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  2. KAZUTAKA NISHIYAMA

KAZUTAKA NISHIYAMA

  (西山 和孝)

Profile Information

Affiliation
Professor, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
Degree
博士（工学）(Mar, 1998, 東京大学)
Researcher number
60342622
ORCID ID
 https://orcid.org/0000-0002-9224-893X
J-GLOBAL ID
202001002398782568
researchmap Member ID
R000014180
External link

Research Interests

 2

Research History

 8
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Education

 2

Committee Memberships

 6
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Awards

 1

Papers

 290
  • Shuichi Sato, Seiji Kawamura, Masaki Ando, Takashi Nakamura, Kimio Tsubono, Akito Araya, Ikkoh Funaki, Kunihito Ioka, Nobuyuki Kanda, Shigenori Moriwaki, Mitsuru Musha, Kazuhiro Nakazawa, Kenji Numata, Shin Ichiro Sakai, Naoki Seto, Takeshi Takashima, Takahiro Tanaka, Kazuhiro Agatsuma, Koh Suke Aoyanagi, Koji Arai, Hideki Asada, Yoichi Aso, Takeshi Chiba, Toshikazu Ebisuzaki, Yumiko Ejiri, Motohiro Enoki, Yoshiharu Eriguchi, Masa Katsu Fujimoto, Ryuichi Fujita, Mitsuhiro Fukushima, Toshifumi Futamase, Katsuhiko Ganzu, Tomohiro Harada, Tatsuaki Hashimoto, Kazuhiro Hayama, Wataru Hikida, Yoshiaki Himemoto, Hisashi Hirabayashi, Takashi Hiramatsu, Feng Lei Hong, Hideyuki Horisawa, Mizuhiko Hosokawa, Kiyotomo Ichiki, Takeshi Ikegami, Kaiki TInoue, Koji Ishidoshiro, Hideki Ishihara, Takehiko Ishikawa, Hideharu Ishizaki, Hiroyuki Ito, Yousuke Itoh, Nobuki Kawashima, Fumiko Kawazoe, Kishimoto Naoko, Kenta Kiuchi, Shiho Kobayashi, Kazunori Kohri, Hiroyuki Koizumi, Yasufumi Kojima, Keiko Kokeyama, Wataru Kokuyama, Kei Kotake, Yoshihide Kozai, Hideaki Kudoh, Hiroo Kunimori, Hitoshi Kuninaka, Kazuaki Kuroda, Kei Ichi Maeda, Hideo Matsuhara, Yasushi Mino, Osamu Miyakawa, Shinji Miyoki, Mutsuko YMorimoto, Tomoko Morioka, Toshiyuki Morisawa, Shinji Mukohyama, Shigeo Nagano, Isao Naito, Kouji Nakamura, Hiroyuki Nakano, Kenichi Nakao, Shinichi Nakasuka, Yoshinori Nakayama, Erina Nishida, Kazutaka Nishiyama, Atsushi Nishizawa, Yoshito Niwa, Taiga Noumi, Yoshiyuki Obuchi, Masatake Ohashi, Naoko Ohishi, Masashi Ohkawa, Norio Okada, Kouji Onozato, Kenichi Oohara, Norichika Sago, Motoyuki Saijo, Masaaki Sakagami, Shihori Sakata, Misao Sasaki
    Journal of Physics: Conference Series, 154, 2009  
  • S. Hosoda, T. Ogawa, H. Kuninaka, K. Nishiyama, Y. Shimizu
    47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2009  
  • Hitoshi Kuninaka, Kazutaka Nishiyama, Jun'ichiro Kawaguchi, Ken'ichi Shirakawa, Masatoshi Matsuoka
    60th International Astronautical Congress 2009, IAC 2009, 2 1323-1330, 2009  
  • Yasuhiro Kawakatsu, Hitoshi Kuninakat, Kazutaka Nishiyama
    Advances in the Astronautical Sciences, 134 801-812, 2009  
  • Kazutaka Nishiyama, Hitoshi Kuninaka
    60th International Astronautical Congress 2009, IAC 2009, 7 5741-5747, 2009  Lead author
  • 西山和孝
    宇宙航空研究開発機構特別資料 JAXA-SP-, (08-013), 2009  Lead author
  • 小川卓哉, 細田聡史, 國中均, 西山和孝, 山極芳樹
    宇宙科学技術連合講演会講演集(CD-ROM), 53rd, 2009  
  • 西山和孝
    航空原動機・宇宙推進講演会講演論文集(CD-ROM), 49th, 2009  Lead author
  • 豊田康裕, 西山和孝, 國中均
    航空原動機・宇宙推進講演会講演論文集(CD-ROM), 49th, 2009  
  • 細田聡史, 小川卓哉, 國中均, 西山和孝
    航空原動機・宇宙推進講演会講演論文集(CD-ROM), 49th, 2009  
  • Kazutaka Nishiyama, Hitoshi Kuninaka
    Surface and Coatings Technology, 202(22-23) 5262-5265, Aug 30, 2008  Peer-reviewedLead author
