Curriculum Vitaes
Profile Information
- Affiliation
- Professor, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
- Degree
- Ph.D.(Mar, 2005, The University of Tokyo)
- J-GLOBAL ID
- 200901090793977023
- researchmap Member ID
- 5000092383
Research Interests
5Research History
4-
Feb, 2007 - Jun, 2009
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Apr, 2005 - Jan, 2007
Education
3-
Apr, 1996 - Mar, 1998
Committee Memberships
5-
Apr, 2023 - Present
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May, 2021 - Apr, 2023
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May, 2016 - Jul, 2017
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Nov, 2015 - Jul, 2017
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Oct, 2013 - Jul, 2015
Awards
25-
Apr, 2023
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Nov, 2021
Papers
250-
Acta Astronautica, Dec, 2025
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Acta Astronautica, Oct, 2025 Peer-reviewedLead authorCorresponding author
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Science Advances, 10(39), Sep 27, 2024The isotopic compositions of samples returned from Cb-type asteroid Ryugu and Ivuna-type (CI) chondrites are distinct from other carbonaceous chondrites, which has led to the suggestion that Ryugu/CI chondrites formed in a different region of the accretion disk, possibly around the orbits of Uranus and Neptune. We show that, like for Fe, Ryugu and CI chondrites also have indistinguishable Ni isotope anomalies, which differ from those of other carbonaceous chondrites. We propose that this unique Fe and Ni isotopic composition reflects different accretion efficiencies of small FeNi metal grains among the carbonaceous chondrite parent bodies. The CI chondrites incorporated these grains more efficiently, possibly because they formed at the end of the disk’s lifetime, when planetesimal formation was also triggered by photoevaporation of the disk. Isotopic variations among carbonaceous chondrites may thus reflect fractionation of distinct dust components from a common reservoir, implying CI chondrites/Ryugu may have formed in the same region of the accretion disk as other carbonaceous chondrites.
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Nature Communications, 15 7488, Aug 29, 2024 Peer-reviewedAbstract Primordial carbon delivered to the early earth by asteroids and meteorites provided a diverse source of extraterrestrial organics from pre-existing simple organic compounds, complex solar-irradiated macromolecules, and macromolecules from extended hydrothermal processing. Surface regolith collected by the Hayabusa2 spacecraft from the carbon-rich asteroid 162173 Ryugu present a unique opportunity to untangle the sources and processing history of carbonaceous matter. Here we show carbonaceous grains in Ryugu can be classified into three main populations defined by spectral shape: Highly aromatic (HA), Alkyl-Aromatic (AA), and IOM-like (IL). These carbon populations may be related to primordial chemistry, since C and N isotopic compositions vary between the three groups. Diffuse carbon is occasionally dominated by molecular carbonate preferentially associated with coarse-grained phyllosilicate minerals. Compared to related carbonaceous meteorites, the greater diversity of organic functional chemistry in Ryugu indicate the pristine condition of these asteroid samples.
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Space Telescopes and Instrumentation 2024: Optical, Infrared, and Millimeter Wave, 213-213, Aug 23, 2024
Misc.
210-
Advances in the Astronautical Sciences, 148 2059-2071, 2013
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Planetary People, 21(3) 247-252, Sep, 2012 Peer-reviewed
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Journal of the Japan Society for Simulation Technology, 31(2) 105-109, Jun 15, 2012
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Proceedings of the International Astronautical Congress, IAC, 3 1654-1659, 2012
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Advances in the Astronautical Sciences, 142 3547-3560, 2012
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Advances in the Astronautical Sciences, 142 1737-1754, 2012
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Advances in the Astronautical Sciences, 142 1319-1331, 2012
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Planetary People - The Japanese Society for Planetary Sciences, 21(3) 247-252, 2012
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Proceedings of The 21st Workshop on Astrodynamics and Flight Mechanics, Jul, 2011
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Advances in the Astronautical Sciences, 140 147-161, 2011
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62nd International Astronautical Congress 2011, IAC 2011, 2 1343-1348, 2011
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The Proceedings of Mechanical Engineering Congress, Japan, 2011 _J191063-1-_J191063-5, 2011 Peer-reviewedJapan Aerospace Exploration Agency (JAXA) successfully achieved the world's first solar power sail technology by IKAROS (Interplanetary Kite-craft Accelerated by Radiation Of the Sun) mission in 2010. It demonstrated a photon propulsion and thin film solar power generation during its interplanetary cruise. The 200m2-span sail was deployed and kept extended by centrifugal force of the spacecraft rotation. IKAROS also succeeded in accelerating and controlling the orbit by actively exploiting solar radiation pressure, and thus became the world's first actual solar sailer flying an interplanetary voyage. This paper presents the design of IKAROS solar sail system, operation results and introduces a perspective of this new technology to apply to the next generation mission toward Jupiter and Trojan asteroids.
