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On-orbit experiment system of separation mechanism for pico-satellite on sub-payload of M-V rocket
https://jaxa.repo.nii.ac.jp/records/7655
https://jaxa.repo.nii.ac.jp/records/7655987327a7-6dbf-461a-96e3-b7587e6b8a85
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 | On-orbit experiment system of separation mechanism for pico-satellite on sub-payload of M-V rocket | |||||
言語 | ||||||
言語 | eng | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 超小型衛星 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 分離機構 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 分離速度 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 軌道上実験システム | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 光電センサー | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 熱解析 | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | ロケット | |||||
キーワード | ||||||
主題Scheme | Other | |||||
主題 | 実験 | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | pico-satellite | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | separation mechanism | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | separation speed | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | on-orbit experiment system | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | photoelectric sensor | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | thermal analysis | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | rocket | |||||
キーワード | ||||||
言語 | en | |||||
主題Scheme | Other | |||||
主題 | experimentation | |||||
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 | M-Vロケット6号機サブペイロードを利用した超小型衛星用分離機構の軌道上実験システム | |||||
著者 |
宇井, 恭一
× 宇井, 恭一× 宮下, 直己× 宮本, 径× 松永, 三郎× Ui, Kyoichi× Miyashita, Naoki× Miyamoto, Kei× Matsunaga, Saburo |
|||||
著者所属 | ||||||
東京工業大学 大学院理工学研究科 | ||||||
著者所属 | ||||||
東京工業大学 大学院理工学研究科 | ||||||
著者所属 | ||||||
東京工業大学 大学院理工学研究科 | ||||||
著者所属 | ||||||
東京工業大学 大学院理工学研究科 | ||||||
著者所属(英) | ||||||
en | ||||||
Tokyo Institute of Technology Graduate School of Science and Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Tokyo Institute of Technology Graduate School of Science and Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Tokyo Institute of Technology Graduate School of Science and Engineering | ||||||
著者所属(英) | ||||||
en | ||||||
Tokyo Institute of Technology Graduate School of Science and 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 |
平成16年度アストロダイナミクスシンポジウム:講演後刷り集 en : ISAS proceedings of 14th Workshop on Astrodynamics and Flight Mechanics 2004: A Collection of Technical Papers p. 121-126, 発行日 2005-03 |
|||||
抄録 | ||||||
内容記述タイプ | Abstract | |||||
内容記述 | 本研究では、超小型衛星用分離機構の汎用化を目指し、M-Vロケット6号機のサブペイロードを用いて分離実証実験を行うべく準備を進めている。300mm×150mm×125mmの空間内に、分離機構、ダミー衛星、計測装置、電源制御、通信、分離許可信号処理システムなどを搭載し、打ち上げ1,421秒後から168秒間、クリスマス島可視領域において実験を行う。本稿では、実験の概要、開発状況、評価のための解析項目などについて述べる。 | |||||
抄録(英) | ||||||
内容記述タイプ | Other | |||||
内容記述 | Laboratory for Space Systems (LSS) prepares an on-orbit experiment of a separation mechanism for nano-satellite on a sub-payload of M-V Rocket No.6. The sub-payload is a space for a counter weight to motion balance of the M-V rocket. LSS was permitted to use the space to conduct the present experiments. The size of the sub-payload is about 300 mm x 150 mm x 124 mm. The weight is 5 kg, provided that the allowable margin of error is less than 5 percent. The experiment system consists of the separation mechanism, a dummy mass instead of a pico-satellite, a measurement subsystem and a rocket interface subsystem. The dummy mass is a substitute for a pico-satellite. The size is 10 cm cubic and weight is about 1 kg. The measurement subsystem measures a separation speed, a motion of the dummy mass after separation and temperatures at four points. The rocket interface subsystem consists of a power, communication and timer receiving. The system attached B3PL of M-V rocket turns on before the launch and conducts a separation after 1,421 s from the launch. Acquired data in the separation are transmitted for 168 s at Christmas Island in the Republic of Kiribati. The paper describes overview, development status and measurement item to verify the system. | |||||
ISSN | ||||||
収録物識別子タイプ | ISSN | |||||
収録物識別子 | 0918-8053 | |||||
資料番号 | ||||||
内容記述タイプ | Other | |||||
内容記述 | 資料番号: AA0047897022 |