Profile Information
- Affiliation
- Professor, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
- Degree
- Doctor of Philosophy(The University of Tokyo)Master of Engineering(The University of Tokyo)
- J-GLOBAL ID
- 200901060615181820
- researchmap Member ID
- 1000144472
- External link
Research Interests
8Research Areas
3Research History
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2010 - 2017
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2007 - 2010
Education
4Committee Memberships
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2017 - Present
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2008 - Present
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2006 - Present
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2003 - Present
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1998 - Present
Awards
3Papers
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Advances in the Astronautical Sciences, 171 3903-3918, 2020© 2020, Univelt Inc. All rights reserved. ISAS/JAXA has successfully launched the micro-satellite “TRICOM-1R” by the world’s smallest orbit rocket “SS-520 No.5” from Uchinoura Space Center on February 3rd in 2018. ISAS modified the existing sounding rocket SS-520 adding a small 3rd-stage solid-motor and the attitude control system. It flies spinning for the attitude stabilization in the flight. Therefore, we devised the rhumb-line control system with a new scheme. This rhumb-line system has the high-performance functions; the high-preciseness, the high-maneuver rate and the suppression of the unnecessary nutation angle generated at the RCS injection. This paper reports the development of the G&C system and the flight results.
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Advances in the Astronautical Sciences, 156 2063-2073, 2016The first Epsilon rocket was launched successfully with a small payload 'HISAKI' on September 14th, 2013 in Japan. Epsilon has a new absorber structure in Payload Attach Fitting to reduce the vibration condition for payload. We designed the robust control logic to satisfy the compatibility of robust stability and response against various disturbances. The 3rd Stage under spinning has a Rhumb-line Control function which reduces the pointing error at separation and ignition of solid motor. We could insert the payload into the orbit precisely by 'LVIC' guidance, suitable for low thrust propulsion in Post Boost Stage. We will present the flight results of the Guidance & Control (G&C) system and dynamics of Epsilon rocket.
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Aeronautical and Space Sciences Japan, 63(5) 148-154, 2015
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JOURNAL OF THE JAPAN WELDING SOCIETY, 83(3) 215-219, 2014
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Proceedings of the International Astronautical Congress, IAC, 11 8242-8248, 2013The Epsilon launch vehicle, the newest version of Japan's solid propulsion rocket, has successfully had its maiden flight in this September carrying the extreme ultra-violet planetary telescope satellite SPRINT- A. It should be emphasized that the JAXA appreciates the advantages of combined power of the standardized small satellites and the Epsilon's highly efficient launch system, both developed by JAXA, to increase the level of space activities. Although the launch site of the Epsilon rocket, the Uchinoura Space Center (USC), was originally considered a highly compact launch complex, some modifications were made to become more efficient. The efficient launch vehicle and the compact USC established one of the most powerful tools that contribute to small missions (tentatively, maximum 1.2 ton into LEO and 450kg into SSO, as of the first flight). The purpose of the Epsilon rocket is to provide small satellites with a responsive launching, which means in this study we focus on a low cost, user friendly and ultimately efficient launch system. To realize this, the design concept of the Epsilon involves various innovative next generation technologies such as the highly intelligent autonomous checkout system and the mobile launch control. Owing to these endeavors, it was proved that the lift-off can be executed in less than 6 days after the first stage motor stand-on although the first flight took longer for extra tests and operations to complete the entire development. Another aspect that small satellites will most welcome is more user-friendly character involving: A reduction in the acoustic vibration level by refined ground facilities an attenuation of the sinusoidal vibration environment by a special vibration attenuator and a highly accurate orbit injection by a liquid propelled upper stage. Their effectiveness was well demonstrated. Now that the first flight was finished, the most important is what the next step will be in the future. JAXA has been conducting intensive researches on a next generation Epsilon to launch a more powerful and lower cost version Epsilon (El) in 2017 (TBD). In order to minimize the level of technical risks, JAXA plans to take a step by step approach to improve the cost and performance of the launch system toward El. According to this strategy, the second flight will be conducted in 2015 with an enhanced launch capacity of more than 500kg into SSO. This paper provides the results of the first flight of the Epsilon and reveals its evolution plan. Copyright© (2013) by the International Astronautical Federation.
