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: 著書/レポートタイプへの貢献会議での発言

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.

元の言語英語
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
出版者International Astronautical Federation, IAF
ページ1964-1969
ページ数6
ISBN(電子版)9781510818934
出版物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(印刷物)0074-1795

その他

その他66th International Astronautical Congress 2015: Space - The Gateway for Mankind's Future, IAC 2015
イスラエル
Jerusalem
期間10/12/1510/16/15

Fingerprint

meteoroids
debris
Debris
sensor
orbitals
sensors
Sensors
monitors
transducer
arcs
in situ measurement
electrical conductivity
in situ
electrical resistivity
momentum
spacecraft
spacecraft equipment
Spacecraft equipment
damage
Strip telecommunication lines

All Science Journal Classification (ASJC) codes

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

これを引用

Kitazawa, Y., Matsumoto, H., Okudaira, O., Kimoto, Y., Hanada, T., Akahoshi, Y., ... Hasegawa, S. (2015). IAC-15-A6.1.8 Development on in-situ sensors for micro-meteoroid and orbital debris measurement at JAXA. : 66th International Astronautical Congress 2015, IAC 2015: Space - The Gateway for Mankind's Future (pp. 1964-1969). (Proceedings of the International Astronautical Congress, IAC; 巻数 3). International Astronautical Federation, IAF.

IAC-15-A6.1.8 Development on in-situ sensors for micro-meteoroid and orbital debris measurement at JAXA. / Kitazawa, Yukihito; Matsumoto, Haruhisa; Okudaira, Osamu; Kimoto, Yugo; Hanada, Toshiya; Akahoshi, Yasuhiro; Sakurai, Akira; Kunihiro, Funakoshi; Yasaka, Tetsuo; Nakaniura, Maki; Kobayashi, Masanori; Hasegawa, Sunao.

66th International Astronautical Congress 2015, IAC 2015: Space - The Gateway for Mankind's Future. International Astronautical Federation, IAF, 2015. p. 1964-1969 (Proceedings of the International Astronautical Congress, IAC; 巻 3).

研究成果: 著書/レポートタイプへの貢献会議での発言

Kitazawa, Y, Matsumoto, H, Okudaira, O, Kimoto, Y, Hanada, T, Akahoshi, Y, Sakurai, A, Kunihiro, F, Yasaka, T, Nakaniura, M, Kobayashi, M & Hasegawa, S 2015, IAC-15-A6.1.8 Development on in-situ sensors for micro-meteoroid and orbital debris measurement at JAXA. : 66th International Astronautical Congress 2015, IAC 2015: Space - The Gateway for Mankind's Future. Proceedings of the International Astronautical Congress, IAC, 巻. 3, International Astronautical Federation, IAF, pp. 1964-1969, 66th International Astronautical Congress 2015: Space - The Gateway for Mankind's Future, IAC 2015, Jerusalem, イスラエル, 10/12/15.
Kitazawa Y, Matsumoto H, Okudaira O, Kimoto Y, Hanada T, Akahoshi Y その他. IAC-15-A6.1.8 Development on in-situ sensors for micro-meteoroid and orbital debris measurement at JAXA. : 66th International Astronautical Congress 2015, IAC 2015: Space - The Gateway for Mankind's Future. International Astronautical Federation, IAF. 2015. p. 1964-1969. (Proceedings of the International Astronautical Congress, IAC).
Kitazawa, Yukihito ; Matsumoto, Haruhisa ; Okudaira, Osamu ; Kimoto, Yugo ; Hanada, Toshiya ; Akahoshi, Yasuhiro ; Sakurai, Akira ; Kunihiro, Funakoshi ; Yasaka, Tetsuo ; Nakaniura, Maki ; Kobayashi, Masanori ; Hasegawa, Sunao. / IAC-15-A6.1.8 Development on in-situ sensors for micro-meteoroid and orbital debris measurement at JAXA. 66th International Astronautical Congress 2015, IAC 2015: Space - The Gateway for Mankind's Future. International Astronautical Federation, IAF, 2015. pp. 1964-1969 (Proceedings of the International Astronautical Congress, IAC).
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abstract = "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.",
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