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        <title>Hayabusa2 Mission: Document</title>
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        <Citation_Information>
            <author_list>Watanabe, Sei-ichiro; Yoshikawa, Makoto; Tsuda, Yuichi; Tanaka, Satoshi</author_list>
            <editor_list>Murakami, Shin-ya; Yamamoto, Yukio; Crombie, M. Katherine; Ishihara, Yoshiaki</editor_list>
            <publication_year>2024</publication_year>
            <doi>10.17597/ISAS.DARTS/HYB2-00102</doi>
            <keyword>Hayabusa2</keyword>
            <keyword>(162173) Ryugu</keyword>
            <description>This collection contains the documents applicable to the Hayabusa2 mission as a whole.</description>
        </Citation_Information>
        <Modification_History>
            <Modification_Detail>
                <modification_date>2020-08-17</modification_date>
                <version_id>1.0</version_id>
                <description>Initial release</description>
            </Modification_Detail>
            <Modification_Detail>
                <modification_date>2021-08-20</modification_date>
                <version_id>2.0</version_id>
                <description>Updated the mission event timeline document and added a calibration paper of ONC-T.</description>
            </Modification_Detail>
            <Modification_Detail>
                <modification_date>2022-03-11</modification_date>
                <version_id>3.0</version_id>
                <description>Updated label of the collection to include Context_Area class and added a calibration paper of MasMag.</description>
            </Modification_Detail>
            <Modification_Detail>
                <modification_date>2024-12-10</modification_date>
                <version_id>4.0</version_id>
                <description>Added LIDAR and DCAM3 papers.</description>
            </Modification_Detail>
        </Modification_History>
    </Identification_Area>
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        <Time_Coordinates>
            <start_date_time>2014-12-03T04:22:04Z</start_date_time>
            <stop_date_time nilReason="unknown" xsi:nil="true"/>
        </Time_Coordinates>
        <Investigation_Area>
            <name>Hayabusa2 Asteroid Sample Return Mission</name>
            <type>Mission</type>
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                <lid_reference>urn:jaxa:darts:context:investigation:mission.hyb2</lid_reference>
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                <name>Hayabusa2</name>
                <type>Host</type>
                <description>The Hayabusa2 spacecraft is designed to obtain samples from the asteroid (162173) Ryugu and to bring back the samples to Earth, to investigate the origin of water and organic materials on Earth. It is important to understand the early history and transfer processes of the Solar System. The sub-systems that comprise the Hayabusa2 spacecraft are the telecommunications system; the power system; the attitude and orbit control system (AOCS). The telecommunications system has three X-band low-gain antennas, XLGA-A, XLGA-B, and XLGA-C, one X-band medium-gain antenna (XMGA), one X-band high-gain antenna (XHGA-T; T means transmission), and one Ka-band high-gain antenna (KaHGA-T; T means transmission). The spacecraft hosts an optical navigation camera (ONC), a laser altimeter (LIDAR; LIght Detection And Ranging), a near-infrared spectrometer (NIRS3), a thermal infrared imager (TIR), laser range finders (LRF), a flash light (FLA) that is used for finding position of target marker, five target markers (TM), a small carry-on impactor (SCI), a deployable camera (DCAM3), a lander developed by DLR and CNES (MASCOT; Mobile Asteroid surface SCOuT), three rovers (MINERVA-II1 Rover-1a, Rover-2a, MINERVA-II2 Rover-2; MINERVA-II is MIcro Nano Experimental Robot Vehicle for Asteroid the Second Generation), a sampler horn, a small monitor camera (CAM-H; CAMera Head), and a re-entry capsule.</description>
                <Internal_Reference>
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            <Observing_System_Component>
                <name>DCAM3 (Deployable Camera 3)</name>
                <type>Host</type>
                <description>The Deployable Camera 3 (DCAM3) is a small separable camera unit for simultaneous close-range observations of the impact event using Small Carry-on Impactor (SCI). DCAM3 consists of DCAM3-A (analog camera system), DCAM3-D (digital camera system), power unit, and antennas for digital and analog transmissions. The receiver units and antennas (DCAM3-ANT for DCAM3-A, and DCAM3-ANT2 for DCAM3-D) for radio communication from DCAM3, and a control unit (CAM-C) are onboard the Hayabusa2 spacecraft. The DCAM3 is the successor of DCAM1 and DCAM2 which were separated from the JAXA's solar sail spacecraft IKAROS to monitor deployment process of the solar sail.</description>
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                <name>MASCOT</name>
                <type>Host</type>
