Curriculum Vitaes

Masahiko HAYAKAWA

  (早川 雅彦)

Profile Information

Affiliation
Assistant Professor, Institute of Space and Astronautical Science, Department of Planetary Science, Japan Aerospace Exploration Agency
assistant professor, Department of Earth and Planetary Science, The University of Tokyo
Degree
Master of Science(Nagoya University)
Doctor of Science(Nagoya University)

Contact information
hayakawaplaneta.sci.isas.jaxa.jp
J-GLOBAL ID
200901009402364446
researchmap Member ID
1000363026

Papers

 63
  • K. Yumoto, E. Tatsumi, T. Kouyama, D. R. Golish, Y. Cho, T. Morota, S. Kameda, H. Sato, B. Rizk, D. N. DellaGiustina, Y. Yokota, H. Suzuki, J. de León, H. Campins, J. Licandro, M. Popescu, J. L. Rizos, R. Honda, M. Yamada, N. Sakatani, C. Honda, M. Matsuoka, M. Hayakawa, H. Sawada, K. Ogawa, Y. Yamamoto, D. S. Lauretta, S. Sugita
    Icarus, 420, Sep 15, 2024  
    Various natural effects gradually alter the surfaces of asteroids exposed to the space environment. These processes are collectively known as space weathering. The influence of space weathering on the observed spectra of C-complex asteroids remains uncertain. This has long hindered our understanding of their composition and evolution through ground-based telescope observations. Proximity observations of (162173) Ryugu by the telescopic Optical Navigation Camera (ONC-T) onboard Hayabusa2 and that of (101955) Bennu by MapCam onboard Origins, Spectral Interpretation, Resource Identification, and Security-Regolith Explorer (OSIRIS-REx) found opposite spectral trends of space weathering; Ryugu darkened and reddened while Bennu brightened and blued. How the spectra of Ryugu and Bennu evolved relative to each other would place an important constraint for understanding their mutual relationship and differences in their origins and evolutions. In this study, we compared the space weathering trends on Ryugu and Bennu by applying the results of cross calibration between ONC-T and MapCam obtained in our companion paper. We show that the average Bennu surface is brighter by 18.0 ± 1.5% at v band (550 nm) and bluer by 0.18 ± 0.03 μm−1 (in the 480–850 nm spectral slope) than Ryugu. The spectral slopes of surface materials are more uniform on Bennu than on Ryugu at spatial scales larger than ∼1 m, but Bennu is more heterogeneous at scales below ∼1 m. This suggests that lateral mixing of surface materials due to resurfacing processes may have been more efficient on Bennu. The reflectance−spectral slope distributions of craters on Ryugu and Bennu appeared to follow two parallel trend lines with an offset before cross calibration, but they converged to a single straight trend without a bend after cross calibration. We show that the spectra of the freshest craters on Ryugu and Bennu are indistinguishable within the uncertainty of cross calibration. These results suggest that Ryugu and Bennu initially had similar spectra before space weathering and that they evolved in completely opposite directions along the same trend line, subsequently evolving into asteroids with different disk-averaged spectra. These findings further suggest that space weathering likely expanded the spectral slope variation of C-complex asteroids, implying that they may have formed from materials with more uniform spectral slopes.
  • Shota Kikuchi, Kei Shirai, Ko Ishibashi, Koji Wada, Yasuhiro Yokota, Rie Honda, Toshihiko Kadono, Yuri Shimaki, Naoya Sakatani, Kazunori Ogawa, Hirotaka Sawada, Takanao Saiki, Yuya Mimasu, Yuto Takei, Seiji Sugita, Toru Kouyama, Naru Hirata, Satoru Nakazawa, Makoto Yoshikawa, Satoshi Tanaka, Sei-ichiro Watanabe, Yuichi Tsuda, Masahiko Arakawa
    Advances in Space Research, May, 2024  
  • Moe Matsuoka, Ei-ichi Kagawa, Kana Amano, Tomoki Nakamura, Eri Tatsumi, Takahito Osawa, Takahiro Hiroi, Ralph Milliken, Deborah Domingue, Driss Takir, Rosario Brunetto, Antonella Barucci, Kohei Kitazato, Seiji Sugita, Yuri Fujioka, Osamu Sasaki, Shiho Kobayashi, Takahiro Iwata, Tomokatsu Morota, Yasuhiro Yokota, Toru Kouyama, Rie Honda, Shingo Kameda, Yuichiro Cho, Kazuo Yoshioka, Hirotaka Sawada, Masahiko Hayakawa, Naoya Sakatani, Manabu Yamada, Hidehiko Suzuki, Chikatoshi Honda, Kazunori Ogawa, Kei Shirai, Cateline Lantz, Stefano Rubino, Hisayoshi Yurimoto, Takaaki Noguchi, Ryuji Okazaki, Hikaru Yabuta, Hiroshi Naraoka, Kanako Sakamoto, Shogo Tachibana, Toru Yada, Masahiro Nishimura, Aiko Nakato, Akiko Miyazaki, Kasumi Yogata, Masanao Abe, Tatsuaki Okada, Tomohiro Usui, Makoto Yoshikawa, Takanao Saiki, Satoshi Tanaka, Fuyuto Terui, Satoru Nakazawa, Sei-ichiro Watanabe, Yuichi Tsuda
    Communications Earth & Environment, 4(1), Sep 27, 2023  Peer-reviewed
