Curriculum Vitaes
Profile Information
- Affiliation
- Assistant Professor, Institute of Space and Astronautical Science, Department of Planetary Science, Japan Aerospace Exploration Agencyassistant professor, Department of Earth and Planetary Science, The University of Tokyo
- Degree
- Master of Science(Nagoya University)Doctor of Science(Nagoya University)
- Contact information
- hayakawa
planeta.sci.isas.jaxa.jp - J-GLOBAL ID
- 200901009402364446
- researchmap Member ID
- 1000363026
Research Interests
9Research Areas
2Research History
3Education
2Papers
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The Planetary Science Journal, 7(5) 121-121, May 1, 2026Abstract The Hayabusa2 extended mission, nicknamed Hayabusa2# ( # is pronounced SHARP, which stands for the Small Hazardous Asteroid Reconnaissance Probe), is JAXA’s small body explorer to conduct science and engineering investigations in space. After the successful return to the Earth with the samples from the carbonaceous asteroid (162173) Ryugu on 2020 December 6, Hayabusa2 diverted away from Earth to start its decade-long extended mission. The major scope includes an engineering demonstration of long-term maintenance strategies for spacecraft and operation systems and scientific investigations during various mission phases. Major scientific investigations include spacecraft-based telescopic observations of exoplanets and zodiacal dust observations during the cruise phase, flyby observations of the near-Earth asteroid (98943) Torifune in 2026 July, and rendezvous observations of near-Earth asteroid 1998 KY26 in 2031. This study overviews Hayabusa2#’s flyby and the physical properties of Torifune. Although the flyby operation planning is still ongoing, the mission will attempt to fly by the target at a distance (from the asteroid’s center) of 1–10 km. The flyby speed is planned to be 5.25 km s −1 , while the encounter location is 0.81 au from the Sun. The mission plans to fix the spacecraft’s orientation during the flyby, only allowing for a very limited pointing change to attain higher-resolution imaging. The mission will attempt to obtain science and engineering returns during the flyby. The planned investigations will offer stronger insights into material transport mechanisms in the inner solar system and a demonstration of planetary defense technologies.
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Icarus, 448 116916-116916, Apr, 2026 Peer-reviewed
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The Astronomical Journal, 171(3) 187-187, Feb 25, 2026Abstract Observations of exoplanet transits by small satellites have gained increasing attention for reducing biases in the detection of long-period planets. However, no unambiguous detection of an exoplanet has yet been demonstrated using optics with apertures smaller than 60 mm. Here, we investigated the detectability of exoplanet transits using the telescopic Optical Navigation Camera (ONC-T) on board the Hayabusa2 spacecraft, which has an effective aperture of only 15 mm. We conducted transit observations of the hot Jupiters WASP-189 b and MASCARA-1 b, collecting data for 10 and four events, respectively. The transit signal was detected with a signal-to-noise ratio (SNR) of 13 for WASP-189 b and 8 for MASCARA-1 b for each event. Stacking all events improved the SNR to 40 and 16, respectively. The transit midtimes of each event were measured with a precision of 6 minutes and were consistent with Transiting Exoplanet Survey Satellite (TESS) data to within 2 minutes. The planet-to-star radius ratio was determined with an absolute precision of 0.004 (6% relative) and agreed with TESS results to within 0.002 (3% relative). The recent ONC-T and TESS data enabled an update to the planetary ephemerides. We report a 4 σ discrepancy between the updated orbital period of MASCARA-1 b and previously reported values. ONC-T sets a new record for the smallest-aperture instrument to detect an exoplanet transit from space, advancing the frontier of exoplanet science with miniature instrumentation. Our results suggest that optics as small as ONC-T may be capable of detecting transiting long-period Jupiters: a population that remains underrepresented in current surveys.
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The Astrophysical Journal, 988(1) 12-12, Jul 10, 2025Abstract Diffuse Galactic light (DGL) is starlight scattered by interstellar dust. In visible wavelengths, earlier studies observed DGL toward regions of low optical depth in high Galactic latitude, and show marginal consistency with a theoretical model assuming single scattering by dust grains. However, a model for DGL in regions of high optical depth has not been established. In this study, we analyze wide-field imaging data toward a region of high optical depth near the Galactic center, which was obtained with the Optical Navigation Camera on board the Hayabusa2 spacecraft. The data are reduced by dark-current and stray-light subtraction, flat-field correction, and sensitivity calibration for the DGL measurement. In the image, we select dark low-intensity areas where background starlight is highly absorbed by interstellar dust, and extract the DGL component by masking pixels contaminated by stars. As a result, we find that the DGL intensity decreases toward high optical depth, and this trend is reversed from the previous measurements in optically thin regions. To explain the observed trend, we introduce DGL models inferred from a radiative transfer equation in a plane-parallel dusty slab. By assuming literature values for the albedo and scattering asymmetry factor of interstellar dust, the measured DGL intensity can be fitted by a model in which a dust slab without internal emitters is illuminated by backside stars.
Misc.