                <description>The MASCOT (Mobile Asteroid surface SCOuT) is compact landing package onboard the Hayabusa2 Spacecraft, that was developed by DLR (German Aerospace Center) and CNES (French National Center for Space Studies). MASCOT has a wide-angle camera (MASCAM; MAScot CAMera) to capture images of the lander's surrounding, an infrared spectroscopic microscope (MicrOmega) to investigate the composition and characteristics of the minerals on the surface of Ryugu, a thermal radiometer (MARA; MAscot RAdiometer) to measure the surface temperature, and a magnetometer (MasMag; MAScot MAGnetometer) to measure any magnetic field. MASCOT has a hopping mechanism using a motor to rotate a swing-arm within the lander. This hopping mechanism is designed for correcting attiude with respect to the surface, and changing location only once. MASCOT does not use solar cells but is equipped with a lithium primary battery built into the lander. The duration of the battery is about 16 hours, which corresponds to about two rotations of Ryugu.</description>
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                <name>MINERVA-II1 Rover-1a HIBOU</name>
                <type>Host</type>
                <description>MINERVA-II (MIcro Nano Experimental Robot Vehicle for Asteroid the Second Generation) is the successor of MINERVA installed on the Hayabusa spacecraft. There are two containers, one is MINERVA-II1, and the other is MINERVA-II2. MINERVA-II1 consists of Rover-1a, Rover-1b, OME-B1 (basic structure), and OME-C1 (cover). Two rovers, Rover-1a and Rover-1b, were named as HIBOU (Highly Intelligent Bouncing Observation Unit) and OWL (Observation unit with intelligent Wheel Locomotion) after landing to Ryugu, respectively. One of the purpose of HIBOU and OWL is to verify efficient moving by hopping on the surface with very weak gravity. This hopping is implemented by using a motor to rotate a swing-arm within the rover. HIBOU and OWL are designed to hop autonomously. HIBOU has solar cells, antenna for communicating with the Hayabusa2 spacecraft, two wide-angle cameras, two cameras for stereo view, temperature sensors, optical sensors, an accelerometer, and a gyroscope. Almost all HIBOU's surfaces are covered by solar cells different with OWL's surfaces, therefore HIBOU is thermally more sensitive to sunlight incidence than OWL.</description>
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                <name>MINERVA-II1 Rover-1b OWL</name>
                <type>Host</type>
                <description>MINERVA-II (MIcro Nano Experimental Robot Vehicle for Asteroid the Second Generation) is the successor of MINERVA installed on the Hayabusa spacecraft. There are two containers, one is MINERVA-II1, and the other is MINERVA-II2. MINERVA-II1 consists of Rover-1a, Rover-1b, OME-B1 (basic structure), and OME-C1 (cover). Two rovers, Rover-1a and Rover-1b, were named as HIBOU (Highly Intelligent Bouncing Observation Unit) and OWL (Observation unit with intelligent Wheel Locomotion) after landing to Ryugu, respectively. One of the purpose of HIBOU and OWL is to verify efficient moving by hopping on the surface with very weak gravity. This hopping is implemented by using a motor to rotate a swing-arm within the rover. HIBOU and OWL are designed to hop autonomously. OWL has solar cells, antenna for communicating with the Hayabusa2 spacecraft, a wide-angle camera, two cameras for stereo view, temperature sensors, optical sensors, an accelerometer, and a gyroscope. OWL's surfaces are covered by solar cells except for small areas at top and bottom surfaces different with HIBOU's surfaces, therefore OWL is thermally less sensitive to sunlight incidence than HIBOU.</description>
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                <name>MINERVA-II2 Rover-2 ULULA</name>
                <type>Host</type>
                <description>MINERVA-II (MIcro Nano Experimental Robot Vehicle for Asteroid the Second Generation) is the successor of MINERVA installed on the Hayabusa spacecraft. There are two containers, one is MINERVA-II1, and the other is MINERVA-II2. MINERVA-II2 consits of Rover-2, OME-B2 (basic structure), and OME-C2 (cover). The Rover-2 was named as ULULA (University-made Landing Unit for Locomotion on Asteroid) after landing to Ryugu. Purpose of Rover-2 is to explore efficient moving mechanism by hopping. There are four actuators onboard, micro-hopping by vibration of cilia utilizing centrifugal force, hopping by permanent magnet action, hopping by bi-metal action caused by ambient temperature change, and hopping with leaf-spring action utilizing spring's elastic energy. Rober-2 has two same cameras called MICAM, six temperature sensors, two accelerometers, and six photodiodes to determine attitude by detecting Sun.</description>
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                <name>Small Monitor Camera (CAM-H)</name>
                <type>Instrument</type>
                <description>Small Monitor Camera (CAM-H; abbreviation of CAMera Head) is used to capture an image around the sampler horn to visually comfirm expansion of sampler horn after the launch, and compression of it during touchdown to the asteroid. This instrument is part of DCAM3-A (DCAM3 Analog) system. Data from CAM-H is sent to CAM-C (CAMera Control) that is onboard Hayabusa2 spacecraft.</description>
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                <name>LIght Detection And Ranging (LIDAR)</name>
                <type>Instrument</type>
                <description>LIDAR, LIght Detection And Ranging, is a laser altimeter onboard Hayabusa2 spacecraft. LIDAR is part of navigation system of spacecraft, but it can be used for scientific instrument.  By measuring distance to surface of (162173) Ryugu will enable us to acquire spacecraft position information and topography of (162173) Ryugu, and derive albedo using measured intensity of reflected light by (162173) Ryugu. LIDAR also has dust count mode and mode for laser link experiment.</description>