  • S. Kawamura, M. Ando, T. Nakamura, K. Tsubono, T. Tanaka, I. Funaki, N. Seto, K. Numata, S. Sato, K. Ioka, N. Kanda, T. Takashima, K. Agatsuma, T. Akutsu, T. Akutsu, K. S. Aoyanagi, K. Arai, Y. Arase, A. Araya, H. Asada, Y. Aso, T. Chiba, T. Ebisuzaki, M. Enoki, Y. Eriguchi, M. K. Fujimoto, R. Fujita, M. Fukushima, T. Futamase, K. Ganzu, T. Harada, T. Hashimoto, K. Hayama, W. Hikida, Y. Himemoto, H. Hirabayashi, T. Hiramatsu, F. L. Hong, H. Horisawa, M. Hosokawa, K. Ichiki, T. Ikegami, K. T. Inoue, K. Ishidoshiro, H. Ishihara, T. Ishikawa, H. Ishizaki, H. Ito, Y. Itoh, S. Kamagasako, N. Kawashima, F. Kawazoe, H. Kirihara, N. Kishimoto, K. Kiuchi, S. Kobayashi, K. Kohri, H. Koizumi, Y. Kojima, K. Kokeyama, W. Kokuyama, K. Kotake, Y. Kozai, H. Kudoh, H. Kunimori, H. Kuninaka, K. Kuroda, K. I. Maeda, H. Matsuhara, Y. Mino, O. Miyakawa, S. Miyoki, Y. Morimoto, T. Morioka, T. Morisawa, S. Moriwaki, S. Mukohyama, M. Musha, S. Nagano, I. Naito, N. Nakagawa, K. Nakamura, H. Nakano, K. Nakao, S. Nakasuka, Y. Nakayama, E. Nishida, K. Nishiyama, A. Nishizawa, Y. Niwa, M. Ohashi, N. Ohishi, M. Ohkawa, A. Okutomi, K. Onozato, K. Oohara, N. Sago, M. Saijo, M. Sakagami, S. I. Sakai
    Journal of Physics: Conference Series, 122(Part 3) 2393-2397, 2008  
  • M. Ando, S. Kawamura, T. Nakamura, K. Tsubono, T. Tanaka, I. Funaki, N. Seto, K. Numata, S. Sato, K. Ioka, N. Kanda, T. Takashima, K. Agatsuma, T. Akutsu, T. Akutsu, K. S. Aoyanagi, K. Arai, Y. Arase, A. Araya, H. Asada, Y. Aso, T. Chiba, T. Ebisuzaki, M. Enoki, Y. Eriguchi, M. K. Fujimoto, R. Fujita, M. Fukushima, T. Futamase, K. Ganzu, T. Harada, T. Hashimoto, K. Hayama, W. Hikida, Y. Himemoto, H. Hirabayashi, T. Hiramatsu, F. L. Hong, H. Horisawa, M. Hosokawa, K. Ichiki, T. Ikegami, K. T. Inoue, K. Ishidoshiro, H. Ishihara, T. Ishikawa, H. Ishizaki, H. Ito, Y. Itoh, S. Kamagasako, N. Kawashima, F. Kawazoe, H. Kirihara, N. Kishimoto, K. Kiuchi, S. Kobayashi, K. Kohri, H. Koizumi, Y. Koima, K. Kokeyama, W. Kokuyama, K. Kotake, Y. Kozai, H. Kudoh, H. Kunimori, H. Kuninaka, K. Kuroda, K. I. Maeda, H. Matsuhara, Y. Mino, O. Miyakawa, S. Miyoki, M. Y. Morimoto, T. Morioka, T. Morisawa, S. Moriwaki, S. Mukohyama, M. Musha, S. Nagano, I. Naito, N. Nakagawa, K. Nakamura, H. Nakano, K. Nakao, S. Nakasuka, Y. Nakayama, E. Nishida, K. Nishiyama, A. Nishizawa, Y. Niwa, M. Ohashi, N. Ohishi, M. Ohkawa, A. Okutomi, K. Onozato, K. Oohara, N. Sago, M. Saijo, M. Sakagami, S. I. Sakai
    Journal of Physics: Conference Series, 120(Part 3), Jan 1, 2008  
  • Kazutaka Nishiyama, Satoshi Hosoda, Yukio Shimizu, Hitoshi Kuninaka, Ryudo Tsukizaki
    44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2008  Lead author
  • Yasuhiro Toyoda, Kazutaka Nishiyama, Satoshi Hosoda, Yukio Shimizu, Hitoshi Kuninaka
    44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2008  Lead author
  • 月崎竜童, 西山和孝, 細田聡史, 小泉宏之, 清水幸夫, 國中均
    宇宙科学技術連合講演会講演集(CD-ROM), 52nd, 2008  
  • 豊田康裕, 西山和孝, 清水幸夫, 國中均
    宇宙科学技術連合講演会講演集(CD-ROM), 52nd, 2008  
  • 國中均, 西山和孝
    アストロダイナミクスシンポジウム講演後刷り集(Web), 17th, 2008  
  • HAYASHI Hiroshi, USUI Miyuki, NAKAYAMA Yoshinori, SHIMIZU Yukio, NISHIYAMA Kazutaka, KUNINAKA Hitoshi
    JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 55(647) 604-611, Dec 5, 2007  
    An ion engine with 10,000sec-class high specific impulse is expected as primary propulsion for interplanetary space mission with extremely high delta-V, and needs high voltage for ion acceleration over 10kV. The microwave discharge ion source without solid electrodes can supply sophisticated technologies and simple composition on electrical isolation for such a high voltage. New electro-static grid made of carbon-carbon composite material was fabricated based on the numerical simulation of “igx” code. The “μ10HIsp” ion engine combining the ECR ion source, microwave discharge neutralizer, DC blocks, propellant isolators, carbon-carbon composite grid and so on generated successfully a plasma beam with 10,000sec specific impulse using 15kV acceleration voltage.
