IAC-15-A6.1.8 Development on in-situ sensors for micro-meteoroid and orbital debris measurement at JAXA

Yukihito Kitazawa, Haruhisa Matsumoto, Osamu Okudaira, Yugo Kimoto, Toshiya Hanada, Yasuhiro Akahoshi, Akira Sakurai, Funakoshi Kunihiro, Tetsuo Yasaka, Maki Nakaniura, Masanori Kobayashi, Sunao Hasegawa

研究成果: Chapter in Book/Report/Conference proceedingConference contribution

抄録

The spacc debris monitor (SDM) is a large-Area impact sensor for in situ measurements of micro-mctcoroids and spacc debris of the sub-millimetre to millimetre size in the near-F.arth space environment. These meteoroid and debris particles arc very small to be detected by ground-based observations (radars and optical telcscopes) but are sufficiently large to cause serious damage to spacecraft equipment in the low Earth orbit region. The nominal detection area of the SDM is 0.1 m2 (0.35 m ∗ 0.3 m), but its dimensions can be easily modified to accommodate different SDM constraints. The SDM is made from a flexible printed circuit, which is produced from a thin film of a nonconductive material (such as polyimide) on which thin conductivc stripes are formed in parallel. The stripe width is approximately 50 pin. and the spatial separation is approximately 100 pm. as shown in Figure 1. When a micro- debris particle with an effective diameter near to or larger than the spatial separation of the stripes (here approximately 100 pm) collides with the sensor film at a velocity sufficient to penetrate it. one or more of the stripes arc cut and become nonconductive. Debris impacts can thus be detected by monitoring the electrical conductivity (resistivity) of the stripes. This sensor system can measure the size of the incident micro-debris particles by detecting the number of severed stripes. The measurement concept is registered as a patent in many countries (US8564430, CA 2712411, CN ZL200980108349.4, UA 94873, JP 5492568, and EA1906). The first SDM was launched with HTV-5 on August 19, 2015 and represents the world's first micro-debris measurement demonstration experiment to be conductcd on the ISS using the concept of conductive (resistive) strip lines for debris detection. Another type of micro-debris sensor is also on board the HTV-5 mission and is based on an impact sensor that is a piezoelectric transducer. It comprises a Chiba-koudai Debris Monitor (CDM), where six piezoelectric sensors arc attached to a structure of KASPER to provide impact timing information and impact momentum. JAXA is currently conducting an analysis of the acquired data.

本文言語英語
ホスト出版物のタイトル66th International Astronautical Congress 2015, IAC 2015
ホスト出版物のサブタイトルSpace - The Gateway for Mankind's Future
出版社International Astronautical Federation, IAF
ページ1964-1969
ページ数6
ISBN(電子版)9781510818934
出版ステータス出版済み - 1 1 2015
イベント66th International Astronautical Congress 2015: Space - The Gateway for Mankind's Future, IAC 2015 - Jerusalem, イスラエル
継続期間: 10 12 201510 16 2015

出版物シリーズ

名前Proceedings of the International Astronautical Congress, IAC
3
ISSN(印刷版)0074-1795

その他

その他66th International Astronautical Congress 2015: Space - The Gateway for Mankind's Future, IAC 2015
Countryイスラエル
CityJerusalem
Period10/12/1510/16/15

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Astronomy and Astrophysics
  • Space and Planetary Science

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