    Abstract Returned samples from Cb-type asteroid (162173) Ryugu exhibit very dark spectra in visible and near-infrared ranges, generally consistent with the Hayabusa2 observations. A critical difference is that a structural water absorption of hydrous silicates is around twice as deep in the returned samples compared with those of Ryugu’s surface, suggesting Ryugu surface is more dehydrated. Here we use laboratory experiments data to indicate the spectral differences between returned samples and asteroid surface are best explained if Ryugu surface has (1) higher porosity, (2) larger particle size, and (3) more space-weathered condition, with the last being the most effective. On Ryugu, space weathering by micrometeoroid bombardments promoting dehydration seem to be more effective than that by solar-wind implantation. Extremely homogeneous spectra of the Ryugu’s global surface is in contrast with the heterogeneous S-type asteroid (25143) Itokawa’s spectra, which suggests space weathering has proceeded more rapidly on Cb-type asteroids than S-type asteroids.
  • Kohji Tsumura, Shuji Matsuura, Kei Sano, Takahiro Iwata, Hajime Yano, Kohei Kitazato, Kohji Takimoto, Manabu Yamada, Tomokatsu Morota, Toru Kouyama, Masahiko Hayakawa, Yasuhiro Yokota, Eri Tatsumi, Moe Matsuoka, Naoya Sakatani, Rie Honda, Shingo Kameda, Hidehiko Suzuki, Yuichiro Cho, Kazuo Yoshioka, Kazunori Ogawa, Kei Shirai, Hirotaka Sawada, Seiji Sugita
    Earth, Planets and Space, 75(1), Aug 22, 2023  Peer-reviewed
    Abstract Zodiacal light (ZL) is sunlight scattered by interplanetary dust particles (IDPs) at optical wavelengths. The spatial distribution of IDPs in the Solar System may hold an important key to understanding the evolution of the Solar System and material transportation within it. The number density of IDPs can be expressed as $$n(r) \sim r^{-\alpha }$$, and the exponent $$\alpha \sim 1.3$$ was obtained by previous observations from interplanetary space by Helios 1/2 and Pioneer 10/11 in the 1970s and 1980s. However, no direct measurements of $$\alpha $$ based on ZL observations from interplanetary space outside Earth’s orbit have been performed since then. Here, we introduce initial results for the radial profile of the ZL at optical wavelengths observed over the range 0.76$$-$$1.06 au by ONC-T aboard the Hayabusa2# mission in 2021-2022. The ZL brightness we obtained is well reproduced by a model brightness, although there is a small excess of the observed ZL brightness over the model brightness at around 0.9 au. The radial power-law index we obtained is $$\alpha = 1.30 \pm 0.08$$, which is consistent with previous results based on ZL observations. The dominant source of uncertainty arises from the uncertainty in estimating the diffuse Galactic light (DGL). Graphical Abstract
  • Manabu Yamada, Toru Kouyama, Koki Yumoto, Eri Tatsumi, Naofumi Takaki, Yasuhiro Yokota, Tomokatsu Morota, Naoya Sakatani, Masahiko Hayakawa, Moe Matsuoka, Rie Honda, Chikatoshi Honda, Shingo Kameda, Hidehiko Suzuki, Yuichiro Cho, Kazuo Yoshioka, Kazunori Ogawa, Kei Shirai, Hirotaka Sawada, Seiji Sugita
    Earth, Planets and Space, 75(1), Mar 13, 2023  Peer-reviewed
    After delivering its sample capsule to Earth, the Hayabusa2 spacecraft started its extended mission to perform a flyby of asteroid 2001 CC21 in 2026 and rendezvous with asteroid 1998 KY26 in 2031. During the extended mission, the optical navigation camera (ONC) of Hayabusa2 will play an important role in navigation and science observations, but it has suffered from optical deterioration after the spacecraft's surface contact with and sampling of asteroid Ryugu. Furthermore, the sensitivity of the telescopic camera (ONC-T) has continued to decrease for more than a year, posing a serious problem for the extended mission. These are problems that could potentially be encountered by other sample-return missions involving surface contact. In this study, we evaluated the long-term variation of ONC performance over the 6.5 years following the launch in 2014 to predict how it will perform during observations of the two target asteroids in its extended mission (6 and 11 years from the Earth return, respectively). Our results showed several important long-term trends in ONC performance, such as transmission, dark noise level, and hot pixels. During the long cruising period of the extended mission, we plan to observe both zodiacal light and exoplanet transits as additional science targets. The accuracy of these observations is sensitive to background noise level and stray-light contamination, so we conducted new test observations to search for the lowest stray light, which has been found to depend on spacecraft attitude. The results of these analyses and new test observations suggest that the Hayabusa2 ONC will be able to conduct cruising, flyby, and rendezvous observations of asteroids with sufficient accuracy.

