Curriculum Vitaes
Profile Information
- Affiliation
- Professor, Institute of Space and Astronautical Science, Department of Space Flight Systems, Japan Aerospace Exploration Agency(Concurrent)Project Manager, JAXA Space Exploration Center, Martian Moons Exploration Project Team
- Degree
- PhD(The University of Tokyo)
- J-GLOBAL ID
- 200901025451103270
- researchmap Member ID
- 5000092382
- External link
Research Interests
7Papers
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The Journal of the Astronautical Sciences, Jan 8, 2026
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Acta Astronautica, Dec, 2024
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The Journal of the Astronautical Sciences, Nov 15, 2024
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Space Telescopes and Instrumentation 2024: Ultraviolet to Gamma Ray, 89-89, Aug 21, 2024
Misc.
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Proceedings of the Optimization Symposium, 2014 _2109-1_-_2109-6_, 2014DESTINY is injected to long elliptical orbit by Epsilon rocket launcher. If the apogee altitude of the injected orbit is high enough, it is achieved to ease the requirements for design and operation of the spacecraft. This paper investigates the ability of trajectory injection by means of 4-stage Epsilon rocket using the method of multi objective optimization under several flight constraints.
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Proceedings of the Optimization Symposium, 2014 _1219-1_-_1219-3_, 2014"DESTINY" is an acronym of "Demonstration and Experiment of Space Technology for INterplanetary voYage", which is proposed by JAXA/ISAS as "ISAS Small Scientific Satellite" mission. In this mission, trajectory design is one an important technical element because of its many revolution low-thrust orbits with many mission objectives and constraints. Evolutionary computation is utilized to find candidates for the orbit.
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Abstracts Fall Meeting of the Japanese Society for Planetary Sciences, 2013 "P3-21", Nov 20, 2013
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57 5p, Oct 9, 2013 Peer-reviewed
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誘導制御シンポジウム資料, 30th, 2013
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Technical report of IEICE. SANE, 112(229) 239-244, Oct 3, 2012We present the overview and the current status of SPICA (Space Infrared Telescope for Cosmology and Astrophysics), which is a mission optimized for mid- and far-infrared astronomy with a cryogenically cooled 3.2m telescope. SPICA has high spatial resolution and unprecedented sensitivity in the mid- and far-infrared, which will enable us to address a number of key problems in present-day astronomy, ranging from the star-formation history of the universe to the formation of planets. To reduce the mass of the whole mission, SPICA will be launched at ambient temperature and cooled down on orbit by mechanical coolers on board with an efficient radiative cooling system, a combination of which allows us to have a 3-m class cooled (6K) telescope in space with moderate total weight (3.7t). SPICA is proposed as a Japanese-led mission together with extensive international collaboration. ESA's contribution to SPICA has been studied under the framework of the ESA Cosmic Vision. The consortium led by SRON is in charge of a key focal plane instrument SAFARI (SPICA Far-Infrared Instrument). Korea and Taiwan are also important partners for SPICA. US participation to SPICA is under discussion. The SPICA project is now in the "risk mitigation phase". The target launch year of SPICA is 2022.
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12th Space Science Symposium, P4-12B, Jan, 2012
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 10(ists28) Tk\_19-Tk\_25, 2012Since 2008, a new plan for next Mars exploration program has been proposed and discussed by scientists and engineers in Japan. This exploration program is named MELOS, or Mars Exploration with Lander and Orbiter Synergy, a long-awaited program in the planetary science community in Japan after unsuccessful end of Nozomi Mars orbiter and ongoing challenge of Akatsuki Venus orbiter. The goal of the whole program is to understand Mars as a system, by elucidation of Martian climate, atmospheric escape, internal structure, surface environment and interaction by them. A series of missions has been planned, and several spacecraft including orbiters and landers are under discussion to be launched in early 2020's. In this paper, we investigate launch opportunities during early 2020's and estimate the payload mass in each case. Feasible interplanetary transfer trajectories from Earth to Mars are proposed. Preliminary design of insertion sequence into the Mars orbit and some orbit candidates derived from mission requirements are also shown together with numerical simulation results.
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アストロダイナミクスシンポジウム講演後刷り集(Web), 20th, 2011
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Proceedings of The 20th Workshop on Astrodynamics and Flight Mechanics, 189-192, Jul, 2010
Presentations
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71st International Astronautical Congress, Oct, 2020
Research Projects
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科学研究費助成事業, 日本学術振興会, Mar, 2023 - Mar, 2024
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科学研究費助成事業, 日本学術振興会, Apr, 2022 - Mar, 2024
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科学研究費助成事業, 日本学術振興会, Nov, 2021 - Mar, 2024
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Grants-in-Aid for Scientific Research, Japan Society for the Promotion of Science, Apr, 2019 - Mar, 2021
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科学研究費助成事業, 日本学術振興会, Apr, 2014 - Mar, 2017