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 教授
- 学位
- 博士（工学)(2000年3月 東京大学)
- 研究者番号
- 10342619
- J-GLOBAL ID
- 202101019944115931
- researchmap会員ID
- R000018454
- 外部リンク
主要な受賞
25-
2025年4月
主要な論文
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Acta Astronautica 236 47-61 2025年6月19日 査読有り
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Acta Astronautica 235 47-54 2025年5月24日 査読有り招待有り筆頭著者責任著者The Smart Lander for Investigating the Moon (SLIM), with a dry mass of about 200 kg, was launched by the H-IIA vehicle on September 7, 2023, and made a precision lunar landing on January 19, 2024 (Coordinated Universal Time). The landing precision was evaluated to be within ~10 m at an altitude of approximately 50m from the Moon surface, far exceeding the target landing accuracy of 100 m and realizing the world’s first pinpoint landing, although a trouble occurred just before landing and one of the two main engines lost thrust. The two micro/nano rovers of the SLIM separated immediately before landing and successfully captured SLIM images in fully autonomous operation mode. The operation team also obtained spectroscopic observations of rocks from sci- entific instruments onboard the SLIM, which are expected to provide clues on the origin of the Moon. Although not designed to endure the harsh temperatures of the lunar day and night, the lander operated after three lunar nights, gathering various engineering data. This paper reports the results of the lunar landing operations of SLIM
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Journal of Guidance, Control, and Dynamics 25-29 2025年3月11日 査読有り
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Acta Astronautica 226(P1) 772-781 2024年11月13日 査読有り
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Aerospace Science and Technology 155(P1) 2024年9月23日 査読有り
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Journal of Evolving Space Activities 2 2024年9月2日 査読有り
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Transactions of the Japan Society for Aeronautical and Space Sciences 67(1) 23-31 2024年1月4日 査読有り
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Transactions of the Japan Society for Aeronautical and Space Sciences 66(6) 199-208 2023年11月4日 査読有り
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The Journal of the Astronautical Sciences 69 1726-1743 2022年11月11日 査読有り
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JOURNAL OF SPACECRAFT AND ROCKETS 59(2) 651-659 2022年3月29日 査読有り
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JOURNAL OF GUIDANCE, CONTROL, AND DYNAMICS 46(4) 695-708 2022年2月1日 査読有り
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Journal of Guidance, Control, and Dynamics 45(2) 280-295 2022年2月1日 査読有り
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Transactions of the Society of Instrument and Control Engineers 58(3) 194-201 2022年
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19(3) 334-343 2021年5月4日 査読有り
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Proceedings of the International Astronautical Congress, IAC C4 2021年
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AIAA Propulsion and Energy Forum, 2021 2021年
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Journal of Guidance, Control, and Dynamics 44(4) 854-861 2020年12月1日 査読有り
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Acta Astronautica 176(6) 438-454 2020年11月1日 査読有り
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日本航空宇宙学会論文集 68(2) 89-95 2020年8月1日 査読有り<p>A Fault Detection, Isolation, and Recovery (FDIR) algorithm for attitude control systems is a key technology to increasing the reliability and survivability of spacecraft. Micro/nano interplanetary spacecraft, which are rapidly evolving in recent years, also require robust FDIR algorithms. However, the implementation of FDIR algorithms to these micro/nano spacecraft is difficult because of the limitations of their resources (power, mass, cost, and so on). This paper shows a strategy of how to construct a FDIR algorithm in the limited resources, taking examples from micro deep space probe PROCYON. The strategy focuses on function redundancies and multi-layer FDIR. These ideas are integrated to suit the situation of micro/nano interplanetary spacecraft and demonstrated in orbit by the PROCYON mission. The in-orbit results are discussed in detail to emphasize the effectiveness of the FDIR algorithm. </p>
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Aerospace 7(97) 97-97 2020年7月1日 査読有りJAXA’s ERG (Exploration of Energization and Radiation in Geospace) Spacecraft, which is nicknamed Arase, was launched on 20 December 2016. Arase is a spin-stabilized and Sun-oriented spacecraft. Its mission is to explore how relativistic electrons in the radiation belts are generated during space storms. Two different on-ground attitude determination algorithms are designed for the mission: A TRIAD-based algorithm that inherits from old missions and a filtering-based new algorithm. This paper, first, discusses the design of the filtering-based attitude determination algorithm, which is mainly based on an Unscented Kalman Filter (UKF), specifically designed for spinning spacecraft (SpinUKF). The SpinUKF uses a newly introduced set of attitude parameters (i.e., spin-parameters) to represent the three-axis attitude of the spacecraft and runs UKF for attitude estimation. The paper then presents the preliminary attitude estimation results for the spacecraft that are obtained after the launch. The results are presented along with the encountered challenges and suggested solutions for them. These preliminary attitude estimation results show that the expected accuracy of the fine attitude estimation for the spacecraft is less than 0.5°.
