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Practical analytic solution of relative motion between formation flying satellites with different ballistic coefficients in near-circular reference orbit
https://jaxa.repo.nii.ac.jp/records/7573
https://jaxa.repo.nii.ac.jp/records/7573a253c4d0-399f-4055-91f0-93609a0dd368
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 | Practical analytic solution of relative motion between formation flying satellites with different ballistic coefficients in near-circular reference orbit | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 編隊飛行 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 衛星軌道 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 位置誤差 | |||||
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 | 状態遷移行列 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 伝播方程式 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 相対運動 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 数学的解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 数値解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 軌道 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 共分散 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 摂動 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 永年摂動 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | formation flying | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | satellite orbit | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | position error | |||||
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 | state transition matrix | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | propagation equation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | relative motion | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | mathematical analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | numerical analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | trajectory | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | covariance | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | perturbation | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | secular perturbation | |||||
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 | 異なる弾道係数を持つフォーメーションフライト衛星の円軌道における相対運動解析の1手法 | |||||
著者 |
山元, 透
× 山元, 透× Yamamoto, Toru |
|||||
著者所属 | ||||||
宇宙航空研究開発機構 総合技術研究本部 | ||||||
著者所属(英) | ||||||
en | ||||||
Japan Aerospace Exploration Agency Institute of Aerospace Technology | ||||||
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 en : Proceedings of 15th Workshop on JAXA Astrodynamics and Flight Mechanics p. 41-46, 発行日 2006-03 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 衛星群のフォーメーションフライトは多様なミッションに適用可能な技術であり、近年注目を浴びている。円軌道に近い軌道におけるランデブーの問題にはHill方程式のClohessy-Wiltshire解が有効であるが、フォーメーションフライトミッションにおいて長期間相対的な位置を保持し続ける場合には空気抵抗や重力による摂動力の差の寄与が大きく、不十分である。本講演では、2衛星の弾道係数の差と、重力による摂動力の差を考慮した、長期間の相対運動解析のための実際的手法を提案する。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Formation flying of multiple satellites is an evolving technology with many possible applications. To design the formation-flying missions, it is important to understand the characteristics of the mission orbit and the dynamics of the relative motion. This paper proposes an analytic solution for relative motion of formation-flying satellites that includes not only the effect from J(sub 2) perturbations but also the effect caused by the difference in their ballistic coefficients. The solution is practical and useful for mission analysis and design of formation-flying missions in near-circular orbit. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0063480008 |