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                <name>Near InfraRed Spectrometer (NIRS3)</name>
                <type>Instrument</type>
                <description>The Near Infrared Spectrometer (NIRS3) onboard the Hayabusa2 spacecraft is a point spectrometer that operates over the effective wavelength range of 1.8-3.2 micrometers with a 0.1 degree field-of-view. The 3 of the name NIRS3 comes from 3 micrometers. Around 3 micrometers, there are absorption lines of minerals with hydroxyl groups (OH). The primary goal of NIRS3 is to map the distribution of hydrated minerals on the target near-Earth asteroid (162173) Ryugu.</description>
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                <name>Optical Navigation Camera</name>
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                <description>The Optical Navigation Camera (ONC) system onboard the Hayabusa2 spacecraft consists of one telescopic camera (ONC-T) and two wide-angle cameras (ONC-W1 and ONC-W2). The ONC-T is a telescopic camera with seven band-pass filters in the visible and near-infrared range. These filters are placed on a wheel, which rotates to put a selected filter for different observations, enabling multi-band imaging.</description>
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                <name>Small Carry-on Impactor (SCI)</name>
                <type>Instrument</type>
                <description>Small Carry-on Impactor (SCI) is a deployable instrument for creating artificial crater on asteroid by impacting a liner. The liner is 2 kg copper lump, because copper can be easily separated from the asteroid's sample. By ignition of an explosive, liner will be ejected at a high speed, about 2 km/s, and while chaging its shape. This experiment will enable us to access subsurface materials which will not be affected by space weathering.</description>
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                <name>Thermal Infrared Imager (TIR)</name>
                <type>Instrument</type>
                <description>The Thermal Infrared Imager (TIR) onboard the Hayabusa2 spacecraft is based on an uncooled micro-bolometer array which can obtain thermal images of a target asteroid (162173) Ryugu. The TIR is the bolometric imager with a broadband filter in the thermal infrared range (8 to 12 um). It covers the temperature range about 150 to 460 K, and has the field of view about 16.7 x 12.7 degrees, with 0.051 degree per pixel (328 x 248 pixels). TIR is modified version of Longwave Infrared Imager (LIR) of Akatsuki, also known as Venus Climate Orbiter and PLANET-C. The primary objectives of TIR are to investigate thermophysical properties of the surface of asteroids, such as porosity, grain size, and boulder abundance. Brightness temperature map of the asteroid is derived from TIR data for each time, and the brightness temperature map at each time and its forecast is obtained with the ground calibration data. Multiple observation also estimates surface roughness at each site.</description>
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                <name>DCAM3-A (DCAM3 Analog)</name>
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                <description>DCAM3-A is analog imaging system onboard DCAM3. The purpose of DCAM3-A is a continuous monitoring of the impact event.</description>
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                <name>DCAM3-D (DCAM3 Digital)</name>
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                <description>DCAM3-D is digital imaging system onboard DCAM3. The purpose of DCAM3-D is a scientific observation of the event with wide-angle and in high-resolution.</description>
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                <name>MASCOT Camera</name>
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                <description>MASCAM (MAScot CAMera) has Wide-angle camera that takes pictures during the descent to the asteroid surface and will provide ground data for the instruments on board Hayabusa2 as well as contextual information for the instruments on board MASCOT. MASCAM has LED illumination devices in 4 colors, red, gren, blue, and near-infrared. These LEDs used in night time and acquire different reflectance image in wavelength.</description>
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                <name>MASCOT Fluxgate Magnetometer</name>
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                <description>MASMAG (MAScot fluxgate MAGnetometer) is designed to determine the asteroid's magnetic field.</description>
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                <name>MARA</name>
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                <description>MARA (MAscot RAdiometer) is a radiometer onboard MASCOT. MARA is used for the high-resolution determination of the surface temperature as well as the thermal changes during the day-night changes on the asteroid.</description>
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                <description>MicrOmega is a near-IR hyperspectral microscope and is designed to determine the mineralogical composition of the asteroid surface.</description>
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            <name>(162173) Ryugu</name>
            <alternate_designation>1999 JU3</alternate_designation>
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