Misc.

 55
  • 津村耕司, 松浦周二, 佐野圭, 岩田隆浩, 岩田隆浩, 矢野創, 矢野創, 北里宏平, 瀧本幸司, 山田学, 諸田智克, 神山徹, 早川雅彦, 横田康弘, 巽瑛理, 松岡萌, 坂谷尚哉, 本田理恵, 亀田真吾, 鈴木秀彦, 長勇一郎, 吉岡和夫, 小川和律, 白井慶, 澤田弘崇, 杉田精司, 杉田精司
    日本惑星科学会秋季講演会予稿集(Web), 2023, 2023  
  • 佐々木晶, 神田志穂, 菊地紘, 道上達広, 諸田智克, 本田親寿, 宮本英昭, 逸見良道, 杉田精司, 巽瑛理, 渡邊誠一郎, 竝木則行, 平林正稔, 平田成, 中村智樹, 野口高明, 廣井孝弘, 松本晃治, 野田寛大, 坂谷尚哉, 亀田真吾, 神山徹, 鈴木秀彦, 山田学, 本田理恵, 横田康弘, 長勇一郎, 吉岡和夫, 早川雅彦, 松岡萌, 金丸仁明, 澤田弘崇, 吉川真
    日本惑星科学会秋季講演会予稿集(Web), 2020, 2020  
  • 嶌生有理, 荒川政彦, 佐伯孝尚, 門野敏彦, 高木靖彦, 和田浩二, 飯島祐一, 今村裕志, 岡本千里, 白井慶, 中澤暁, 早川雅彦, 平田成, 矢野創
    衝撃波シンポジウム講演論文集(CD-ROM), 2019, 2020  
  • 和田浩二, 石橋高, 木村宏, 荒川政彦, 澤田弘崇, 小川和律, 白井慶, 本田理恵, 飯島祐一, 門野敏彦, 坂谷尚哉, 三桝裕也, 戸田知朗, 嶌生有理, 中澤暁, 早川基, 佐伯孝尚, 高木靖彦, 今村裕志, 岡本千里, 早川雅彦, 平田成, 矢野創
    日本惑星科学会秋季講演会予稿集(Web), 2019, 2019  
  • 荒川政彦, 佐伯孝尚, 門野敏彦, 高木靖彦, 和田浩二, 飯島祐一, 今村裕志, 岡本千里, 嶌生有理, 白井慶, 中澤暁, 早川雅彦, 平田成, 矢野創, 澤田弘崇, 小川和律, 石橋高, 木村宏, 小林正規, 坂谷尚哉, 早川基, 本田理恵, 杉田精司, 諸田智克, 亀田真吾, 巽瑛理, 本田親寿, 横田康弘, 神山徹, 山田学, 鈴木秀彦, 吉岡和夫, 長勇一郎, 松岡萌
    日本惑星科学会秋季講演会予稿集(Web), 2019, 2019  
  • 杉田精司, 巽瑛理, 長谷川直, 鈴木雄大, 上吉原弘明, 本田理恵, 亀田真吾, 諸田智克, 本田親寿, 神山徹, 山田学, 早川雅彦, 横田康弘, 坂谷尚哉, 鈴木秀彦, 小川和律, 澤田弘崇
    日本地球惑星科学連合大会予稿集(Web), 2018, 2018  
  • SHIMAKI Yuri, WADA Koji, SHIRAI Kei, ARAKAWA Masahiko, KADONO Toshihiko, ISHIBASHI Ko, KIMURA Hiroshi, TAKAGI Yasuhiko, HIRATA Naru, HAYAKAWA Masahiko, MOROTA Tomokatsu, TATSUMI Eri, KANAMARU Masanori, SAKATANI Naoya, KAMEDA Shingo, SUGITA Seiji, MICHIKAMI Tatsuhiro, TANAKA Satoshi, MIURA Akira, YAMAGUCHI Tomohiro, YAMADA Manabu, HONDA Rie, YOKOTA Yasuhiro, NAKAMURA Tomoki, SAWADA Hirotaka, OGAWA Kazunori, SAIKI Takanao, YAMAMOTO Yukio, SENSHU Hiroki, NOGUCHI Takaaki, WATANABE Sei-ichiro
    日本地球惑星科学連合大会予稿集(Web), 2018, 2018  
  • 白石浩章, 白井慶, 石原吉明, 早川雅彦, 水野貴秀, 後藤健, 尾崎正伸, 山田和彦, 田中智, 山田竜平, 及川純, 村上英記
    日本火山学会講演予稿集, 2017 43, Sep 21, 2017  
  • Suzuki Hidehiko, Yamada Manabu, Kouyama Toru, Tatsumi Eri, Kameda Shingo, Honda Rie, Sawada Hirotaka, Ogawa Naoko, Morota Tomokatsu, Honda Chikatoshi, Sakatani Naoya, Hayakawa Masahiko, Yokota Yasuhiro, Yamamoto Yukio, Sugita Seiji
    Aug, 2017  
    50th ISAS Lunar and Planetary Symposium (August 3-4, 2017. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
  • 村上 英記, 小林 直樹, 白石 浩章, 田中 智, 早川 雅彦, 後藤 健, 石原 吉明, 山田 竜平, 川村 太一, 月内部構造探査WG
    日本惑星科学会秋期講演会予稿集, 2014 "P2-36", Sep 10, 2014  
  • ARAKAWA MASAHIKO, WADA KOJI, はやぶさ2 SCI, DCAM3チーム
    遊・星・人: 日本惑星科学会誌, 22(3) 152-158, Sep, 2013  Peer-reviewedInvited
  • 佐伯孝尚, 今村裕志, 澤田弘崇, 早川雅彦, 白井慶, 荒川政彦, 門野敏彦, 高木靖彦, 和田浩二, 小川和律
    宇宙科学技術連合講演会講演集(CD-ROM), 57th, 2013  
  • Abstracts Fall Meeting of the Japanese Society for Planetary Sciences, 2012 19-19, Oct 24, 2012  
  • 佐伯孝尚, 今村裕志, 澤田弘崇, 早川雅彦, 白井慶, 荒川政彦, 門野敏彦, 高木靖彦, 和田浩二
    宇宙科学技術連合講演会講演集(CD-ROM), 56th, 2012  
  • 荒川政彦, 門野敏彦, 高木靖彦, 和田浩二, 平田成, 小林正規, 本田理恵, 白井慶, 早川雅彦, 岡本千里, 小川和律, 矢野創, 中澤暁, 飯島祐一, 佐伯孝尚, 今村裕志, 澤田弘崇
    日本惑星科学会秋季講演会予稿集(Web), 2012, 2012  
  • 村上 英記, 田中 智, 小林 直樹, 白石 浩章, 早川 雅彦, 山田 竜平, 石原 靖, 岡元 太郎, 竹内 希, 早川 基, 月内部構造探査WG
    日本惑星科学会秋期講演会予稿集, 2011 128-128, Oct 23, 2011  
  • 山田 竜平, 白石 浩章, 竹内 希, 小林 直樹, 田中 智, 村上 英記, 石原 靖, 岡元 太郎, 早川 雅彦, 早川 基, Garcia Raphael, Lognonne Philippe