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IEICE technical report, 110(250) 155-160, Oct 20, 2010The Japan Aerospace Exploration Agency (JAXA) makes the world's first solar power sail craft IKAROS demonstration of photon propulsion and thin film solar power generation during its interplanetary cruise. The spacecraft deploys and spans a membrane of 20 meters in diameter using the spin centrifugal force. It also deploys thin film solar cells on the membrane, in order to evaluate its thermal control property and anti-radiation performance in the real operational field. The spacecraft weighs approximately 310kg, launched together with the agency's Venus Climate Orbiter, AKATSUKI on May 21, 2010. This paper presents the summary of development and operation of IKAROS.
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JAXA research and development report, 9(09-007) 73-84, Mar, 2010The Japan Aerospace Exploration Agency (JAXA) will make the solar power sail craft demonstrate for both its photon propulsion and thin film solar power generation during its interplanetary cruise. The spacecraft deploys and spans its membrane taking the advantage of the spin centrifugal force. The deployment system of large membrane was developed. The overall deployment experiment of solar power sail using a balloon was planned. However the balloon was not launched due to the bad weather. In this paper, the contents and significance of the experiment are reported.
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61st International Astronautical Congress 2010, IAC 2010, 12 10379-10386, 2010
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61st International Astronautical Congress 2010, IAC 2010, 6 4720-4725, 2010 Peer-reviewed
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IEICE technical report, 107(2) 19-24, Apr 9, 2007Miniature space GPS receivers have been developed by means of automobile-navigation technology. We expanded the frequency sweep range in order to cover large Doppler shift on orbit. The GPS receiver was modified to output pseudorange data with accurate time tag. We tested the performance in low earth orbits by means of a GPS simulator. The range error caused by the receiver is measured to be 1 meter. The position accuracy is estimated to be less than 17 meters (rms) in the low earth orbits. This GPS receiver was on-boarded on INDEX satellite, which launched in 2005. Cold start positioning was confirmed repeatedly to finish within 30 minutes on orbit. The orbit determination was performed to evaluate the random position error of GPS receiver by means of the residual error. The random error of GPS position is as large as 2 meter for PDDP=2 on orbit. These results on orbit are consistent with the simulation results in use of a GPS simulator.
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(6) 27-34, Mar 30, 2007Miniature space GPS (Global Positioning System) receivers have been developed by means of automobile-navigation technology. The weight and power consumption of the GPS receiver are 35 g and 1 W, respectively. We expanded the frequency sweep range in order to cover large Doppler shift in orbit. We tested the performance in low earth orbits by means of a GPS simulator. The GSP receiver succeeded in cold start acquisition in less than 30 minutes. This GPS receiver was on-boarded on INDEX satellite launched in August 2005. The performances of cold start acquisition and position accuracy was verified in orbit.
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宇宙航空研究開発機構特別資料 JAXA-SP-, (06-015), 2007
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IEICE technical report, 106(217) 17-22, Aug 18, 2006Miniature space GPS receivers have been developed by means of automobile-navigation technology. The weight and power consumption of the GPS receiver are 35g and 1W, respectively. We expanded the frequency sweep range in order to cover large Doppler shift in orbit. We tested the performance in low earth orbits by means of a GPS simulator. The GSP receiver succeeded in cold start acquisition in less than 30 minutes. This GPS receiver was on-boarded on INDEX satellite launched in August 2005. The performances of cold start acquisition and position accuracy was verified in orbit.
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Proceedings of the IEICE General Conference, 2006(1) "SE-11"-"SE-12", Mar 8, 2006
Books and Other Publications
2Presentations
2Professional Memberships
1-
Apr, 2005 - Present
Research Projects
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科学研究費助成事業, 日本学術振興会, Apr, 2024 - Mar, 2028
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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, 2019 - Mar, 2024
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Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (C), Japan Society for the Promotion of Science, Apr, 2018 - Mar, 2021
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Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B), Japan Society for the Promotion of Science, Apr, 2016 - Mar, 2019
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Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B), Japan Society for the Promotion of Science, Apr, 2014 - Mar, 2018
