| 講演名 | 2010/10/21 Mission Trajectory Design using Three-Body Dynamics , |
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| PDFダウンロードページ | PDFダウンロードページへ |
| 抄録(和) | 〓〓〓〓 〓〓〓 〓〓 〓〓 〓〓〓〓 〓〓 〓〓〓 〓〓〓 〓〓 〓〓 〓〓〓 〓〓〓〓〓 2 〓 〓〓 (two-body problem) 〓 〓〓〓 Hohmann transfer 〓 〓〓〓〓 〓〓 Patched Conic Approximation 〓〓 〓 〓〓 〓〓〓〓〓 〓〓. Hohmann transfer 〓 〓 〓〓〓〓 〓〓 〓 〓〓〓 〓〓〓 〓 〓〓 〓〓 〓〓〓 〓〓 〓〓〓〓〓, Patched Conic Approximation 〓 〓〓〓〓 〓〓 〓〓 2 〓 〓〓〓 〓〓〓〓 〓 〓 〓〓〓 2 〓 〓〓〓 〓〓〓 Hohmann 〓〓 〓〓〓 〓〓〓〓 〓〓〓〓〓〓 〓〓 〓〓 〓〓 〓〓〓 〓 〓〓〓 〓〓〓〓. 〓 〓〓〓 〓〓〓 〓〓〓〓 〓〓〓〓 〓, 〓 〓〓〓 〓〓〓〓〓 2 〓 〓〓〓 〓, 〓〓 〓〓〓〓 〓〓 〓〓〓〓 〓〓〓 〓〓 〓〓〓〓〓 〓〓 〓〓 〓〓 〓〓〓 〓〓 〓〓〓〓 〓〓. 〓〓〓, 〓〓 〓〓 〓〓〓 〓〓 〓〓〓〓〓 〓〓 〓〓〓 〓〓〓 〓〓 〓〓〓 〓〓〓〓 〓〓〓〓 〓〓 〓〓〓 Patched Conic Approximation 〓 〓〓〓〓 〓〓〓 〓〓 〓〓〓 〓〓 (conic) 〓〓〓 〓〓〓 〓〓 〓〓 〓〓〓 〓 〓〓〓 〓〓〓 〓〓〓〓 〓〓〓 〓〓〓〓 〓〓. 〓〓 〓〓 3 〓 〓〓〓〓 〓〓〓〓 〓〓 〓 〓〓〓 〓〓〓〓 〓〓〓〓〓 〓〓〓〓〓 〓〓〓〓〓. 〓〓〓〓〓〓 〓〓〓〓 〓〓〓 〓〓 〓〓 〓 〓〓〓 〓〓〓〓 〓〓 〓〓〓〓 〓〓〓 〓〓〓 〓 〓〓 〓〓〓〓. 〓 〓〓〓〓〓 2 〓〓〓 〓〓〓 〓〓 〓〓 〓〓 〓〓〓 〓〓〓〓〓 〓〓〓 〓〓〓〓 〓〓〓〓 〓〓 〓〓〓 〓〓〓〓. |
| 抄録(英) | Most mission trajectory design technologies for space exploration have been utilized the Patched Conic Approximation which is based on Hohmann transfer in two-body problem. The Hohmann transfer trajectory is basically an elliptic trajectory, and Patched Conic Approximation consists of Hohmann transfer trajectories in which each trajectory are patched to the next one. This technology is the most efficient method when considering only one major planet at each patch trajectory design. The disadvantages of the conventional Patched Conic Approach are more fuel (or mass) needed and only conic trajectories are designed. Recent space exploration missions need to satisfy more various scientific or engineering goals, and mission utilizing smaller satellites are needed for cost reduction. The geometrical characteristics of three-body dynamics could change the paradigm of the conventional solar system. In this theoretical concept, one can design a trajectory connecting around the solar system with comparably very small energy. In this paper, the basic three-body dynamics are introduced and a spacecraft mission trajectory is designed utilizing the three-body dynamics. |
| キーワード(和) | 〓〓 〓〓 〓〓 / 3 〓 〓〓〓 |
| キーワード(英) | Mission Trajectory Design / Three-body Dynamics |
| 資料番号 | SAT2010-71 |
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| 研究会情報 | |
| 研究会 | SAT |
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| 開催期間 | 2010/10/21(から1日開催) |
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| 講演論文情報詳細 | |
| 申込み研究会 | Satellite Telecommunications (SAT) |
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| 本文の言語 | ENG |
| タイトル（和） | |
| サブタイトル（和） | |
| タイトル（英） | Mission Trajectory Design using Three-Body Dynamics |
| サブタイトル（和） | |
| キーワード(1)（和/英） | 〓〓 〓〓 〓〓 / Mission Trajectory Design |
| キーワード(2)（和/英） | 3 〓 〓〓〓 / Three-body Dynamics |
| 第 1 著者 氏名（和/英） | / Tae-Jin Chung |
| 第 1 著者 所属（和/英） | Satellite Technology Research Center, KAIST |
| 発表年月日 | 2010/10/21 |
| 資料番号 | SAT2010-71 |
| 巻番号（vol） | vol.110 |
| 号番号（no） | 256 |
| ページ範囲 | pp.- |
| ページ数 | 6 |
| 発行日 | |