Curriculum Vitaes
Profile Information
- Affiliation
- Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
- Degree
- (BLANK)(Yokohama National University)
- J-GLOBAL ID
- 200901026954630207
- researchmap Member ID
- 1000363037
月惑星や小惑星を探査する際に必要とされる
光や電波を使った『距離を測る技術』をテーマとして
ハードウェアの研究開発を中心に
実際のプロジェクトに非常に近いところから将来の要素技術まで
幅広く研究を行っています
光や電波を使った『距離を測る技術』をテーマとして
ハードウェアの研究開発を中心に
実際のプロジェクトに非常に近いところから将来の要素技術まで
幅広く研究を行っています
Research Interests
5Research Areas
2Research History
6-
May, 1993 - Dec, 1993
Education
3-
Apr, 1988 - Mar, 1993
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Apr, 1984 - Mar, 1988
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- Mar, 1980
Committee Memberships
1-
Apr, 2015 - Mar, 2017
Awards
5-
Sep, 2017
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Apr, 2014
Papers
69-
Journal of the Society for Information Display, Mar 1, 2023 Peer-reviewedInvitedLead authorCorresponding author
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Advances in Space Research, Jan, 2023 Peer-reviewed
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Earth, Planets and Space, 74(1), Nov 8, 2022 Peer-reviewedAbstract Japanese asteroid explorer Hayabusa2 arrived at C-type asteroid 162,173 Ryugu in June 2018. The laser altimeter (LIDAR) onboard Hayabusa2 measured its own transmitted laser and returned pulse intensities from a Ryugu surface until November 2019. Because the Ryugu surface is extremely rough, topography dominates over the material properties in the conventional derivation of normal albedo. Thus, we developed a method to retrieve the normal albedo from the rough surface of a C-type asteroid at a LIDAR laser wavelength of 1.064 μm. The albedo map covering an equatorial band between – 40° and + 20° in latitude was created with 3˚-by-3˚ resolution using the intensity data obtained before the conjunction of the spacecraft with the Sun. The average of the normal albedo is 0.0405 $$\pm$$ 0.0027, whereas approximately half of the 3°-by-3° grids are between 0.04 and 0.045. The low and uniform normal albedo feature is common to other remote-sensing observations of Ryugu by visible and near-infrared cameras onboard Hayabusa2. Graphical Abstract
Misc.
113-
宇宙科学技術連合講演会講演集(CD-ROM), 64th, 2020
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宇宙科学技術連合講演会講演集(CD-ROM), 62nd, 2018
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宇宙科学技術連合講演会講演集(CD-ROM), 61st, 2017
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電子情報通信学会技術研究報告, 115(447(SANE2015 107-115)), 2016
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電子情報通信学会技術研究報告, 116(115(SANE2016 10-20)), 2016
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Technical report of IEICE. SANE, 114(448) 25-30, Feb 18, 2015A high-speed downlink communication system is required to meet various applications for nano/small satellites. Therefore, it is essential to implement a transmitter with small weight and power in such satellites. We have developed high speed communication system over 300 Mbps for small satellite. In order to reduce DC power consumption of transmitter, we have developed GaN-HEMT power amplifier for X band downlink. The Hodoyoshi-4 satellite equipped with the developed communication system was launched in 2014 and we demonstrated 348 Mbps downlink from 50-kg class satellite. This paper describes the summary of the developed system, the experiment of high speed downlink, and future works.
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Technical report of IEICE. SAT, 114(449) 43-48, Feb 18, 2015A high-speed downlink communication system is required to meet various applications for nano/small satellites. Therefore, it is essential to implement a transmitter with small weight and power in such satellites. We have developed high speed communication system over 300 Mbps for small satellite. In order to reduce DC power consumption of transmitter, we have developed GaN-HEMT power amplifier for X band downlink. The Hodoyoshi-4 satellite equipped with the developed communication system was launched in 2014 and we demonstrated 348 Mbps downlink from 50-kg class satellite. This paper describes the summary of the developed system, the experiment of high speed downlink, and future works.
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電子情報通信学会技術研究報告, 115(67(SANE2015 6-15)), 2015
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Technical report of IEICE. SANE, 114(264) 11-16, Oct 22, 2014A high-speed downlink communications system is required to meet various applications for nano/small satellites. It is essential to implement a transmitter with small weight and power in such satellites. We have developed a compact 348Mbps transmitter incorporating a powerful error correction on ground station receiver. This system has been demonstrated a high-speed down link communication system at "Hodoyoshi-4" satellite with 50 kg mass.