Misc.
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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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Advances in the Astronautical Sciences, 166 233-241, 2018© 2018 Univelt Inc. All rights reserved. The Epsilon launch vehicle, the newest version of Japan’s solid propulsion rocket, made its maiden flight in September of 2013. The purpose of the Epsilon launch vehicle is to provide small satellites with responsive launching with low-cost, user-friendly and efficient launch system. The first flight was successfully finished, JAXA has been conducting intensive researches on a more powerful and lower cost version of Epsilon. In order to minimize technical risks and to keep up with demand of future payloads, JAXA plans to take a step-by-step approach toward Future Launch System. As the first upgrade toward Future Launch System, JAXA has started the development of the Enhanced Epsilon. This development is mainly the renewal of the second stage, and also includes each subsystem’s improvement. This paper describes the development and flight result of the Enhanced Epsilon’s Guidance and Control System.
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Aeronautical and Space Sciences Japan, 63(8) 265-272, 2015
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, 12(29) Tg_21-Tg_28, 2014The development of the Epsilon launch vehicle, Japan's next generation solid rocket launcher, has just moved to the final stretch for its first launch scheduled in the summer of 2013 to carry the planetary telescope satellite SPRINT-A. The JAXA appreciates the advantages of combined benefits of the standardized small satellites and the Epsilon's highly efficient launch system in order to increase the level of space activities. The primary purpose of Epsilon is to provide small satellites with a responsive launch that means "Small, Low cost, Fast and Reliable". The attention should be directed toward the innovative design concept of Epsilon, which aims at developing the next generation technologies such as the highly intelligent autonomous checkout system and the mobile launch control. Now that the full-scale development is about to be finished, the most important is what the next step should be beyond the Epsilon. This paper deals with the significance of the Epsilon launch vehicle and how it contributes to the possible evolution of future space transportation systems.
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平成25年度宇宙輸送シンポジウム: 講演集録 = Proceedings of Space Transportation Symposium FY2013, 2014平成25年度宇宙輸送シンポジウム(2014年1月16日-17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: SA6000016009レポート番号: STCP-2013-009
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Aeronautical and Space Sciences Japan, 59(695) 371-377, 2011
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ACTA ASTRONAUTICA, 62(1) 1-8, Jan, 2008The M-V launch vehicle of Japan Aerospace Exploration Agency (JAXA) has successfully injected Japan's fifth X-ray space telescope "SUZAKU" into its low earth orbit in this past July. The attitude and vibration control algorithm of the M-V rocket used to be highlighted by its H-infinity robust stability since its first flight conducted in 1997. Beyond this, its robustness character has been further enhanced using the mu-synthesis approach to get better robust characteristics not only in stability but in tracking performance under uncertainty of the system dynamics. The performance has been validated by the latest back-to-back successful flights of the vehicle: in May 2003 to directly inject Japan's first asteroid sample return spaceship "HAYABUSA" into the planned inter-planetary trajectory and in this past July to launch the telescope. The mu-synthesis has been applied for the first time ever for Japan's launcher control beyond the reliable H-infinity design. The plant dynamics has an extremely high-order and unstable characteristics, thus the standard mu-synthesis format cannot be directly applied. The paper gives a unique methodology to apply the theory to such a real high-order complicated system. (c) 2007 Elsevier Ltd. All rights reserved.
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ACTA ASTRONAUTICA, 62(1) 1-8, Jan, 2008The M-V launch vehicle of Japan Aerospace Exploration Agency (JAXA) has successfully injected Japan's fifth X-ray space telescope "SUZAKU" into its low earth orbit in this past July. The attitude and vibration control algorithm of the M-V rocket used to be highlighted by its H-infinity robust stability since its first flight conducted in 1997. Beyond this, its robustness character has been further enhanced using the mu-synthesis approach to get better robust characteristics not only in stability but in tracking performance under uncertainty of the system dynamics. The performance has been validated by the latest back-to-back successful flights of the vehicle: in May 2003 to directly inject Japan's first asteroid sample return spaceship "HAYABUSA" into the planned inter-planetary trajectory and in this past July to launch the telescope. The mu-synthesis has been applied for the first time ever for Japan's launcher control beyond the reliable H-infinity design. The plant dynamics has an extremely high-order and unstable characteristics, thus the standard mu-synthesis format cannot be directly applied. The paper gives a unique methodology to apply the theory to such a real high-order complicated system. (c) 2007 Elsevier Ltd. All rights reserved.
