Curriculum Vitaes
Profile Information
- Affiliation
- Senior Researcher, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
- Degree
- 博士（工学）(Mar, 2005, 東京大学)
- Researcher number
- 60443280
- J-GLOBAL ID
- 202001000370405138
- researchmap Member ID
- R000014112
Research History
3-
Apr, 2006 - Present
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Apr, 2005 - Mar, 2006
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Apr, 1999 - Mar, 2002
Education
4-
Apr, 1997 - Mar, 1999
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Apr, 1993 - Mar, 1995
Committee Memberships
4-
Apr, 2019 - Mar, 2021
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Nov, 2014 - Aug, 2017
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Nov, 2009 - Jul, 2014
Awards
9-
Mar, 2019
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May, 2013
Papers
63-
Journal of Evolving Space Activities, 1, Dec, 2023 Peer-reviewed
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2023 62nd Annual Conference of the Society of Instrument and Control Engineers (SICE), Sep 6, 2023
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 19(2) 186-192, 2021
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Acta Astronautica, 170 206-223, May, 2020© 2019 IAA This paper investigates the launch capability of the SS-520 as a CubeSat launch vehicle. The SS-520 was developed by JAXA originally as a two-stage, spin-stabilized, solid-propellant sounding rocket. With less than 2.6 tons in total mass and 10 m in length, the SS-520-5 successfully launched a single 3U-sized CubeSat into orbit on February 3, 2018. The SS-520-5 obtained its capability as a CubeSat launch vehicle by installing a 3rd stage solid motor in addition to the RCS between the 1st and 2nd stages. However, its launch capability was limited due to its rocket system configuration. In order to pursue the SS-520's launch capability, two effective modifications from the SS-520-5 are proposed: thrust enhancement of the 1st stage motor and installation of an additional RCS between the 2nd and 3rd stages. The framework of launch capability analysis is established by a multi-objective genetic algorithm (MOGA), where its two objectives are selected as the altitudes of perigee and apogee. The analysis reveals that the two proposed modifications to the SS-520-5 work effectively but differently. The 10% increase of the 1st stage enhancement is particularly effective when the target altitude of perigee is low (e.g., 200 km), whereas the installment of the additional RCS with 30 kg increases accessibility to a much higher altitude of perigee, even to circular orbit reaching altitudes of 550 km for a 1U-sized CubeSat and 280 km for a 6U-sized CubeSat. The simultaneous application of both modifications would result in launch capability able to deliver a 10-kg payload. From a more general perspective, the results in this paper suggest that it is possible for a very small launch vehicle (VSLV) of the 3-ton class and 10 m in length to deliver a 10-kg-class payload into low Earth orbit.
Misc.
58-
観測ロケットシンポジウム2020 講演集 = Proceedings of Sounding Rocket Symposium 2020, Mar, 20213rd Sounding Rocket Symposium (March 24-25, 2021. Online Meeting)
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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), 63rd, 2019
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平成30年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2018, Jan, 2019平成30年度宇宙輸送シンポジウム（2019年1月17日-18日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県資料番号: SA6000136091レポート番号: STEP-2018-036
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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), 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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航空原動機・宇宙推進講演会講演論文集(CD-ROM), 57th, 2017
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Jan, 2017Space Transportation Symposium FY2016 (January 19-20, 2017. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
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Aeronautical and Space Sciences Japan, 63(5) 148-154, 2015
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Aug, 201447th ISAS Lunar and Planetary Symposium (August 4-6, 2014. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
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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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平成24年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium: FY2012, Jan, 2013平成24年度宇宙輸送シンポジウム (2013年1月17日-1月18日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県 Space Transportation FY2012 (January 17-18, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan 形態: カラー図版あり 形態: PDF 著者人数: 18名 Physical characteristics: Original contains color illustrations Physical characteristics: PDF Number of authors: 18 Translation title: High frequency reusable launch vehicle system: Realtime rocket enjine health check monitoring using FDIR 資料番号: AA0061856051 レポート番号: STCP-2012-051
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Aeronautical and Space Sciences Japan, 60(8) 283-289, 2012
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Aeronautical and Space Sciences Japan, 60(10) 357-363, 2012
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AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, 11 123-129, 2012The performance of tank devices, such as porous metals and a metal fiber, on liquid propellant retention was evaluated under microgravity environment. IKAROS carries the gas-liquid equilibrium propulsion system which stores propellant as liquid phase in a storage tank and expels only gaseous propellant from the tank. Surface tension in pores of tank devices holds liquid propellant in them. As a result of microgravity experiments, it was found that the performance on liquid retention is higher than that estimated from results of bubble point experiment, and it strongly depends on the existence of bubbles in liquid propellant. From the results of the experiment, this paper proposes the location of porous metals in the storage tank to prevent bubbles from remaining with propellant consumption.
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The Proceedings of Mechanical Engineering Congress, Japan, 2011 _J191063-1-_J191063-5, 2011Japan 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.