58-
日本惑星科学会秋季講演会予稿集(Web), 2020, 2020
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衝撃波シンポジウム講演論文集(CD-ROM), 2019, 2020
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日本惑星科学会秋季講演会予稿集(Web), 2018, 2018
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日本地球惑星科学連合大会予稿集(Web), 2018, 2018
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Aug, 201750th ISAS Lunar and Planetary Symposium (August 3-4, 2017. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
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Conductivity anomaly研究会論文集, 39-43, 2017
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遊・星・人: 日本惑星科学会誌, 22(3) 152-158, Sep, 2013 Peer-reviewedInvited
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Abstracts Fall Meeting of the Japanese Society for Planetary Sciences, 2012 19-19, Oct 24, 2012
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Lunar Planet. Sci., XXXII, 1571-1572, 2001
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Lunar Planet. Sci., XXXII, 1497-1498, 2001
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Lunar Planet. Sci., XXXII, 1495-1496, 2001
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Lunar Planet. Sci., XXXII, 1497-1498, 2001
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Lunar Planet. Sci., XXXII, 1495-1496, 2001
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PROCEEDINGS OF THE FOURTH INTERNATIONAL CONFERENCE ON EXPLORATION AND UTILISATION OF THE MOON, 462 187-190, 2000
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PROCEEDINGS OF THE FOURTH INTERNATIONAL CONFERENCE ON EXPLORATION AND UTILISATION OF THE MOON, 462 107-114, 2000
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Proceeding of International Workshop on Penetrometry in the Solar System, 125-136, 2000
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The Institute of Space and Astronautical Science report, 677 1-21, 2000A hard landing probe "penetrator" has been thought to be a very useful tool for planetary exploration, because it provides cost-effective capability of deploying scientific instruments on planetary surface and subsurface. But development of the penetrator for planetary exploration requires better understanding penetration dynamics in geological materials. The present paper describes some experimental results on the penetrator dynamics obtained during the course of the development of the LUNAR-A penetrator. Special emphasis is placed on understanding the effect of the oblique incidence and the attack angle of the penetrator on penetration depth and a final attitude at the rest position. Many impact experiments into a simulated lunar surface material are made using penetrators 30 mm in diameter, and the penetration characteristics (penetration path length and inflection angle) are investigated as functions of impact velocity, penetrator shape, impact angle and attack angle. The results indicate that the torque applied to the penetrator in cases of the impact with a finite attack angle changes the penetration characteristics significantly. The experimental data also suggests that the impact angle does not have a substantial effect on penetration path length and that the truncation of the nose tip from a conical nose is efficient to stabilize the penetration orientation.
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PROCEEDINGS OF THE FOURTH INTERNATIONAL CONFERENCE ON EXPLORATION AND UTILISATION OF THE MOON, 462 107-114, 2000
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Proceeding of International Workshop on Penetrometry in the Solar System, 125-136, 2000
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Inst. Space Astron. Sci. Rep. No.677, 677 1-21, 2000A hard landing probe "penetrator" has been thought to be a very useful tool for planetary exploration, because it provides cost-effective capability of deploying scientific instruments on planetary surface and subsurface. But development of the penetrator for planetary exploration requires better understanding penetration dynamics in geological materials. The present paper describes some experimental results on the penetrator dynamics obtained during the course of the development of the LUNAR-A penetrator. Special emphasis is placed on understanding the effect of the oblique incidence and the attack angle of the penetrator on penetration depth and a final attitude at the rest position. Many impact experiments into a simulated lunar surface material are made using penetrators 30 mm in diameter, and the penetration characteristics (penetration path length and inflection angle) are investigated as functions of impact velocity, penetrator shape, impact angle and attack angle. The results indicate that the torque applied to the penetrator in cases of the impact with a finite attack angle changes the penetration characteristics significantly. The experimental data also suggests that the impact angle does not have a substantial effect on penetration path length and that the truncation of the nose tip from a conical nose is efficient to stabilize the penetration orientation.
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Abstracts Fall Meeting of the Japanese Society for Planetary Sciences, 1999 34-34, Nov 13, 1999
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MOON AND MARS, 23(11) 1825-1828, 1999
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MOON AND MARS, 23(11) 1825-1828, 1999
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Abstracts Fall Meeting of the Japanese Society for Planetary Sciences, 1998 53-53, Oct 13, 1998
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Journal of the Japan Society of Precision Engineering, 63(10) 1346-1350, 1997
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Abstracts Fall Meeting of the Japanese Society for Planetary Sciences, 1996 58-58, Oct 2, 1996
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Abstracts Fall Meeting of the Japanese Society for Planetary Sciences, 1996 59-59, Oct 2, 1996
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日本惑星科学会秋季講演会予稿集, 1996 60, Oct, 1996
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Abstracts Fall Meeting of the Japanese Society for Planetary Sciences, 1995 205-205, Nov 13, 1995The accelerometer onboard LUNAR-A penetrator is developed to estimate the depth of emplacement and information on the physical properties of the lunar regolith. The decceleration record is also indispensable to design the structure of the outer case of lunar penetrator and to investigate quantitatively the shock-resistant capacity for the payload instruments. Investigation of several kinds of sensors' performance and improvement of the data acquisition system are made in order to design the most suitable accelerometer and its electronics for LUNAR-A penetrator. Using the piezoelectric type sensor with annular shear mode, the acceleration profiles with the sufficient accuracy are obtained under the actual flight conditions.
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JOURNAL OF PHYSICS OF THE EARTH, 41(5) 291-304, 1993
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JOURNAL OF PHYSICS OF THE EARTH, 41(5) 291-304, 1993
Books and Other Publications
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Primitive Solar Nebula and Origin of the Planets(Terra Publication Press), 1993
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Primitive Solar Nebula and Origin of the Planets(Terra Publication Press), 1993
Presentations
231-
69th Space Sciences and technology Conference, Nov 25, 2025
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56th LPSC, Mar 13, 2025
Professional Memberships
3-
2009 - Present
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1992 - Present
Works
6Research Projects
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Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (A), Japan Society for the Promotion of Science, Apr, 2015 - Mar, 2018
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Grants-in-Aid for Scientific Research, Japan Society for the Promotion of Science, 2000 - 2002
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Grants-in-Aid for Scientific Research, Japan Society for the Promotion of Science, 1997 - 1998
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Grants-in-Aid for Scientific Research, Japan Society for the Promotion of Science, 1992 - 1993
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1984 - 1990