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

Hihara, Hiroki; Iwase, Kaori; Sano, Junpei; Otake, Hisashi; Okada, Tatsuaki; Funase, Ryu; Kashikawa, Nobunari; Higashino, Isamu; Masuda, Takatsugu

doi:10.1117/1.jrs.8.084987

Cited by 12 publications

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“…TIR is a light-weighted thermal infrared imager, inherited from the Longwave Infrared Camera (LIR) onboard Akatsuki (PLANET-C) Venus climate orbiter (Fukuhara et al 2011), which enabled development on a very short timescale and use of the same apparatus for calibration for the cold temperature range in the space chamber. TIR consists of the sensor unit (TIR-S), the power supply unit (TIR-AE), and the digital electronics unit (DE) (Hihara et al 2014). The photographs of TIR-S and TIR-AE are shown in Fig.…”

Section: Configuration and Functions Of Tirmentioning

confidence: 99%

“…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.…”

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Thermal Infrared Imaging Experiments of C-Type Asteroid 162173 Ryugu on Hayabusa2

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Section: Configuration and Functions Of Tirmentioning

confidence: 99%

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Thermal Infrared Imaging Experiments of C-Type Asteroid 162173 Ryugu on Hayabusa2

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“…TIR consists of the sensor unit (TIR-S), the power supply unit (TIR-AE), and the digital electronics unit (DE) (Hihara et al 2014). The photographs of TIR-S and TIR-AE are shown in Fig.…”

Section: Configuration and Functions Of Tirmentioning

confidence: 99%

“…The mechanical shutter is located between the lens and filter, and operated using a stepping motor. The Photograph of the detector package and the uncooled micro-bolometer array in the package, and scanning electron microscope image of a detector pixel (from Hihara et al 2014) shutter is only opened to take images and basically closed to protect direct irradiation of sunlight for contingency. The shutter is made of an aluminum plate with almite processing, or anodic oxidized coating, and its hemispherical emissivity is 0.89.…”

Section: Configuration and Functions Of Tirmentioning

confidence: 99%

Thermal Infrared Imaging Experiments of C-Type Asteroid 162173 Ryugu on Hayabusa2

Okada¹,

Fukuhara²,

Tanaka³

et al. 2016

Hayabusa2

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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.

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“…HAYABUSA2 asteroid probe was launched successfully in 2014 for the exploration of C class near-Earth asteroid 162173 (1999JU3) 1 . The system integration environment and the outlook of HAYABUSA2 are shown in Figure 1.…”

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Infrared sensor system using robotics technology for inter-planetary mission

Hihara¹,

Takano

Sano³

et al. 2015

SPIE Proceedings

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Infrared sensor system is a major concern for inter-planetary missions in order to investigate the nature and the formation processes of planets and asteroids. Since it takes long time for the communication of inter-planetary probes, automatic and autonomous functions are essential for provisioning observation sequence including the setup procedures of peripheral equipment. Robotics technology which has been adopted on HAYABUSA2 asteroid probe provides functions for setting up onboard equipment, sensor signal calibration, and post signal processing. HAYABUSA2 was launched successfully in 2014 for the exploration of C class near-Earth asteroid 162173 (1999JU3). An optical navigation camera with telephoto lens (ONC-T), a thermal-infrared imager (TIR), and a near infrared spectrometer (NIRS3) have been developed for the observation of geology, thermo-physical properties, and organic or hydrated materials on the asteroid. ONC-T and TIR are used for those scientific purposes as well as assessment of landing site selection and safe descent operation onto the asteroid surface for sample acquisition. NIRS3 is used to characterize the mineralogy of the asteroid surface by observing the 3-micron band, where the particular diagnostic absorption features due to hydrated minerals appear.Modifications were required in order to apply robotics technology for the probe due to the difference of operation on satellites from robot operation environment. The major difference is time line consideration, because the standardized robotics operation software development system is based on event driven framework. The consistency between the framework of time line and event driven scheme was established for the automatic and autonomous operation for HAYABUSA2.

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

Cited by 12 publications

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Thermal Infrared Imaging Experiments of C-Type Asteroid 162173 Ryugu on Hayabusa2

Thermal Infrared Imaging Experiments of C-Type Asteroid 162173 Ryugu on Hayabusa2

Thermal Infrared Imaging Experiments of C-Type Asteroid 162173 Ryugu on Hayabusa2

Infrared sensor system using robotics technology for inter-planetary mission

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