研究者業績
基本情報
- 所属
- 国立研究開発法人宇宙航空研究開発機構 宇宙科学研究所 宇宙機応用工学研究系
- 研究者番号
- 10415896
- J-GLOBAL ID
- 202001008437142898
- researchmap会員ID
- R000015178
研究キーワード
1経歴
1-
2005年4月 - 現在
論文
31-
Acta Astronautica 222 481-492 2024年9月
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Acta Astronautica 213 665-675 2023年12月
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Proceedings of the International Astronautical Congress, IAC 2023-October 2023年A 6U CubeSat “OMOTENASHI” was developed to be the world's smallest moon lander. It was launched by NASA's SLS Artemis-1 on November 16, 2022. However, because of the spacecraft anomaly, the battery was depleted and the communication with the spacecraft had been lost. After we gave up the moon landing experiment, we have been conducting a search and rescue operation till September 2023. But it was unsuccessful, unfortunately. In this article, the mission objective, the spacecraft design, the planed mission scenario, and the in-orbit operation results are presented. Additionally, lessons learned from the development and the in-orbit operation are presented.
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Active vibration suppression control for multiple mechanical coolers on board observation satellitesAIAA Scitech 2020 Forum 1 2020年This paper describes a method providing active vibration control of multiple mechanical coolers for space applications. Typical observation satellites have multiple mechanical coolers and their induced micro vibrations degrade pointing accuracy and cooler efficiency. In order to reduce such the vibration, active control is proposed. However, in the conventional control method for mechanical coolers, only considers the vibration of a single cooler and single axis has considered. Here we propose a method to simultaneously control the vibration of a satellite equipped with multiple mechanical coolers. We will discuss the condition of controllability, and actuator position and direction, and present the result of a simulation study.
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Proceedings of SPIE - The International Society for Optical Engineering 11444 2020年The X-Ray Imaging and Spectroscopy Mission (XRISM) is the successor to the 2016 Hitomi mission that ended prematurely. Like Hitomi, the primary science goals are to examine astrophysical problems with precise high-resolution X-ray spectroscopy. XRISM promises to discover new horizons in X-ray astronomy. XRISM carries a 6 x 6 pixelized X-ray micro-calorimeter on the focal plane of an X-ray mirror assembly and a co-aligned X-ray CCD camera that covers the same energy band over a large field of view. XRISM utilizes Hitomi heritage, but all designs were reviewed. The attitude and orbit control system were improved in hardware and software. The number of star sensors were increased from two to three to improve coverage and robustness in onboard attitude determination and to obtain a wider field of view sun sensor. The fault detection, isolation, and reconfiguration (FDIR) system was carefully examined and reconfigured. Together with a planned increase of ground support stations, the survivability of the spacecraft is significantly improved.
MISC
47-
大気球シンポジウム: 平成28年度 = Balloon Symposium: 2016 2016年11月大気球シンポジウム 平成28年度（2016年11月1-2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: SA6000057016レポート番号: isas16-sbs-016
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宇宙科学技術連合講演会講演集 60 6p 2016年9月
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大気球シンポジウム: 平成27年度 = Balloon Symposium: 2015 2015年11月大気球シンポジウム 平成27年度（2015年11月5-6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 Balloon Symposium 2015 (November 5-6, 2015. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan 資料番号: SA6000044007 レポート番号: isas15-sbs-007
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大気球シンポジウム: 平成26年度 = Balloon Symposium: 2014 2014年11月大気球シンポジウム 平成26年度（2014年11月6-7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 Balloon Symposium 2014 (November 6-7, 2014. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan 資料番号: SA6000021011 レポート番号: isas14-sbs-011
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大気球シンポジウム: 平成26年度 = Balloon Symposium: 2014 2014年11月大気球シンポジウム 平成26年度（2014年11月6-7日. 宇宙航空研究開発機構宇宙科学研究所 (JAXA)(ISAS)）, 相模原市, 神奈川県著者人数: 18名資料番号: SA6000021014レポート番号: isas14-sbs-014
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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 2013年1月平成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, 神奈川県形態: カラー図版あり形態: PDF資料番号: AA0061856060レポート番号: STCP-2012-060
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SPACE TELESCOPES AND INSTRUMENTATION 2010: ULTRAVIOLET TO GAMMA RAY 7732 77320Z-77320Z-18 2010年The joint JAXA/NASA ASTRO-H mission is the sixth in a series of highly successful X-ray missions initiated by the Institute of Space and Astronautical Science (ISAS). ASTRO-H will investigate the physics of the high-energy universe by performing high-resolution, high-throughput spectroscopy with moderate angular resolution. ASTRO-H covers very wide energy range from 0.3 keV to 600 keV. ASTRO-H allows a combination of wide band X-ray spectroscopy (5-80 keV) provided by multilayer coating, focusing hard X-ray mirrors and hard X-ray imaging detectors, and high energy-resolution soft X-ray spectroscopy (0.3-12 keV) provided by thin-foil X-ray optics and a micro-calorimeter array. The mission will also carry an X-ray CCD camera as a focal plane detector for a soft X-ray telescope (0.4-12 keV) and a non-focusing soft gamma-ray detector (40-600 keV). The micro-calorimeter system is developed by an international collaboration led by ISAS/JAXA and NASA. The simultaneous broad bandpass, coupled with high spectral resolution of Delta E similar to 7 eV provided by the micro-calorimeter will enable a wide variety of important science themes to be pursued.