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宇宙科学技術連合講演会講演集(CD-ROM), 51st, 2007
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宇宙科学技術連合講演会講演集(CD-ROM), 51st 2C09, 2007
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JOURNAL OF VIBRATION AND CONTROL, 10(9) 1243-1254, Sep, 2004This paper presents a methodology for applying mu-synthesis to a real high-order system: launch vehicle attitude and vibration control. The design involves robust characteristics against uncertainties of the system parameters as well as precise tracking performance under limited rigidity. As the plant dynamics has an extremely high order and unstable character, the standard mu-synthesis cannot be directly applied. Thus, the standard procedure is modified in a special way in order to make the approach more efficient. The methodology provided in the study will contribute to a better understanding of how to apply the robust control theory to complicated real problems.
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JVC/Journal of Vibration and Control, 10(9) 1243-1254, Sep, 2004This paper presents a methodology for applying μ-synthesis to a real high-order system: launch vehicle attitude and vibration control. The design involves robust characteristics against uncertainties of the system parameters as well as precise tracking performance under limited rigidity. As the plant dynamics has an extremely high order and unstable character, the standard μ-synthesis cannot be directly applied. Thus, the standard procedure is modified in a special way in order to make the approach more efficient. The methodology provided in the study will contribute to a better understanding of how to apply the robust control theory to complicated real problems.
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Proceedings of the 16th IFAC Symposium on Automatic Control in Aerospace, St.Petersburg, Russia, Printing, 2004June, 2004
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Proceedings of the 16th IFAC Symposium on Automatic Control in Aerospace, St.Petersburg, Russia, Printing, 2004June, 2004
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8TH IEEE INTERNATIONAL WORKSHOP ON ADVANCED MOTION CONTROL, PROCEEDINGS, pp, 293-298 293-298, 2004Altitude control of winged a body is realized with predictive functional controller (PFC). Although the predictive controllers are more or less in the domain of process industry, this paper proves that computational efficient PFC can be implemented on the systems with fast dynamics. The nonlinear model of winged body was written in the form of Takagi-Sugeno fuzzy model, the form that is suitable for implementation with PFC. High quality control requirements are short settle time with aperiodical step response and zero steady state error and was achieved using PFC. Predictive controller proved as a good solution.
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ACTA ASTRONAUTICA, 53(12) 971-981, Dec, 2003Despite huge amount of data collected by the previous interplanetary spacecraft and probes, the origin and evolution of the solar system still remains unveiled due to limited information they brought back. Thus, the Institute of Space and Astronautical Science (ISAS) of Japan has been given a commitment to pave the way to an asteroid sample return mission: the MUSES-C project. A key to success is considered the reentry with hyperbolic velocity, which has not ever been demonstrated as yet. With this as background, a demonstrator of atmospheric reentry system, DASH, has been designed to demonstrate the high-speed reentry technology as a GTO piggyback mission. The capsule, identical to that of the sample return mission, can experience the targeted level of thermal environment even from the GTO by tracing a specially designed reentry trajectory. After the purpose of the mission was outlined at the last IAF symposium, the final fitting tests have been conducted in the ISAS Sagamihara Campus involving the flight model hardware. Furthermore, a series of rehearsals for recovery have been already executed. The paper describes the current mission status of the project. (C) 2003 Elsevier Ltd. All rights reserved.
Books and Other Publications
2Professional Memberships
12Works
22Research 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, Japan Society for the Promotion of Science, Apr, 2019 - Mar, 2024
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Grants-in-Aid for Scientific Research, Japan Society for the Promotion of Science, Apr, 2016 - Mar, 2019
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Grants-in-Aid for Scientific Research, Japan Society for the Promotion of Science, Apr, 2013 - Mar, 2016
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Grants-in-Aid for Scientific Research, Japan Society for the Promotion of Science, 2010 - 2012
Industrial Property Rights
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特願平9-172355号
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Patent No.5, 775094 (アメリカ合衆国)
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第2716086号
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Patent No.5, 775094 (U.S.A.)