  • Kazutaka Nishiyama, Yukio Shimizu, Ikkoh Funaki, Hitoshi Kuninaka, Kyoichiro Toki
    JOURNAL OF PROPULSION AND POWER, 23(3) 513-521, May, 2007  Peer-reviewedLead author
  • Hitoshi Kuninaka, Kazutaka Nishiyama, Yukio Shimizu, Satoshi Hosoda, Hiroyuki Koizumi, Ju N.Ichiro Kawaguchi
    Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2 1885-1891, 2007  
  • Y. Sakamoto, H. Kuninaka, Y. Shimizu, K. Nishiyama
    Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting, 22 15409-15413, 2007  
  • Miyuki Usui, Kazutaka Nishiyama, Hitoshi Kuninaka
    Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 3 2894-2905, 2007  
  • 豊田康裕, 西山和孝, 清水幸夫, 國中均
    宇宙科学技術連合講演会講演集(CD-ROM), 51st, 2007  
  • 西山和孝, 豊田康裕, 國中均
    宇宙科学技術連合講演会講演集(CD-ROM), 51st, 2007  Lead author
  • Hitoshi Kuninaka, Kazutaka Nishiyama, Ikko Funaki, Tetsuya Yamada, Yukio Shimizu, Ju N.Ichiro Kawaguchi
    Journal of Propulsion and Power, 23(3) 544-551, 2007  Peer-reviewed
  • Hitoshi Kuninaka, Kazutaka Nishiyama, Ikko Funaki, Yukio Shimizu, Tetsuya Yamada, Jun'ichiro Kawaguchi
    IEEE Transactions on Plasma Science, 34(5 II) 2125-2132, Oct, 2006  Peer-reviewed
  • Kazutaka Nishiyama, Hitoshi Kuninaka
    Thin Solid Films, 506-507 588-591, May 26, 2006  Peer-reviewedLead author
  • Sachiko Sugimoto, Hitoshi Kuninaka, Kazutaka Nishiyama, Yusuke Sakamoto
    Journal of Geophysical Research: Space Physics, 111(4), Apr, 2006  Peer-reviewed
  • Nakai Tatsuya, Miyamoto Takashi, Nishiyama Kazutaka, Kuninaka Hitoshi
    宇宙航空研究開発機構特別資料 JAXA-SP-, (5) 82-86, Feb 28, 2006  
    Along with the development of microwave discharge ion engines, it is necessary that a analysis model of the ion sources is developed. As the first stage, probe measurements of the ion source of micro 20, which is under the development now, were done. In the discharge chamber of micro 20, it is expected that a certain circumferential distribution is exist because of the magnetic field and the gas ports in the discharge chamber. In this research, we got the distribution between inside magnet rows, which indicated an increase in electron temperatures and a decrease in plasma densities along the direction of the Delta B drift of electrons. Moreover, it is found that electron temperatures and plasma densities change in two different cases of the locations of the gas ports. These results show that the best shape of the discharge chamber can improve the performance improvement of micro 20.
  • KUNINAKA Hitoshi, NISHIYAMA Kazutaka, FUNAKI Ikko, YAMADA Tetsuya, SHIMIZU Yukio, KAWAGUCHI Jun′ichiro
    The Journal of Space Technology and Science, 22(1) 1_1-1_10, 2006  
    The microwave discharge ion engine “μ10” has a long life and high reliability because of electrodeless plasma generation in both the ion generator and the neutralizer. A single μ10 generates a thrust of 8 mN, specific impulse of 3,200 seconds, and consuming 350 W of electric power. Four μ10s propelled the “Hayabusa” asteroid explorer, launched on May 2003, combining a new orbit change scheme “Delta-V Earth Gravity Assist”. In 2005, Hayabusa, using solar electric propulsion, managed to successfully cover the distance between 0.86 AU and 1.7 AU from Sun in the solar system, as well as rendezvous with, land on, and lift off from the asteroid Itokawa. During the 2-year flight, the ion engine system generated a delta-V of 1,400 m/s while consuming 22 kg of xenon propellant and operating for 25,800 hours. Hayabusa solved failures of reaction wheels and chemical thrusters by means of xenon cold gas jet from the ion engine system and aims to return to Earth in 2010.