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DESIGN AND DEVELOPMENT OF FIBER OPTIC ROTATION SENSORS 113-124 2019年7月1日
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Earth, Planets and Space 70(1) 102 2018年12月1日
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Acta Astronautica 152 299-309 2018年11月1日
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航空宇宙技術 17 35-43 2018年3月1日<p>SLIM (Smart Lander for Investigating Moon) is the Lunar Landing Demonstrator which is under development at ISAS/JAXA. SLIM demonstrates not only so-called Pin-Point Landing Technique to the lunar surface, but also demonstrates the design to make the explorer small and lightweight. Realizing the compact explorer is one of the key points to achieve the frequent lunar and planetary explorations. This paper summarizes the preliminary system design of SLIM, especially the way to reduce the size.</p>
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SPACEFLIGHT MECHANICS 2017, PTS I - IV 160 2615-2629 2017年
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Transactions of the Japan Society for Aeronautical and Space Sciences 60(3) 181-191 2017年
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 60(3) 181-191 2017年
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 14(30) Pt_7-Pt_14 2016年<p>In this study, a crater detection method for a moon-landing system with low computational resources is proposed. The proposed method is applied to the Smart Lander for Investigating Moon (SLIM), which aims for a pin-point landing on the moon. According to this plan, surface images of the moon will be captured by a camera mounted on the space probe, and the craters are to be detected from the images. Based on the positional relationship between detected craters, the method estimates the exact flight position of the space probe. Because the computational resources of SLIM are limited, rapid and accurate crater detection must be performed using fixed-point arithmetic on a field-programmable gate array (FPGA). This study proposes a crater detection method that uses principal component analysis (PCA). The computational processing for crater detection by PCA is performed by product-sum operations, which are suitable for fixed-point arithmetic. Moreover, this method is capable of parallel processing; hence high-speed processing is expected. This study not only introduces a crater detection method using PCA but also evaluates the properties of this method.</p>
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INTERNATIONAL JOURNAL OF MICROGRAVITY SCIENCE AND APPLICATION 32(2) 2015年 査読有り
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航空宇宙技術 14 59-65 2015年In this paper, direction control of balloon gondola with only untwisting motor is proposed. Typically a reaction wheel and another actuator for unloading the reaction wheel are in use to control the attitude (or direction) of the gondola. Although this method can get high accuracy control performance, two actuators spend many resources of the gondola. The proposed method uses only untwisting motor installed above the gondola to rotate. This method can not realize such high accuracy control performance but realize direction control with the most simple configuration. The proposed method is applied to prototype GAPS (General Anti-Particle Spectrometer) balloon experiment in 2012. This paper shows control design for this experiment and the results of the proposed method.