    日本惑星科学会秋期講演会予稿集, 2011 49-49, Oct 23, 2011  
  • KOBAYASHI N., SHIRAISHI H., MURAKAMI H., TAKEUCHI N., OKAMOTO T., KUGE K., YAMADA R., OGAWA K., KAKUMA H., ISHIHARA Y., ARAKI E., ZAO D., IIJIMA Y., KAWAMURA T., SHIRAI K., HAYAKAWA M., FUJIMURA A., YAMADA I.
    2011 17-17, Sep 5, 2011  
  • Lunar Planet. Sci., XXXII, 1495-1496, 2001  
  • S Tanaka, S Yoshida, M Hayakawa, A Fujimura, H Mizutani
    PROCEEDINGS OF THE FOURTH INTERNATIONAL CONFERENCE ON EXPLORATION AND UTILISATION OF THE MOON, 462 187-190, 2000  
    We developed a numerical thermal model of the LUNAR-A penetrator. To make this model precise, we performed two types of experiments. One was to measure thermal conductivity (K) and the heat capacity (Cp) for each component of the penetrator. We successfully obtained these data within 10% in precision. The other was to perform a thermal response experiment for a fully integrated penetrator. With this experiment, we calibrated an initial thermal model which was constructed from the component level data. By inverting the data of the thermal response experiment, we could obtain a final thermal model which is consistent with the component level data and the thermal response experiment as a whole. Numerical simulations of the temperature Field around the penetrator in the lunar regolith indicate that the uncertainty of the thermal model leads to the error of estimating the original temperature gradient of the regolith within 6%.
  • H Mizutani, A Fujimura, M Hayakawa, S Tanaka, H Shiraishi, S Yoshida
    PROCEEDINGS OF THE FOURTH INTERNATIONAL CONFERENCE ON EXPLORATION AND UTILISATION OF THE MOON, 462 107-114, 2000  
    The Japanese lunar penetrator mission, LUNAR-A, is planned to be launched in February 2003. This mission aims to study the lunar interior by using seismometers and heat flow probes on board the lunar penetrators. Two penetrators will be deployed on the lunar surface; one on the nearside, and another on the farside. The seismic study will be made by observing various deep moonquakes at two widely different penetrator sites. fin particular, observations of the amplitudes and travel-times of nearside deep moonquake events at the farside station will reveal core size of the moon, if it exists. Heat flow experiments are also made at two sites in order to better constrain the average lunar heat flow. Obtaining the new data on the core size and the average lunar heat now are crucial to understand the bulk abundance of the siderophile and refractory elements, which in turn are essential to understand the origin of the moon.
  • Proceeding of International Workshop on Penetrometry in the Solar System, 125-136, 2000  
  • Hiroaki SHIRAISHI, Satoshi TANAKA, Masahiko HAYAKAWA, Akio FUJIMURA, Hiroshi MIZUTANI
    The Institute of Space and Astronautical Science report, 677 1-21, 2000  
    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.
  • H Mizutani, A Fujimura, M Hayakawa, S Tanaka, H Shiraishi, S Yoshida