  • Hitoshi Kuninaka, Kazutaka Nishiyama, Ikko Funaki, Tetsuya Yamada, Yukio Shimizu, Jun'ichiro Kawaguchi
    Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference, 1 151-164, 2006  
  • Kazutaka Nishiyama, Ryoichi Kikuchi, Hitoshi Kuninaka, Haruki Takegahara
    AIAA 57th International Astronautical Congress, IAC 2006, 10 6765-6770, 2006  Lead author
  • Tatsuya Nakai, Kazutaka Nishiyama, Hitoshi Kuninaka
    AIAA 57th International Astronautical Congress, IAC 2006, 9 6321-6327, 2006  
  • Kazutaka Nishiyama, Tatsuya Nakai, Hitoshi Kuninaka
    Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference, 10 8160-8171, 2006  
  • Kuninaka Hitoshi, Nishiyama Kazutaka, Funaki Ikko, Shimizu Yukio, Yamada Tetsuya
    (5) 12-18, Aug 1, 2005  
    The microwave discharge ion engines 'micro10s' are devoted to the main propulsion on 'HAYABUSA' asteroid explorer. In the development program various kinds of tests and assessments were applied to the ion engines and the spacecraft; the endurance test, the EMI susceptibility test, the interference test between plasma and communication microwave, the beam exhaust test on the spacecraft, the assessment on plasma interference with solar array, so on. The spacecraft was input in the deep space by M-V rocket on May 9, 2003. After vacuum exposure and several runs of baking for reduction of residual gas the ion engine system established the continuous acceleration of the spacecraft toward the asteroid 'ITOKAWA'. On the beginning of December 2004 the ion engines reached the total number of space operational time 20,000 hour. And the spacecraft passed by the aphelion 1.7 astronautical unit on February 18, 2005 so that the microwave discharge ion engine micro10s became the electric propulsion to arrive at the furthest space from Sun. It will rendezvous with the target asteroid on September 2005.
  • KUNINAKA HITOSHI, HORIUCHI YASUO, NISHIYAMA KAZUTAKA, FUNAKI IKKOH, SHIMIZU YUKIO, YAMADA TETSUYA
    Aeronautical and Space Sciences Japan, 53(618) 203-210, Jul 5, 2005  Peer-reviewed
  • 西山 和孝, 國中 均, 清水 幸夫
    宇宙科学シンポジウム, 5 491-494, Jan 6, 2005  Lead author
  • Hitoshi Kuninaka, Yukio Shimizu, Tetsuya Yamada, Ikko Funaki, Kazutaka Nishiyama
    41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2005  
  • NISHIYAMA Kazutaka
    SPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 4(4) 21-27, 2005  Peer-reviewedLead author
    A completely new solar electric propulsion concept, the Air Breathing Ion Engine (ABIE), has been proposed for spacecraft drag makeup at very low altitudes, ranging from 150 to 200 km. ABIE scoops up neutral atoms and molecules traveling at an orbital velocity of approximately 8 km/s, ionizes them by means of an electron cyclotron resonance plasma source that is efficient in a wide range of low gas pressures, and accelerates the ionized air particles electrostatically to exhaust velocities larger than 100 km/s. The key technology of this thruster is the design of a propellant inlet which allows the incoming flow to enter the discharge chamber, yet it prevents the thermalized gas from escaping upstream. In this system, an air-breathing-type neutralizer may also be employed, in which case the need to carry on-board xenon propellant is eliminated and results in gains in payload mass if the mission duration is longer than 2 years. This technology should give researchers access to a part of the atmosphere that is currently very difficult to measure and is thus called the "ignorosphere." Promising applications other than aeronomy include science missions involving accurate gravity and magnetic field mapping, and high-resolution Earth surveillance.
