://purl.org/coar/access_right/c_14cb | |||||||||
| 著者 |
Murakami, Naomi
× Murakami, Naomi
× Yamanaka, Koji
|
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| 著者所属（英） | ||||||||||
| en | ||||||||||
| Japan Aerospace Exploration Agency(JAXA) | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| Japan Aerospace Exploration Agency(JAXA) | ||||||||||
| 出版者（英） | ||||||||||
| 出版者 | Institute of Electrical and Electronics Engineers, Inc.(IEEE) | |||||||||
| 書誌情報 |
en : 2015 IEEE Aerospace Conference 発行日 2015-03 |
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| 会議概要（会議名, 開催地, 会期, 主催者等）（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | Aerospace Conference, 2015 IEEE (March 7-14, 2015. Yellowstone Conference Center Big Sky), Montana, USA | |||||||||
| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | This paper describes solutions to the lunar Distant Retrograde Orbit (DRO) rendezvous in terms of trajectory and launch window design. Our study is motivated by the future potential to construct a new space station or fuel refilling ports in the Earth-Moon neighborhood. A DRO, which has a long-term stability, is a possible candidate for the orbit in which such habitable structures are located. Since these structures have to rendezvous with visiting vehicles from Low Earth Orbit (LEO), it is valuable to investigate rendezvous technology in DROs. Our current study is focused on designing rendezvous trajectories which require reasonable operational cost, such as delta-v and flight time. Launch window analysis derived from trajectory design is also within the scope of this paper. We applied a three-impulse transfer with retrograde powered lunar gravity assist, and examined the total delta-v and flight time required to transfer from LEO to various phase points in a certain DRO. The results showed how a certain region where the ΔV cost is low exists, and the flight time varies considerably according to the rendezvous point. We proposed an applicable launch window with these features in mind. We also conducted a case study to evaluate delta-v and the flight time required for rendezvous after the visiting vehicle is inserted into the DRO at a certain distance from the station. The result showed the potential to widen the option to rendezvous. In our study, trajectories are computed using Systems Tool Kit (STK) / Astrogator software module. Unlike a Circular Restricted Three-Body Problem (CRTBP) model, STK/Astrogator employs various force models and accurately integrates trajectories, which enables more realistic operation scenarios to be discussed. | |||||||||
| ISBN | ||||||||||
| 識別子タイプ | ISBN | |||||||||
| 関連識別子 | 978-1-4799-5379-0 | |||||||||
| DOI | ||||||||||
| 識別子タイプ | DOI | |||||||||
| 関連識別子 | http://dx.doi.org/10.1109/AERO.2015.7119023 | |||||||||
| 関連名称 | info:doi/10.1109/AERO.2015.7119023 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: PA1510041000 | |||||||||