    PROCEEDINGS OF THE FOURTH INTERNATIONAL CONFERENCE ON EXPLORATION AND UTILISATION OF THE MOON, 462 107-114, 2000  
    The Japanese lunar penetrator mission, LUNAR-A, is planned to be launched in February 2003. This mission aims to study the lunar interior by using seismometers and heat flow probes on board the lunar penetrators. Two penetrators will be deployed on the lunar surface; one on the nearside, and another on the farside. The seismic study will be made by observing various deep moonquakes at two widely different penetrator sites. fin particular, observations of the amplitudes and travel-times of nearside deep moonquake events at the farside station will reveal core size of the moon, if it exists. Heat flow experiments are also made at two sites in order to better constrain the average lunar heat flow. Obtaining the new data on the core size and the average lunar heat now are crucial to understand the bulk abundance of the siderophile and refractory elements, which in turn are essential to understand the origin of the moon.
  • Proceeding of International Workshop on Penetrometry in the Solar System, 125-136, 2000  
  • Hiroaki SHIRAISHI, Satoshi TANAKA, Masahiko HAYAKAWA, Akio FUJIMURA, Hiroshi MIZUTANI
    Inst. Space Astron. Sci. Rep. No.677, 677 1-21, 2000  
    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.
  • Yoshida Shinsuke, Tanaka Satoshi, Hourai Kiichi, Mizutani Hitoshi, Fujimura Akio, Hayakawa Masahiko, Hirai Ken'ichi
    Abstracts Fall Meeting of the Japanese Society for Planetary Sciences, 1999 34-34, Nov 13, 1999  
  • S Tanaka, S Yoshida, M Hayakawa, K Horai, A Fujimura, H Mizutani
    MOON AND MARS, 23(11) 1825-1828, 1999  
    Lunar heat flow experiment is planned by using two LUNAR-A penetrators which will be deployed on the near-side and far-side of the lunar surface in 2000. Each penetrator has seven absolute and eleven relative temperature sensors. Impact experiments for real-size penetrator models onto a lunar-regolith analogue target confirmed that the sensors and electronics used in the Lunar-A Heat Flow Experiment can survive the shock loading expected during penetration of the penetrator in a lunar regolith. The calibration experiment demonstrates that the temperature sensors have a resolution of 0.01 degrees and that the thermal conductivity device have 10 % accuracy. In order to determine the heat flow value, we need a good thermal model and numerical simulation for the penetrator and the regolith which in turn requires accurate measurements of thermal properties of the penetrator's components. The current numerical models indicate that we will be able to obtain the lunar heat flow values within 20 to 30 percents in precision with this method. (C) 1999 COSPAR. Published by Elsevier Science Ltd.
  • S Tanaka, S Yoshida, M Hayakawa, K Horai, A Fujimura, H Mizutani
    MOON AND MARS, 23(11) 1825-1828, 1999  
