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
72-
Progress in Earth and Planetary Science, 12(34), May, 2025 Peer-reviewed
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IEICE TRANSACTIONS on Electronics, E108-C(5), May, 2025 Peer-reviewedLead author
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Journal of the Society for Information Display, 31(4) 158-168, 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
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Advances in Space Research, 69(5) 2283-2304, Mar 1, 2022 Peer-reviewed
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IEICE Electronics Express, 19(3) 20210518-20210518, Feb 10, 2022 Peer-reviewedLead author
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Earth, Planets and Space, 73(1), Dec, 2021 Peer-reviewed
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Earth, Planets and Space, 73(1), Dec, 2021 Peer-reviewed
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AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 20 125-133, 2021The use of phased array antenna (PAA) with a power taper in a space solar power systems requires a configuration that can be mass-produced. However, there was no conventional method of constructing a PAA with power taper, which suitable for mass production. Therefore, this paper proposes a method of constructing a PAA with a single type of amplifier and uniform spacing between antenna elements, which gradually increases the number of elements in the subarray. As a result of applying the proposed method to a 10-dB truncated Gaussian taper, the power transmission efficiency is equal to or higher than that conventional methods. In addition, the proposed method was demonstrated in experiments using a one-dimensional patch antenna array.
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Earth, Planets and Space, 72(1), Dec, 2020 Peer-reviewed
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Icarus, 114073-114073, Aug, 2020
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IEICE Electronics Express, 17(11) 20200152-20200152, Jun 10, 2020 Peer-reviewedLead author
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Science, 368(6491) 654-659, May 8, 2020 Peer-reviewed
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Journal of Aerospace Information Systems, 17(5) 248-256, May, 2020 Peer-reviewed
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Icarus, 338 113574-113574, Mar, 2020 Peer-reviewed
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Journal of The Society of Instrument and Control Engineers, 59(5) 300-304, 2020
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The Surface Roughness of 162173 Ryugu Based on the Topography from Hayabusa2 Laser Altimeter (LIDAR)51st Lunar and Planetary Science Conference (2020), (2326) 2181, 2020
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51st Lunar and Planetary Science Conference, (2326) 1829, 2020 Peer-reviewed
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 63(2) 42-49, 2020 Peer-reviewedLead author
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Science, 364(6437) eaaw0422-eaaw0422, Mar 19, 2019 Peer-reviewed
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AIAA Scitech 2019 Forum, 2019
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 17(2) 150-154, 2019 Peer-reviewed
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AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 17 89-96, 2018 Peer-reviewedLead author
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Earth, Planets and Space, 69(1), Dec 1, 2017 Peer-reviewed
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International Conference on Space Optics — ICSO 2006, Nov 21, 2017
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Space Science Reviews, 208(1-4) 65-79, Jul, 2017 Peer-reviewed
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Space Science Reviews, 208(1-4) 49-64, Jul, 2017 Peer-reviewed
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Space Science Reviews, 208(1-4) 33-47, Jul, 2017 Peer-reviewedLead author
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PROGRAMME AND ABSTRACTS THE VOLCANOLOGICAL SOCIETY OF JAPAN, 2017 43-43, 2017
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Journal of The Remote Sensing Society of Japan, 37(4) 362-368, 2017 Peer-reviewed<p>The moon and asteroids are known to be covered with dust grains. Since dust grains are thought to travel over the surface of these bodies, they are potentially hazardous for spacecraft, and especially for sample-return missions. However, dust grains detached from the surface are not easy to detect. We have provided the light detection and ranging (LIDAR) system on board Hayabusa2 with a new operational mode, the "dust count mode," in which LIDAR evaluates whether or not each return pulse from 50 continuous observational ranges exceeds a threshold value. Once Hayabusa2 arrives at its target body of Ryugu, we will make observations with various threshold values in order to detect dust distribution.</p>
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PROGRAMME AND ABSTRACTS THE VOLCANOLOGICAL SOCIETY OF JAPAN, 2016 66-66, 2016
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Proceeding of an International CJMT-1 Workshop on Asteroidal Science, 1667 74-96, 2014 Peer-reviewed
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日本航空宇宙学会誌, 60(7) 250-256, Jul, 2012 Peer-reviewedLead author
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Proceedings of the International Astronautical Congress, IAC, 5 3519-3531, 2012
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN, 10(28) Pd_101-Pd_105, 2012In recent years, LIDAR has been used in remote sensing systems, obstacle avoidance systems on planetary landers, rendezvous docking systems, and formation flight control systems. A wide dynamic range is necessary for LIDAR systems on planetary landers and in rendezvous docking systems. For example, a dynamic range of 60 dB was required for the receiving system used in the Hayabusa mission in order to measure distances between 50 m and 50 km. In addition, an obstacle detection and avoidance system of a planetary lander requires a ranging resolution of better than 10 cm. For planetary landers, ISAS/JAXA is developing a customized integrated circuit (IC) for LIDAR reception. This report introduces the design of the customized IC and reports the results of preliminary experiments evaluating the prototype, LIDARX03.