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SPACE TELESCOPES AND INSTRUMENTATION 2014: OPTICAL, INFRARED, AND MILLIMETER WAVE 9143 2014年
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SPACE TELESCOPES AND INSTRUMENTATION 2012: OPTICAL, INFRARED, AND MILLIMETER WAVE 8442 2012年
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 10(28) Pf_15-Pf_19 2012年We are in progress to develop a system for automatic operation of a satellite in order to reduce human load at satellite steady operation phase. The ground station for small satellite REIMEI (INDEX : INnovative-technology Demonstration EXperiment) is used as a test bench for verification of the proposed method. In our new automatic operation system, a scheduler software as a substitutive operator manages all the operations through a unified procedure, including sending command, receiving telemetry, and driving antenna in accordance with an operation time line which is prepared before the operation pass. The scheduler also performs diagnostics of satellite anomaly based upon the received telemetry data and status of the ground station. In case that some anomaly of the satellite is detected, the scheduler initiates an emergency schedule that was prepared depending on the emergency level. The automatic operation system is nearly completed for downlink operations of the data recorder that account for 75% of REIMEI steady operation. This approach is very effective to reduce psychological and physical load of operators.
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Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan (Web) 10(ists28) 2012年
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Advances in Space Research 48(2) 323-333 2011年7月15日
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日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 58(682) 309-315 2010年11月5日A radio astronomical observatory satellite ``ASTRO-G'', which will be launched in 2012, has two characteristics: flexible appendages and high-speed and high-precision attitude maneuvering. Because of these two antithetical features, attitude control system (ACS) of ASTRO-G becomes quite challenging in comparison with those of past satellites. For such a satellite, feedforward control which is robust to model identification error is considered to be important. Nil-Mode-Exciting (NME) profiler is one of references for anti-vibration, which is designed to excite no flexible modes, and thus its robustness is considered to be of most significant. NME profiler, however, is relatively slow reference because of negligible high frequency component. In this paper, we propose Modified NME profiler which is relatively fast reference designed by convolution of NME profiler and Input Shaper. Some anti-vibration experiments are carried out to show the effectiveness of the proposed reference.
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 8(27) Po_4_1-Po_4_6 2010年A space gravitational wave antenna, DECIGO (DECI-hertz interferometer Gravitational wave Observatory) will provide fruitful insights into the universe, particularly on dark energy, the formation mechanism of supermassive black holes, and the inflation of the universe. In the current pre-conceptual design, DECIGO will be comprised of 4 interferometer units; each interferometer unit will be realized by formation flight of three drag-free spacecraft with 1000 km separation. Since DECIGO will be an extremely challenging mission with high-precision formation flight, it is important to increase the technical feasibility before its planned launch in 2024. Thus, we are planning two milestone missions. DECIGO pathfinder (DPF) is the first milestone mission for DECIGO, and key components for DPF are being tested on ground and in orbit. In this article, we review the conceptual design and current status of DECIGO and DPF.
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 8(27) To_4_33-To_4_41 2010年 査読有りSpace VLBI (very long baseline interferometry) mission, ASTRO-G, will be launched in 2013 by Japan Aerospace Exploration Agency (JAXA). ASTRO-G is a follow-on mission of HALCA (VSOP) mission in 1990s, which was the world first space VLBI mission. ASTRO-G will consists of a huge synthetic aperture with diameter of 35,000 Km together with radio antennas in the ground. They will achieve the world highest angular resolution imaging by means of 43 GHz observation. This paper describes the advanced key technologies of ASTRO-G such as the 9 m deployable antenna with very accurate surface, the fast rest - to - rest attitude maneuver, and the precision orbit determination above NAVSTAR's orbits. These advance technologies lead ASTRO-G mission to the astronomical observation with the world highest angular resolution.
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2010 IEEE-ION POSITION LOCATION AND NAVIGATION SYMPOSIUM PLANS 1287-1294 2010年 査読有り
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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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JASMA : Journal of the Japan Society of Microgravity Application 26(1) 21-28 2009年1月31日
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日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 57(660) 25-31 2009年1月5日REIMEI/INDEX (INnovative-technology Demonstration EXperiment) is a 70kg class small satellite which the Institute of Space and Astronautical Science, Japan Exploration Agency, ISAS/JAXA, has developed for observation of auroral small-scale dynamics as well as demonstration of advanced satellite technologies. An important engineering mission of REIMEI is integrated satellite control using commercial RISC CPUs with a triple voting system in order to ensure fault-tolerance against radiation hazards. Software modules concerning every satellite function, such as attitude control, data handling, and mission applications, work cooperatively so that highly sophisticated satellite control can be performed. In this paper, after a concept of the integrated satellite control is introduced, the Integrated Controller Unit (ICU) is described in detail. Also unique topics in developing the integrated control system are shown.
