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Appears in Collections:Biological and Environmental Sciences Journal Articles
Peer Review Status: Refereed
Title: Thermal Infrared Imaging Experiments of C-Type Asteroid 162173 Ryugu on Hayabusa2
Author(s): Okada, Tatsuaki
Fukuhara, Tetsuya
Tanaka, Satoshi
Taguchi, Makoto
Imamura, Takeshi
Arai, Takehiko
Senshu, Hiroki
Ogawa, Yoshiko
Demura, Hirohide
Kitazato, Kohei
Nakamura, Ryosuke
Kouyama, Toru
Sekiguchi, Tomohiko
Hasegawa, Sunao
Hagermann, Axel
Keywords: Thermography
Thermal inertia
Near-Earth asteroid
Planetary exploration
Issue Date: Jul-2017
Date Deposited: 12-Apr-2018
Citation: Okada T, Fukuhara T, Tanaka S, Taguchi M, Imamura T, Arai T, Senshu H, Ogawa Y, Demura H, Kitazato K, Nakamura R, Kouyama T, Sekiguchi T, Hasegawa S & Hagermann A (2017) Thermal Infrared Imaging Experiments of C-Type Asteroid 162173 Ryugu on Hayabusa2. Space Science Reviews, 208 (1-4), pp. 255-286.
Abstract: The thermal infrared imager TIR onboard Hayabusa2 has been developed to investigate thermo-physical properties of C-type, near-Earth asteroid 162173 Ryugu. TIR is one of the remote science instruments on Hayabusa2 designed to understand the nature of a volatile-rich solar system small body, but it also has significant mission objectives to provide information on surface physical properties and conditions for sampling site selection as well as the assessment of safe landing operations. TIR is based on a two-dimensional uncooled micro-bolometer array inherited from the Longwave Infrared Camera LIR on Akatsuki (Fukuhara et al., 2011). TIR takes images of thermal infrared emission in 8 to 12 μm with a field of view of 16 × 12 ∘ and a spatial resolution of 0.05 ∘ per pixel. TIR covers the temperature range from 150 to 460 K, including the well calibrated range from 230 to 420 K. Temperature accuracy is within 2 K or better for summed images, and the relative accuracy or noise equivalent temperature difference (NETD) at each of pixels is 0.4 K or lower for the well-calibrated temperature range. TIR takes a couple of images with shutter open and closed, the corresponding dark frame, and provides a true thermal image by dark frame subtraction. Data processing involves summation of multiple images, image processing including the StarPixel compression (Hihara et al., 2014), and transfer to the data recorder in the spacecraft digital electronics (DE). We report the scientific and mission objectives of TIR, the requirements and constraints for the instrument specifications, the designed instrumentation and the pre-flight and in-flight performances of TIR, as well as its observation plan during the Hayabusa2 mission.
DOI Link: 10.1007/s11214-016-0286-8
Rights: © The Author(s) 2016 This article is distributed under the terms of the Creative Commons Attribution 4.0 International License (, which permits unrestricted use, distribution, and reproduction in any medium, provided you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons license, and indicate if changes were made.
Notes: Additional co-authors: Tsuneo Matsunaga, Takehiko Wada, Jun Takita, Naoya Sakatani, Yamato Horikawa, Ken Endo, Jörn Helbert, and Thomas G. Müller
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