Special Section on Advances in Infrared Remote Sensing and Instrumentation

SpaceWire-based thermal-infrared imager system for asteroid sample return mission HAYABUSA2

[+] Author Affiliations
Hiroki Hihara

NEC TOSHIBA Space Systems, Ltd., 1–10 Nisshin-cho, Fuchu, Tokyo 183-8551, Japan

Kaori Iwase

NEC TOSHIBA Space Systems, Ltd., 1–10 Nisshin-cho, Fuchu, Tokyo 183-8551, Japan

Junpei Sano

NEC TOSHIBA Space Systems, Ltd., 1–10 Nisshin-cho, Fuchu, Tokyo 183-8551, Japan

Hisashi Otake

Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, Kanagawa 252-5210, Japan

Tatsuaki Okada

Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, Kanagawa 252-5210, Japan

Ryu Funase

University of Tokyo, Department of Aeronautics and Astronautics, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-8656, Japan

Ryoichi Kashikawa

NEC TOSHIBA Space Systems, Ltd., 1–10 Nisshin-cho, Fuchu, Tokyo 183-8551, Japan

Isamu Higashino

NEC TOSHIBA Space Systems, Ltd., 1–10 Nisshin-cho, Fuchu, Tokyo 183-8551, Japan

Tetsuya Masuda

NEC Corporation, 1–10 Nisshin-cho, Fuchu, Tokyo 183-8551, Japan

J. Appl. Remote Sens. 8(1), 084987 (Apr 28, 2014). doi:10.1117/1.JRS.8.084987
History: Received November 30, 2013; Revised March 24, 2014; Accepted March 25, 2014
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Abstract.  A thermal-infrared (TIR) imager system is developed for HAYABUSA2, which is planned to be launched in 2014 and aims at sample-return from a C-class near-Earth asteroid 162173 (1999JU3) considered to contain organic or hydrated materials. The system consists of a TIR imager and digital electronics, which are used not only for the scientific investigation of physical properties of the asteroid surface, but also for the assessment of landing site selection and safe descent operation onto the asteroid surface with in situ measurement. TIR adopts an uncooled bolometer. Image operations such as multiple images summation, dark image subtraction, and the compensation of dead pixels are processed onboard. A processing module is connected to sensor interfaces through SpaceWire in order to provide deterministic processing time. Data compression is also provided to reduce the restriction of transmission time, which provides the equivalent compression ratio as JPEG2000 in 1/30 processing time in average. A high-speed data recorder is connected through SpaceWire in order to record TIR data in parallel with other sensor data. The modularity of SpaceWire enables us to use these as built devices for TIR and inherits the same design as the long-wavelength infrared imager developed for the Venus climate orbiter Akatsuki.

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© 2014 Society of Photo-Optical Instrumentation Engineers

Citation

Hiroki Hihara ; Kaori Iwase ; Junpei Sano ; Hisashi Otake ; Tatsuaki Okada, et al.
"SpaceWire-based thermal-infrared imager system for asteroid sample return mission HAYABUSA2", J. Appl. Remote Sens. 8(1), 084987 (Apr 28, 2014). ; http://dx.doi.org/10.1117/1.JRS.8.084987


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