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 10(ists28) Pk_7-Pk_10, 2012 Peer-reviewed
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 10(ists28) Pd_61-Pd_66, 2012 Peer-reviewedA radar for navigation in future Japanese lunar/planetary landing missions is being developed in the Japan Aerospace Exploration Agency (JAXA). The C-band pulse radar provides not only altitude information but also relative velocity against the surface. In this paper, detailed design of a Doppler simulator for the landing radar is described. The simulation accompanied with Digital Terrain Models (DTM) is quite effective because it can analyze accuracy of the velocity measurements while taking account of terrain effects. The validity of the simulation is quantified by comparing with the results of actual field experiments. Furthermore, the performance of the landing radar over lunar terrains is evaluated by the simulation with the KAGUYA DTM products of lunar surfaces.
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IEICE Transactions on Communications, E94-B(11) 2961-2968, 2011 Peer-reviewedLead author
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2010 International Conference on Optical MEMS and Nanophotonics, Optical MEMS and Nanophotonics 2010, 111-112, 2010 Peer-reviewed
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 53(179) 47-53, 2010 Peer-reviewedLead authorHayabusa, launched in May 2003, is the first Japanese spacecraft to have explored the small asteroid Itokawa (1998SF36) and has touched down on Itokawa twice. LIDAR (LIght Detection And Ranging) technology has been developed as an important navigation sensor with the characteristics of light weight (3.7 kg) and wide dynamic range (50 km to 50 m). The performance of LIDAR was perfect in the on-orbit operation and led to Hayabusa successfully touching down on Itokawa. This paper introduces the components of the LIDAR system and discusses ranging results of the onboard operation. For hardware, this paper focuses on the laser module that provided a lot of knowledge and the receiver that is important for evaluating the ranging data. The evaluation is takes particular note of the behavior of the receiver.
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 8(ists27) Td_17-Td_22, 2010 Peer-reviewedIn recent years, LIDAR has been used in remote sensing systems, obstacle avoidance systems on planetary landers, rendezvous docking systems, and formation flight control systems. A wide dynamic range is necessary for LIDAR systems on planetary landers and in rendezvous docking systems. For example, a dynamic range of 60 dB (60dB for light, 120dB for electric signal) was required for the receiving system used in the Hayabusa mission in order to measure distances between 50 m and 50 km. In addition, rendezvous docking systems require a ranging resolution of better than 10 cm. For planetary landers and rendezvous docking systems, ISAS/JAXA is developing a customized integrated circuit (IC) for LIDAR reception. This report introduces the design of the customized IC and reports the results of preliminary experiments evaluating the prototype, LIDARX02.
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60th International Astronautical Congress 2009, IAC 2009, 2 1096-1100, 2009
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN, 7(ists26) Td_1-Td_5, 2009 Peer-reviewedLead authorThe 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. The landing radar employs a pulse-type radar using 4.3GHz C-band microwave radiation. It has a wide beam for measuring the altitude in vertical direction, as well as four narrow tilted beams for measuring the velocity in horizontal direction. 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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The proceedings of the JSME annual meeting, 2008 365-366, 2008The 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.
Misc.
114-
日本地球惑星科学連合大会予稿集(Web), 2023, 2023
Presentations
9-
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
