A Flight Experiment of Electrodynamic Tether using a Small Satellite: as the First Step for Debris Removal
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- KAWAMOTO Satomi
- Japan Aerospace Exploration Agency
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- KOBAYASHI Yuki
- Shizuoka Univ.
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- OHKAWA Yasushi
- Japan Aerospace Exploration Agency
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- KITAMURA Shoji
- Japan Aerospace Exploration Agency
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- NISHIDA Shin-ichiro
- Japan Aerospace Exploration Agency
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- KIKKAWA Chiharu
- Tokyo Metropolitan Univ.
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- YANAGIDA Atsushi
- Waseda Univ.
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- TODA Susumu
- Waseda Univ.
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- YAMAGIWA Yoshiki
- Shizuoka Univ.
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- CHO Mengu
- Kyushu Institute of Technology
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- HANADA Toshiya
- Kyushu University
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抄録
The active removal of existing space debris is the one of the most proactive strategies available to suppress space debris growth. The Aerospace Research and Development Directorate, Japan Aerospace Exploration Agency, is investigating an active space debris removal system that employs highly efficient electrodynamic tether (EDT) technology as its orbital transfer system. As the first step toward the realization of this debris removal system, an EDT flight experiment using a small satellite is planned to establish and demonstrate EDT technology, and to measure EDT characteristics such as electron emission and collection in the space plasma. In this paper, the results of precise numerical simulations for mission analysis arc presented, including available electric currents, orbital changes, tether stability and deployment dynamics, considering small satellite characteristics.
収録刊行物
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- The Journal of Space Technology and Science
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The Journal of Space Technology and Science 24 (2), 2_36-2_44, 2009
特定非営利活動法人 日本ロケット協会
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詳細情報 詳細情報について
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- CRID
- 1390282680057892992
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- NII論文ID
- 130004680123
- 10029362624
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- NII書誌ID
- AA10925183
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- ISSN
- 21864772
- 0911551X
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- HANDLE
- 10228/00007057
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- 本文言語コード
- en
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- データソース種別
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- JaLC
- IRDB
- CiNii Articles
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- 抄録ライセンスフラグ
- 使用不可