    Lunar heat flow experiment is planned by using two LUNAR-A penetrators which will be deployed on the near-side and far-side of the lunar surface in 2000. Each penetrator has seven absolute and eleven relative temperature sensors. Impact experiments for real-size penetrator models onto a lunar-regolith analogue target confirmed that the sensors and electronics used in the Lunar-A Heat Flow Experiment can survive the shock loading expected during penetration of the penetrator in a lunar regolith. The calibration experiment demonstrates that the temperature sensors have a resolution of 0.01 degrees and that the thermal conductivity device have 10 % accuracy. In order to determine the heat flow value, we need a good thermal model and numerical simulation for the penetrator and the regolith which in turn requires accurate measurements of thermal properties of the penetrator's components. The current numerical models indicate that we will be able to obtain the lunar heat flow values within 20 to 30 percents in precision with this method. (C) 1999 COSPAR. Published by Elsevier Science Ltd.
  • Yoshida Shinsuke, Tanaka Satoshi, Hourai Kiichi, Mizutani Hitoshi, Fujimura Akio, Hayakawa Masahiko, Hirai Ken'ichi
    Abstracts Fall Meeting of the Japanese Society for Planetary Sciences, 1998 53-53, Oct 13, 1998  
  • MIZUTANI Hitoshi, FUJIMURAZ Akio, HAYAKAWA Masahiko, TANAKA Satoshi, SHIRAISHI Hiroaki
    Journal of the Japan Society of Precision Engineering, 63(10) 1346-1350, 1997  
  • Hayakawa M., Shiraishi H., Tanaka S., Iijima Y., Fujimura A., Mizutani H., Yamada I., Koyama J., Murakami H., Ishihara Y., Ito K., Suda N., LUNAR-A Penetrator Science Group
    Abstracts Fall Meeting of the Japanese Society for Planetary Sciences, 1996 58-58, Oct 2, 1996  
  • Shiraishi H., Tanaka S., Hayakawa M., Fujimura A., Ishii N., Mizutani H., LUNAR-A Penetrator Group
    Abstracts Fall Meeting of the Japanese Society for Planetary Sciences, 1996 59-59, Oct 2, 1996  
  • 田中智, 水谷仁, 藤村彰夫, 宝来帰一, 早川雅彦, 安部正真, 白石浩章, 平井研一
    日本惑星科学会秋季講演会予稿集, 1996 60, Oct, 1996  
  • SHIRAISHI H., TANAKA S., HAYAKAWA M., FUJIMURA A., MIZUTANI H.
    Abstracts Fall Meeting of the Japanese Society for Planetary Sciences, 1995 205-205, Nov 13, 1995  
    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.
  • 田中智, 水谷仁, 藤村彰夫, 早川雅彦, 安部正真, 宝来帰一, 平井研一
    日本惑星科学会秋季講演会予稿集, 1995 16, Nov, 1995  
  • 早川雅彦, 岡田達明, 春山純一, 水谷仁
    太陽系科学シンポジウム, 16th(1994), 1995  
  • 水谷仁, 藤村彰夫, 早川雅彦, 田中智, 安部正真, 荒木博志, 白石浩章, 山田功夫
    科学衛星・宇宙観測シンポジウム, 3rd 224-227, Oct, 1994  
  • 田中智, 宝来帰一, 安部正真, 荒木博志, 早川雅彦, 藤村彰夫, 水谷仁
    科学衛星・宇宙観測シンポジウム, 2nd 198-201, Oct, 1993  
  • K SHIBUYA, M KASAHARA, M HAYAKAWA, A FUJIMURA, J KOYAMA, K KAMIMUMA, H MIZUTANI
    JOURNAL OF PHYSICS OF THE EARTH, 41(5) 291-304, 1993  