  • 西山和孝, 国中均, 福田美穂, 中村嘉宏
    宇宙科学技術連合講演会講演集(CD-ROM), 49th, 2005  Lead author
  • 宮本尚使, 西山和孝, 国中均, 中島秀紀
    宇宙科学技術連合講演会講演集(CD-ROM), 49th, 2005  
  • HAYASHI Hiroshi, CHO Mengu, NISHIYAMA Kazutaka, KUNINAKA Hitoshi
    JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 52(610) 528-534, Nov 5, 2004  Peer-reviewed
    In recent years, concern has been raised about the interference phenomena (chemical reaction, sputtering etc.) between ionospheric plasma and high-voltage space systems such as the International Space Station and so on. In order to solve the physical mechanisms of these phenomena and establish the prevention technology, it is important to accumulate experimental data based on ground simulation tests. Therefore we have developed a cathode-less microwave discharge oxygen ion source for an ionospheric plasma simulator. The oxygen ion source for ionospheric plasma simulation demands plasma density more than 1012m- 3 and high durability (our target is more than 70hours). This ion source is capable of generating oxygen plasma of the order of 1014m- 3 for more than 100hours with 25W microwave power and 3sccm oxygen gas. In order to investigate the operational performance of the oxygen ion source, we conduct various measurement tests such as plasma diagnosis using a single probe, ionic mass spectroscopy by a Quadrupole Mass Spectrometer (QMS), atomic oxygen flux measurement using a silver coated QCM (Quartz Crystal deposition Monitor) and 70hours operating test etc. This paper reports the experimental results of each measurement tests and assesses performance as an ion source for ionospheric plasma simulator.
  • KUNINAKA Hitoshi, NISHIYAMA Kazutaka, SHIMIZU Yukio, TOKI Kyoichiro, KAWAGUCHI Jun'ichiro, UESUGI Kuninori
    JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 52(602) 129-134, Mar 5, 2004  Peer-reviewed
    The microwave discharge ion engine generates plasmas of the main ion source as well as the neutralizer using 4GHz microwave without discharge electrodes and hollow cathodes, so that long life and durability against oxygen and air are expected. MUSES-C “HAYABUSA” spacecraft installing four microwave discharge ion engines was launched into deep space by M-V rocket on May 9, 2003. After vacuum exposure and several runs of baking for reduction of residual gas the ion engine system established the continuous acceleration of the spacecraft toward an asteroid. The Doppler shift measurement of the communication microwave revealed the performance of ion engines, which is 8mN thrust force for a single unit with 3,200sec specific impulse at 23mN/kW thrust power ratio. At the beginning of December 2003 the accumulated operational time exceeded 7,000 hours and units.
  • Kuninaka Hitoshi, Nishiyama Kazutaka, Shimizu Yukio, Toki Kyoichiro
    (3) 27-31, Mar 1, 2004  
  • 國中 均, 西山 和孝, 清水 幸夫
    宇宙科学シンポジウム, 4 585-588, Jan 8, 2004  
  • Hitoshi Kuninaka, Kazutaka Nishiyama, Yukio Shimizu, Kyoichiro Toki
    40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2004  
  • Kazutaka Nishiyama, Hitoshi Kuninaka, Jun'ichiro Kawaguchi
    International Astronautical Federation - 55th International Astronautical Congress 2004, 1 653-662, 2004  Lead author
  • Kuninaka H., Nishiyama K., Shimizu Y., Toki K.
    Meeting Abstracts of the Physical Society of Japan, 59 233-233, 2004  
  • 国中均, 堀内康男, 船木一幸, 西山和孝, 清水幸夫, 都木恭一郎, 川口淳一郎, 上杉邦憲, 高見剛史
    日本航空宇宙学会年会講演会講演集, 35th, 2004  

