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Feasibility assessment of low-ballistic-coefficient aerocapture for Jupiter exploration
https://jaxa.repo.nii.ac.jp/records/7563
https://jaxa.repo.nii.ac.jp/records/7563a2c45f9b-3e12-4581-840a-dda158ee7568
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
言語 | en | |||||
タイトル | Feasibility assessment of low-ballistic-coefficient aerocapture for Jupiter exploration | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | エアロキャプチャ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ソーラーセイル | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 軌道挿入 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 軌道解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空気力 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 弾道係数 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ソーラーセイル再利用 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 膜温度限界 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 木星 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 再利用 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 空力加熱 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 計算機シミュレーション | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | モンテカルロ法 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerocapture | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | solar sail | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | orbit insertion | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | trajectory analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic force | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | ballistic coefficient | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | reusing solar sail | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | membrane temperature limit | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Jupiter | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | reuse | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerodynamic heating | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | computerized simulation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | Monte Carlo method | |||||
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 | |||||
その他のタイトル | ||||||
その他のタイトル | 木星探査における低弾道エアロキャプチャの可能性 | |||||
著者 |
古川, 宗孝
× 古川, 宗孝× 安部, 隆士× Furukawa, Munetaka× Abe, Takashi |
|||||
著者所属 | ||||||
東京大学 大学院工学系研究科 | ||||||
著者所属 | ||||||
宇宙航空研究開発機構 宇宙科学研究本部 | ||||||
著者所属(英) | ||||||
en | ||||||
University of Tokyo School of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Space and Astronautical Science | ||||||
出版者 | ||||||
出版者 | 宇宙航空研究開発機構宇宙科学研究本部 | |||||
出版者(英) | ||||||
出版者 | Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS) | |||||
書誌情報 |
第16回アストロダイナミクスシンポジウム講演後刷り集 2006 en : Proceedings of 16th Workshop on JAXA Astrodynamics and Flight Mechanics p. 362-370, 発行日 2007-03 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | エアロキャプチャは、従来の化学推進による手段と比較して、軌道投入に要する推進剤を減らすことが可能であると知られている。 突入飛行経路角のウィンドウや空力加熱環境などの厳しい条件から、これまで実現されたことはなかった。しかし、軽量かつ大面積の膜面を利用した低弾道エアロキャプチャならば、そのようなリスクを避け、実現可能性がある。JAXA将来ミッションとして計画されているソーラセイルミッションでは、母船から分離される小型オービタの木星周回軌道への投入も計画されている。そこで、ソーラセイルに使用された母船の膜面の1部を小型オービタの軌道投入に再利用するとした仮定のもと、エアロキャプチャの木星における実現可能性について検討を行った。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | The aerocapture is known to be an orbit insertion technique around planetary body at a fraction of the propellant of the traditional chemical propulsive technique. Severe aerocapture conditions such as the very narrow entry corridor and the aerodynamic heating environment have prevented us from putting it into practical use in a planetary exploration mission. However, the low-ballistic-coefficient aerocapture where an orbiter is connected to the light and wide membrane decelerator has the potential to reduce the risk of the aerocapture. In the Solar Sail mission which is planed as one of the future missions of JAXA, the orbit insertion around Jupiter of the small orbiter which is separated from the mother spacecraft is included. In this paper, we investigated the feasibility of the aerocapture at Jupiter, assuming that a fraction of the Solar Sail membrane of the mother spacecraft was reused in order to insert the separated orbiter into the orbit around Jupiter. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0063481062 |