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Journal of Space Engineering 2(1) 12-24 2009年
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60th International Astronautical Congress 2009, IAC 2009 2 1096-1100 2009年 査読有り
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Proc. 60th International Astronautical Congress 1 IAC-09.A2.5.3-730 2009年 査読有り
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7(26) Ph_29-Ph_33 2009年The second flight of microgravity experiment system using a free fall capsule from a high altitude balloon was conducted in May 2007. Using a drag free control, around 10-4G gravity conditions were obtained for 30 seconds. Results of a combustion experiment with Japanese sparker conducted inside the microgravity experimental unit were also reported.
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7(26) Tg_27-Tg_34 2009年JAXA is developing Mach 5 hypersonic turbojet engine technology that can be applied in a future hypersonic transport. Now, Jet Engine Technology Research Center of JAXA conducts the experimental study using a 1 / 10 scale-model engine. In parallel to engine development activities, a new supersonic flight-testing vehicle for the hypersonic turbojet engine is under development since 2004. In this paper, the system configuration of the flight-testing vehicle is outlined and development status is reported.
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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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日本航空宇宙学会論文集 56(652) 203-210 (J-STAGE)-210 2008年 査読有りFor astronomical observing missions by formation flying satellites in LEO, satellites require control force to keep the relative position, against Keplerian orbit in an inertia coordinate frame. Since satellites require propulsion systems, i.e. thrusters, but the use of thrusters limits the mission lifetime associated with the finite fuel supply. Thus the authors propose the formation flight using electromagnetic force. In this method, the electromagnetic force between super-conducting magnets are used for the relative position control. This method has the obvious advantage of no-fuel to acquire control force. Since such large magnetic moment in earth magnetism generates large disturbance torque, the magnetic moments should be sinusoidal with shorter period than that of the orbit period. Therefore, this paper proposes the relative position control by changing the phase difference between sinusoidal magnetic moments. The proposed method was evaluated with numerical simulations and the results shows the feasibility of the proposed formation flight.
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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 24(3) 296-300 2007年7月30日
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Proceedings of the SICE Annual Conference 3019-3024 2007年 査読有り
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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
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電子情報通信学会論文誌. B, 通信 = The transactions of the Institute of Electronics, Information and Communication Engineers. B 88(1) 69-78 2005年1月1日2004年打上げ予定の小型科学衛星"INDEX"は,60[kg]の小型衛星でありながら高精度の姿勢制御を行ってオーロラ観測を行う科学衛星である.重量及びコストの点でハードウェアの制約を受ける中で,高精度な姿勢制御性能を実現するために様々な工夫を施している.本論文ではこのうち,センサ性能を十分に考慮した姿勢制御系の設計手法,また光学センサの触を避けるための衛星運用方式とその評価などについて述べる.更に,効率的に試験・開発を進めるための柔軟なテレメトリコマンドシステムについても紹介する.
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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 21 66-66 2004年11月4日
MISC
46講演・口頭発表等
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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 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)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 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)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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計測と制御 = Journal of the Society of Instrument and Control Engineers 2012年3月10日 計測自動制御学会
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日本物理学会講演概要集 2012年 一般社団法人 日本物理学会
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電子情報通信学会技術研究報告. SANE, 宇宙・航行エレクトロニクス 2011年10月10日 一般社団法人電子情報通信学会"Small space science Platform for Rapid INvestigation and Test", aka SPRINT - project is a new satellite series for scientific applications of Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (ISAS/JAXA). The design concept of the satellite bus is based on flexibility with alternative, and selectable options. SPRINT-A is the first satellite of the series, which aims to make scientific observations of planetary atmosphere at extreme-ultraviolet wavelength.
