研究者業績
基本情報
- 所属
- 国立研究開発法人宇宙航空研究開発機構 宇宙科学研究所 太陽系科学研究系 助教東京大学 大学院理学系研究科 地球惑星科学専攻 助教
- 学位
- 理学博士(名古屋大学)理学修士(名古屋大学)
- 連絡先
- hayakawa
planeta.sci.isas.jaxa.jp - J-GLOBAL ID
- 200901009402364446
- researchmap会員ID
- 1000363026
経歴
3-
2007年9月 - 現在
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2003年10月 - 2007年8月
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1990年3月 - 2003年9月
学歴
2-
- 1989年
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- 1984年
論文
72-
The Planetary Science Journal 7(5) 121-121 2026年5月1日Abstract 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 2026年4月 査読有り
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The Astronomical Journal 171(3) 187-187 2026年2月25日Abstract 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 2025年7月10日Abstract 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-
第50回月・惑星シンポジウム = Proceedings of the 50th ISAS Lunar and Planetary Symposium 2017年8月第50回月・惑星シンポジウム (2017年8月3-4日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県著者人数: 15名資料番号: SA6000200016
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Conductivity anomaly研究会論文集 39-43 2017年
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遊・星・人: 日本惑星科学会誌 22(3) 152-158 2013年9月 査読有り招待有りはやぶさ2には小型の衝突装置(SCI)が搭載されており,これは秒速2kmで小惑星表面に衝突してクレーターを形成する.このクレーターは小惑星内部を覗くための小窓であり,リモートセンシング観測やサンプル回収から,小惑星表面の宇宙風化や浅内部構造に関する知見を得る.一方, SCIが衝突する様子は分離カメラ(DCAM3)により撮影され,イジェクタカーテンの拡大する様子や小惑星周囲を飛び交うダストを観察する. SCIによる小惑星への衝突は宇宙衝突実験ともいえる.我々はこの世界で最初の小惑星における宇宙衝突実験の機会を利用して,微小重力下における「本物の小惑星物質」のクレーター形成過程を明らかにする.
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日本惑星科学会秋期講演会予稿集 2012 19-19 2012年10月24日
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Lunar Planet. Sci. XXXII, 1497-1498 2001年
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Lunar Planet. Sci. XXXII, 1495-1496 2001年
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Lunar Planet. Sci. XXXII, 1497-1498 2001年
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Lunar Planet. Sci. XXXII, 1495-1496 2001年
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Proc. Fourth Int. Conf. On the Exploration and Utilisation of the Moon: ESA SP-462 462 187-190 2000年
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Proc. Fourth Int. Conf. On the Exploration and Utilization of the Moon:ESA SP-462 462 107-114 2000年
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Proceeding of International Workshop on Penetrometry in the Solar System 125-136 2000年
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Inst. Space Astron. Sci. Rep. No.677 677 1-21 2000年A 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年
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Proceeding of International Workshop on Penetrometry in the Solar System 125-136 2000年
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The Institute of Space and Astronautical Science report 677 1-21 2000年A 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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Adv. Space Res. 23(11) 1825-1828 1999年
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MOON AND MARS 23(11) 1825-1828 1999年
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日本惑星科学会秋期講演会予稿集 1995 205-205 1995年11月13日The 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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J. Phys. Earth 41(5) 291-304 1993年
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JOURNAL OF PHYSICS OF THE EARTH 41(5) 291-304 1993年
書籍等出版物
2-
Primitive Solar Nebula and Origin of the Planets(Terra Publication Press) 1993年
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Primitive Solar Nebula and Origin of the Planets(Terra Publication Press) 1993年
講演・口頭発表等
231-
56th LPSC 2025年3月13日
所属学協会
3-
2009年 - 現在
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1992年 - 現在
Works(作品等)
6共同研究・競争的資金等の研究課題
10-
日本学術振興会 科学研究費助成事業 基盤研究(A) 2015年4月 - 2018年3月
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日本学術振興会 科学研究費助成事業 2000年 - 2002年
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日本学術振興会 科学研究費助成事業 1997年 - 1998年
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日本学術振興会 科学研究費助成事業 1992年 - 1993年
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1984年 - 1990年