TY - GEN
T1 - IAC-15-A6.1.8 Development on in-situ sensors for micro-meteoroid and orbital debris measurement at JAXA
AU - Kitazawa, Yukihito
AU - Matsumoto, Haruhisa
AU - Okudaira, Osamu
AU - Kimoto, Yugo
AU - Hanada, Toshiya
AU - Akahoshi, Yasuhiro
AU - Sakurai, Akira
AU - Kunihiro, Funakoshi
AU - Yasaka, Tetsuo
AU - Nakaniura, Maki
AU - Kobayashi, Masanori
AU - Hasegawa, Sunao
PY - 2015/1/1
Y1 - 2015/1/1
N2 - 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.
AB - 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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M3 - Conference contribution
AN - SCOPUS:84992179845
T3 - Proceedings of the International Astronautical Congress, IAC
SP - 1964
EP - 1969
BT - 66th International Astronautical Congress 2015, IAC 2015
PB - International Astronautical Federation, IAF
T2 - 66th International Astronautical Congress 2015: Space - The Gateway for Mankind's Future, IAC 2015
Y2 - 12 October 2015 through 16 October 2015
ER -