軌道上微小デブリ計測技術の研究開発: JAXA 宇宙環境グループでの開発センサを中心に

第5回スペースデブリワークショップ (2013年1月22-23日. 宇宙航空研究開発機構調布航空宇宙センター), 調布市, 東京

5th Space Debris Workshop (January 22-23, 2013, Chofu Aerospace Center, Japan Aerospace Exploration Agency (JAXA)), Chofu, Tokyo, Japan

軌道上微小デブリ（ダスト）計測の国内での研究開発を概観するとともにJAXA宇宙環境グループで開発中のアクティブセンサの開発状況について報告する。軌道上ダスト計測の研究開発は１９８０年代後半からメテオロイドの計測を目的として活発化した。アクティブ型の計測器は１９９０年の「ひてん」（Muses-A）に搭載されたMDC（Munich Dust Counter）が日本最初の搭載である。一方、パッシブ型の計測器は宇宙科学研究所で計画された彗星からのサンプルリターンミッション(SOCCOR 計画)での研究成果をベースに開発された「キャリブレーテッド・エアロジェル」を用いたダストコレクタが1997 年にスペースシャトルに搭載されたのが最初である。その後、アクティブ型、パッシブ型とも多くの研究が行われてきている。JAXA 宇宙環境グループは諸外国で計測実績がなく、かつ、宇宙機への影響が懸念されるサイズ領域である大きさ１００ micrometers～数ｍｍのデブリの存在量の計測を目的としたアクティブ型計測器を開発した。このセンサは２０１４年の「こうのとり」（HTV）に搭載され実装実証試験を行う予定である。

The history of Japanese R&D into in-situ sensors for micro-meteoroid and orbital debris (MMOD) measurements is neither particularly long nor short. Research into active sensors started for the meteoroid observation experiment on the HITEN (MUSES-A) satellite of ISAS/JAXA launched in 1990, which hadMDC (Munich Dust Counter) on-board sensors for micro meteoroid measurement. This was a collaboration between Technische Universitat Munchen and ISAS/JAXA. The main purpose behind the start of passive sensor research was SOCCOR, a late 80's Japan-US mission that planned to capture cometary dust and return to the Earth. Although this mission was canceled, the research outcomes were employed in a JAXA micro debris sample return mission using calibrated aerogel involving the Space Shuttle and the International Space Station. There have been many other important activities apart from the above, and the knowledge generated from them has contributed to JAXA's development of a new type of active dust sensor. JAXA and its partners have been developing a simple in-situ active dust sensor of a new type to detect dust particles ranging from a hundred micrometers to several millimeters. The distribution and flux of the debris in the size range are not well understood and is difficult to measure using ground observations. However, it is important that the risk caused by such debris is assessed. In-situ measurement of debris in this size range is useful for 1) verifying meteoroid and debris environment models, 2) verifying meteoroid and debris environment evolution models, and 3) the real time detection of explosions, collisions and other unexpected orbital events. Multitudes of thin, conductive copper strips are formed at a fine pitch of 100 um on a film 12.5 um thick of nonconductive polyimide. An MMOD particle impact is detected when one or more strips are severed by being perforated by such an impact. This sensor is simple to produce and use and requires almost no calibration as it is essentially a digital system. Based on this sensor technology, the Kyushu Institute of Technology (KIT) has designed and developed an educational version of the sensor, which is currently on board the nano-satellite Horyu-II, which was built at KIT and launched on May 18, 2012 by JAXA. Although the sensor has a very small sensing area, sensor data were nonetheless successfully received. Moreover, a laboratory version of the sensor fitted on QSAT-EOS, a small satellite, will be launched in December 2012. This version was developed and manufactured by Japan's QPS Institute to evaluate the sensor's capability regarding hypervelocity impact experiments at JAXA. JAXA's flight version, to be employed on satellites and/or the ISS, will be ready soon and a flight demonstration will be conducted on KOUNOTORI (HTV) in 2014. This paper reports on the R&D into in-situ measurement MMOD sensors at JAXA.

著者人数: 12名

形態: カラー図版あり

Number of authors: 12

Physical characteristics: Original contains color illustrations

資料番号: AA0062322026

レポート番号: JAXA-SP-13-018