Misc.

 75
  • 荒井朋子, 小林正規, 石橋高, 吉田二美, 吉田二美, 木村宏, 平井隆之, 山田学, 岡本尚也, 秋田谷洋, 千秋博紀, 和田浩二, SRAMA Ralf, KRUGER Harald, KRUGER Harald, 佐々木晶, 薮田ひかる, 石黒正晃, 渡部潤一, 伊藤孝士, 大坪貴文, 大坪貴文, 大塚勝仁, 大塚勝仁, 阿部新助, 中村智樹, 廣井孝弘, 中村メッセンジャー圭子, 小松睦美, 関口朋彦, 浦川聖太郎, 諸田智克, 紅山仁, 橘省吾, 三河内岳, 野口高明, 金田英宏, 小松吾郎, 小松吾郎, 出村裕英, 平田成, 伊藤元雄, 山口亮, 松浦周二, 巽瑛理, MARSHALL Sean, 矢野創, 吉川真, 尾崎直哉, 山本高行, 豊田裕之, 西山和孝, 今村裕志, 高島建
    日本惑星科学会秋季講演会予稿集(Web), 2024, 2024  
  • 荒井朋子, 小林正規, 石橋高, 吉田二美, 吉田二美, 木村宏, 平井隆之, 岡本尚也, Hong P. K., 山田学, 和田浩二, 千秋博紀, 秋田谷洋, SRAMA Ralf, KRUGER Harald, MARSHALL Sean, 佐々木晶, 薮田ひかる, 石黒正晃, 中村智樹, 大塚勝仁, 大塚勝仁, 渡部潤一, 伊藤孝士, 伊藤孝士, 大坪貴文, 大坪貴文, 阿部新助, 関口朋彦, 浦川聖太郎, 廣井孝弘, 紅山仁, 諸田智克, 橘省吾, 三河内岳, 松浦周二, 伊藤元雄, 山口亮, 野口高明, 中村メッセンジャー圭子, 小松睦美, 小松吾郎, 小松吾郎, 出村裕英, 平田成, 金田英宏, 柳沢俊史, 黒崎裕久, 巽瑛理, 矢野創, 吉川真, 尾崎直哉, 山本高行, 餅原義孝, 徳留真一郎, 豊田裕之, 西山和孝, 今村裕志, 高島建
    日本惑星科学会誌 遊・星・人, 33(1), 2024  
  • 太田方之, 宮原剛, 尾崎直哉, 須崎祐多, 山本高行, 岡橋隆一, 三桝裕也, 佐藤峻介, 西山和孝, 豊田裕之, 今村裕志, 高島健, 石橋高, HONG Peng, 山田学, 小林正規, 荒井朋子, 細沼貴之
    宇宙科学技術連合講演会講演集(CD-ROM), 67th, 2023  
  • 村中崇信, 加藤守, 中田圭祐, 岩頭拓海, 濃野歩, 上野一磨, 中山宜典, 西山和孝
    宇宙科学技術連合講演会講演集(CD-ROM), 67th, 2023  
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Books and Other Publications

 2

Teaching Experience

 3

Professional Memberships

 1

Research Projects

 11
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Media Coverage

 1
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