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Technical report of IEICE. SANE, 114(48) 37-42, May 23, 2014Recently small satellites play important roles in earth observations with medium resolution. This purpose requires a small earth station which is equipped with S band up/down satellite operation functions as well as with X band high data rate reception functions. We have developed a small earth station with a 3.8 m antenna and evaluated them with relatively low cost. This paper describes the cost-effective test method and the results.
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Technical report of IEICE. SANE, 112(17) 47-51, Apr 19, 2012We review the current status and future plans in laser ranging from/to the Earth to a Japanese planetary mission Hayabusa-2. A limited hardware on board and experimental windows being given, configuration of ranging two-way, one-way up/down link assuming station capable of 1 micron ranging is considered from the perspective of accuracy, detection probability. Issues with the requirements of the specifications and required as a ground station request ,as well as international cooperation station for the angle measurement will be discussed.
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Proceedings of the IEICE General Conference, 2012(2) 119-119, Mar 6, 2012
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Technical report of IEICE. SANE, 111(239) 17-22, Oct 10, 2011A high-speed downlink communication system is required to meet different applications for nano/small satellites. Therefore, it is essential to implement a power- and weight-limited transmitter in such satellites. Our recent research has focused on an efficient system adopting CCSDS 131.0-R signaling formats with the limited transmitter incorporating a powerful ground station receiver. To overcome signal distortion at the cost of some limitations of the transmitter, an SCCC turbo equalization system equipped with nonlinear distortion compensation techniques in the receiver has been developed. We simulate the system using practical distortion models to determine the performances of BER and synchronization.
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Proceedings of the Society Conference of IEICE, 2011(1) 253-253, Aug 30, 2011
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Proceedings of the IEICE General Conference, 2011(2) 125-125, Feb 28, 2011
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Proceedings of the IEICE General Conference, 2011(1) 259-259, Feb 28, 2011
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IEICE technical report, 110(308) 25-30, Nov 19, 2010In recent years, small/nano satellites have been developed by universities and companies to utilize space environments. A high speed downlink communication system for small/nano satellites is required to realize different kind of applications. We have developed the effective system which is adopted a low complexity satellite transmitter incorporating a powerful earth station receiver. To overcome same distortions due to the low complexity, turbo equalization is essential for the receiver. We then developed a nonlinear distortion compensation and a blind converge detector for the turbo equalization. This paper presents the concept of the communication system, the principle of these techniques, and the simulation results.
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Proceedings of the IEICE General Conference, 2010(2) 98-98, Mar 2, 2010
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2009(18) 63-65, Jan 28, 2010The Institute of Space and Astronautical Science JAXA is developing a landing radar comprising a radio altimeter and a velocity meter, which are two of the mandatory navigation sensors for a planetary Lander. A BBM of the landing radar has been evaluated on natural terrains by using a helicopter. This paper introduces the BBM hardware and discusses the dynamic performance in field experiments.
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Proceedings of the IEICE General Conference, 2009(1) 309-309, Mar 4, 2009
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Proceedings of the IEICE General Conference, 2009(1) 275-275, Mar 4, 2009
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Proceedings of the IEICE General Conference, 2009(1) 274-274, Mar 4, 2009
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IEICE technical report, 108(267) 47-51, Oct 24, 2008For scientific observation using a lunar and a planetary lander, a pinpoint landing technology whose ambiguity is less than 100m must be needed for landing system. A landing radar that measures an altitude and velocity of a space craft with microwave is very important navigation sensor to realize the pinpoint landing. It is a mandatory sensor for any future missions of planetary landing. This report describes the poroblems of the landing radar BBM in short range measurement.
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Proceedings of the Society Conference of IEICE, 227-227, 2008
Presentations
8-
The 30th International Display Workshops, Dec 7, 2023 Invited
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The 28th International Display Workshops, Dec 2, 2021 Invited
Teaching Experience
1-
宇宙電波応用工学 (総合研究大学院大学物理科学研究科宇宙科学専攻)
Research Projects
23-
科学研究費助成事業, 日本学術振興会, Apr, 2019 - Mar, 2023
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イノベーションハブ構築支援事業, 科学技術振興機構, Oct, 2016 - Sep, 2019
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Grants-in-Aid for Scientific Research, Japan Society for the Promotion of Science, Apr, 2015 - Mar, 2018