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JASMA : Journal of the Japan Society of Microgravity Application 26(1) 9-14 2009年1月31日
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INTERNATIONAL JOURNAL OF MICROGRAVITY SCIENCE AND APPLICATION 26(1) 29-35 2009年This paper proposes control system for a new micro gravity experimental system called BOV (Balloon-based Operation Vehicle). BOV uses a free-fall capsule with double-shell structure to prevent influence of aerodynamic disturbance. Additionally, BOV is raised to 40km by a high altitude balloon to extend micro gravity duration to 30 (or possibly 60) seconds. Thus we realize a medium duration micro gravity experimental system with good micro gravity environment. In this system, the most characteristic point is double-shell structure to realize drag-free system. The inner shell can fall freely since the outer shell is controlled not to collide with the inner shell. In the experiments, we realize good-quality micro gravity and realize to continue moderate micro gravity duration. This system is now improving and near future we can practically utilize BOV's system for moderate micro gravity duration with low-cost easily.
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INTERNATIONAL JOURNAL OF MICROGRAVITY SCIENCE AND APPLICATION 26(1) 43-50 2009年The Balloon-based Operation Vehicle (BOV) originally developed for the micro-gravity experiments is modified as a supersonic flight demonstrator of a sub-scale precooled turbojet engine developed in Japan Aerospace Exploration Agency. In the supersonic flight demonstration, the vehicle is raised by a high-altitude balloon up to a 40 km altitude and is dropped to accelerate to a supersonic velocity. To extend the flight time for an engine combustion test in the supersonic environments, the vehicle is redesigned in a wing-body configuration with a main delta wing and movable vertical and horizontal tail wings so that it can be pulled up above an altitude of 5 km. In this paper, the supersonic flight test plan is introduced, and an overview of the flight demonstrator and the tested supersonic air breathing engine is summarized.
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INTERNATIONAL JOURNAL OF MICROGRAVITY SCIENCE AND APPLICATION 26(1) 21-28 2009年A novel way to conduct microgravity experiments using high altitude balloon is now under development at ISAS/JAXA. By dropping the rocket shaped vehicle from the high altitude balloon, high quality microgravity environment can be served during its free fall of 30 to 60 sec. This paper summarizes the outline of free fall vehicle, which is called as BOV (Balloon based Operation Vehicle). The preliminary results of its second flight test are also presented to show its feasibility.
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Transactions of the Japan Society for Aeronautical and Space Sciences, Space Technology Japan (Web) 7(ists26) 2009年
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Transactions of the Japan Society for Aeronautical and Space Sciences, Space Technology Japan (Web) 7(ists26) 2009年
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JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌 25(1) 3-10 2008年1月31日
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AIAA 57th International Astronautical Congress, IAC 2006 6 4204-4213 2006年12月1日Hayabusa spacecraft performed the final descents and touchdowns twice in November 2005. In final descent phase, terrain alignment maneuvers were accomplished to control both altitude and attitude with respect to the surface by using four beams Laser Range Finder onboard. Then Hayabusa spacecraft made dynamic touchdowns the surface of the asteroid by the sampler system to collect samples automatically. This paper presents the terrain alignment maneuver and touchdown scheme. This paper also describes the novel sample horn system and touchdown dynamics. Touchdown tests on the ground are presented. Then the flight results on descent and touchdown dynamics are shown and discussed.
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JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌 23(4) 197-203 2006年11月30日
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JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌 23(4) 280-280 2006年11月30日
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JASMA : Journal of the Japan Society of Microgravity Application = 日本マイクログラビティ応用学会誌 22(4) 317-317 2005年11月28日
書籍等出版物
1講演・口頭発表等
16-
SPACEOPS 2023 the 17th international conference on space operations 2023年3月6日
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73rd International Astronautical Congress 2022年9月22日
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33rd International Symposium on Space Technology and Science 2022年3月1日
共同研究・競争的資金等の研究課題
3-
日本学術振興会 科学研究費助成事業 基盤研究(A) 2013年5月 - 2018年3月
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日本学術振興会 科学研究費助成事業 基盤研究(B) 2010年4月 - 2014年3月
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日本学術振興会 科学研究費助成事業 学術創成研究費 2004年 - 2008年
