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
| Autor: | Ui, Kyoichi, Miyashita, Naoki, Miyamoto, Kei, Matsunaga, Saburo |
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| Jazyk: | angličtina |
| Rok vydání: | 2005 |
| Předmět: | |
| Zdroj: | 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 = ISAS proceedings of 14th Workshop on Astrodynamics and Flight Mechanics 2004: A Collection of Technical Papers. :121-126 |
| ISSN: | 0918-8053 0047-8970 |
| Popis: | 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。 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. 資料番号: AA0047897022 |
| Databáze: | OpenAIRE |
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