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

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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.

Original languageEnglish
Title of host publication66th International Astronautical Congress 2015, IAC 2015
Subtitle of host publicationSpace - The Gateway for Mankind's Future
PublisherInternational Astronautical Federation, IAF
Pages1964-1969
Number of pages6
ISBN (Electronic)9781510818934
Publication statusPublished - Jan 1 2015
Event66th International Astronautical Congress 2015: Space - The Gateway for Mankind's Future, IAC 2015 - Jerusalem, Israel
Duration: Oct 12 2015Oct 16 2015

Publication series

NameProceedings of the International Astronautical Congress, IAC
Volume3
ISSN (Print)0074-1795

Other

Other66th International Astronautical Congress 2015: Space - The Gateway for Mankind's Future, IAC 2015
CountryIsrael
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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    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. In 66th International Astronautical Congress 2015, IAC 2015: Space - The Gateway for Mankind's Future (pp. 1964-1969). (Proceedings of the International Astronautical Congress, IAC; Vol. 3). International Astronautical Federation, IAF.