WEKO3
アイテム
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"pubdate": {"attribute_name": "公開日", "attribute_value": "2015-03-26"}, "publish_date": "2015-03-26", "publish_status": "0", "recid": "8024", "relation": {}, "relation_version_is_last": true, "title": ["デブリ衝突により起こる太陽電池アレイの持続放電の閾値"], "weko_shared_id": -1}
デブリ衝突により起こる太陽電池アレイの持続放電の閾値
https://jaxa.repo.nii.ac.jp/records/8024
https://jaxa.repo.nii.ac.jp/records/8024b4be1993-2c33-4809-8676-d5453406d2a7
Item type | 会議発表論文 / Conference Paper(1) | |||||
---|---|---|---|---|---|---|
公開日 | 2015-03-26 | |||||
タイトル | ||||||
タイトル | デブリ衝突により起こる太陽電池アレイの持続放電の閾値 | |||||
言語 | ||||||
言語 | jpn | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 航空宇宙環境 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 太陽電池アレイ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 宇宙機給電 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 持続放電 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 宇宙デブリ | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超高速衝突 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 短絡 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 衝突速度 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 電子密度 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 低高度地球周回軌道 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | aerospace environment | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | solar array | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | spacecraft power supply | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | sustained arc | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | space debris | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | hypervelocity impact | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | short circuit | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | impact velocity | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | electron density | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | low Earth orbit | |||||
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(英) | ||||||
その他のタイトル | Threshold of sustained arc by space debris impact on solar array | |||||
著者 |
長崎, 俊和
× 長崎, 俊和× 福重, 進也× 赤星, 保浩× 渡辺, 圭子× 菅原, 賢尚× 高良, 隆男× Cho, Mengu× 原田, 昭治× Nagasaki, Toshikazu× Fukushige, Shinya× Akahoshi, Yasuhiro× Watanabe, Keiko× Sugahara, Kensho× Kora, Takao× Cho, Mengu× Harada, Shoji |
|||||
著者所属 | ||||||
九州工業大学 大学院工学研究科 | ||||||
著者所属 | ||||||
九州工業大学 大学院工学研究科 | ||||||
著者所属 | ||||||
九州工業大学 工学部 機械知能工学科 | ||||||
著者所属 | ||||||
大阪大学 | ||||||
著者所属 | ||||||
九州工業大学 工学部 機械知能工学科 | ||||||
著者所属 | ||||||
九州工業大学 工学部 機械知能工学科 | ||||||
著者所属 | ||||||
九州工業大学 工学部 電気電子工学科 | ||||||
著者所属 | ||||||
九州工業大学 工学部 機械知能工学科 | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology Graduate School of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology Graduate School of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology Department of Mechanical and Control Engineering, Faculty of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Osaka University | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology Department of Mechanical and Control Engineering, Faculty of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology Department of Mechanical and Control Engineering, Faculty of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology Department of Electrical Engineering and Electronics, Faculty of Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Kyushu Institute of Technology Department of Mechanical and Control Engineering, Faculty of Engineering | ||||||
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27回宇宙エネルギーシンポジウム 平成19年度 en : The Twenty-seventh Space Energy Symposium p. 54-58, 発行日 2008-05 |
|||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | In recent years, space debris increases because many rockets and satellites have been launched. A solar array of a spacecraft has become larger with the higher voltage and electrical power. Therefore, the risk of debris impact and possibility of discharge on the solar array is increasing. If space debris impacts solar array, it electric power decreases or loses. When space debris impact on the solar array, high-density plasma is discharged. The arc that led may generate the plasma. This is Temporary Sustained Arc. This discharge can lead to carbonize the insulation layer of the solar array by Joule heat due to the large current through the plasma, and form permanent short-circuit. If this phenomenon continues, a permanent short circuit course will be formed between a solar cell and a substrate. This is Permanent Sustained Arc. It causes decrease or loss of generating capacity of a solar array coupon. In this study, the first purpose is verified that sustained arc is discharged or not by space debris impacts on solar array. The second purpose is elucidated the threshold of sustained arc. We want to reduce the influence affect the missions of a satellite by those results. Therefore, we took notice a density and electron temperature of the plasma which induce to discharge and clarified the threshold of sustained arc generating for hypervelocity impact test by two-stage light gas gun. The triple probe method was used plasma measurement test. The results show that electron temperature and electron density have correlation with impact speed, and the plasma density is higher than the plasma environment on low earth orbit. A possibility of TSA (Temporary Sustained Arc) generation is large over 80 [V], and generating of PSA (Permanent Sustained Arc) was confirmed over 183 [V]-2.4 [A] of power supply voltage. The generating conditions of PSA are sustaining voltage is 50 [V], current is 2.2 [A] and dissipation power of discharge circuit is 110 [W]. Therefore, it is desirable that dissipation power of the satellite is less than 110 [W] for preventing generating of PSA. | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0063965011 |