    In order to study the effectiveness of GPS (Global Positioning System) differential positioning for the deployed Antarctic penetrator, we made fall tests by changing the release altitude at 160, 330, 680, and 1,000 m above the ground. A two-blade helicopter equipped with a Trimble GPS Pathfinder was used in the experiment at the Aoyama Pasture, Hokkaido, in April 1991. As compared with the precise location (0.1 m accuracy) determined by the GPS doubly differenced phase analysis, post-processed 1 min (less than 60 data points during PDOP<10) average of the helicopter hovering GPS differential navigation data was accurate to 10 m for a horizontal location (hovering method). By knowing the release time to an accuracy of 1 s, the impact location can be predicted by tracing the falling trajectory (trajectory method). Thus estimated position was accurate to 30 m against the precise location. As for a height accuracy, there was an error of +/- 10 m in the hovering method. This error further degraded to +/- 20 m when the coordinates of the reference site were replaced by a time-average (1-2 h duration) of the point-positioning results. The above obtained positioning accuracies are enough for a long-range (300 km profile) seismic explosion experiments of each 5-10 km station separation, because the associated errors result only in 0.2% uncertainty on the estimate of P-wave velocity structures.
  • K SHIBUYA, M KASAHARA, M HAYAKAWA, A FUJIMURA, J KOYAMA, K KAMIMUMA, H MIZUTANI
    JOURNAL OF PHYSICS OF THE EARTH, 41(5) 291-304, 1993  
    In order to study the effectiveness of GPS (Global Positioning System) differential positioning for the deployed Antarctic penetrator, we made fall tests by changing the release altitude at 160, 330, 680, and 1,000 m above the ground. A two-blade helicopter equipped with a Trimble GPS Pathfinder was used in the experiment at the Aoyama Pasture, Hokkaido, in April 1991. As compared with the precise location (0.1 m accuracy) determined by the GPS doubly differenced phase analysis, post-processed 1 min (less than 60 data points during PDOP<10) average of the helicopter hovering GPS differential navigation data was accurate to 10 m for a horizontal location (hovering method). By knowing the release time to an accuracy of 1 s, the impact location can be predicted by tracing the falling trajectory (trajectory method). Thus estimated position was accurate to 30 m against the precise location. As for a height accuracy, there was an error of +/- 10 m in the hovering method. This error further degraded to +/- 20 m when the coordinates of the reference site were replaced by a time-average (1-2 h duration) of the point-positioning results. The above obtained positioning accuracies are enough for a long-range (300 km profile) seismic explosion experiments of each 5-10 km station separation, because the associated errors result only in 0.2% uncertainty on the estimate of P-wave velocity structures.
  • 田中智, 宝来帰一, 水谷仁, 藤村彰夫, 早川雅彦, 荒木博志, 安部正真
    科学衛星・宇宙観測シンポジウム, 1992 229-233, Nov, 1992  
  • KAWAKAMI Shin-ichi, KANAORI Yuji, HAYAKAWA Masahiko
    Journal of the Geological Society of Japan, 96(4) 297-381, 1990  
  • Jour. Geol. Soc. Japan, 96, 297-381, 1990  

Books and Other Publications

 2

Presentations

 217

Professional Memberships

 3

Research Projects

 10