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「運動と振動の制御」シンポジウム講演論文集 2011年6月28日 一般社団法人日本機械学会In the lunar-planetary exploration, most of landers made a landing on flat areas of surface, because there are a lot of rocks craters and hills on lunar-planetary surface. For the next generation lunar-planetary exploration, the development of a highly accurate landing technology is demanded to land on the complex terrain. The navigation-guidance technology and hazard avoidance have been studied for the safe landing. Moreover the development of landing leg is required for the safe landing in the final phase of landing sequence. This paper presents the development of experimental system of active landing leg, and examine the landing shock response. In addition, we consider the effectiveness of active landing leg and the application to the control method of lander's overturn prevention.
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電子情報通信学会技術研究報告. SANE, 宇宙・航行エレクトロニクス 2011年4月14日 一般社団法人電子情報通信学会This paper proposes a novel method to improve performance of Fiber Optical Gyroscopes (FOGs) for attitude sensor on a satellite with temperature fluctuation. When a FOG is on satellite, FOG performance is disturbed by temperature fluctuation by sunlight and sunshade or power-on of other instruments. One of the methods to suppress the deterioration of the FOG performance by temperature fluctuation is temperature control. Temperature control for the FOG was carried out at Reimei (Japanese small satellite launched in 2005) and the FOG long term performance was improved. However the FOG short term performance was disturbed. This is because thermal input by temperature control induced Shupe Effect. In addition to this effect, temperature control is a burden for a satellite in terms of power consumption. This paper describes how to improve the FOG performance without temperature control. We consider the dynamic FOG bias rate model with respect to temperature fluctuation and identify this model using system identification analysis. As a result, dynamic FOG bias rate model is identified accurately and the FOG bias rate response with respect to temperature fluctuation is estimated correctly. By subtracting estimated FOG bias rate response from the FOG output, FOG performance is improved against temperature fluctuation.
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電子情報通信学会総合大会講演論文集 2011年2月28日 一般社団法人電子情報通信学会
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電子情報通信学会総合大会講演論文集 2010年3月2日 一般社団法人電子情報通信学会
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電子情報通信学会技術研究報告. SANE, 宇宙・航行エレクトロニクス 2008年12月12日 一般社団法人電子情報通信学会近年光ファイバジャイロ(FOG)が、低消費電力、低価格、小型などの観点から小型衛星の姿勢センサとして注目を浴びている。FOGを姿勢センサとして姿勢制御に用いる場合、衛星軌道上の日照周期による周期的な温度変動がバイアスの温度依存性に影響し、バイアス安定性が悪化するという問題がある。これを解決するためにヒーターを用い温度を一定にする温度制御がとられてきた。温度制御により温度依存性は防ぐことに成功するものの、温度制御を行うと熱入力によってシュッペ効果が生じ、バイアス安定性を悪化させることが新たな問題となってきている。そこで本稿ではシュッペ効果がFOGのバイアスに与える影響を補償するために、ヒーター入力によるシュッペ効果応答を抽出して、線型性を利用しこの効果を差し引く補正方法を提案する。
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電子情報通信学会技術研究報告 2008年6月26日 一般社団法人電子情報通信学会宇宙航空研究開発機構(JAXA)・宇宙科学研究本部(ISAS)では,小型科学衛星の新たなシリーズを立ち上げ,これに供する標準バスの開発に着手している.本シリーズに提案されている各ミッションの多様な要求に対応するため,標準バスの柔軟性を高める工夫が必要となる.本稿では,階層的標準化の定義,コアとオプション仕様を峻別した「セミオーダメイド」コンセプトの概要,統合化/モジュール化などのアーキテクチャのトレードオフスタディ,などについて述べる.
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電子情報通信学会技術研究報告 2008年6月26日 一般社団法人電子情報通信学会将来の地球観測・科学観測ミッションの為に高精度、広ダイナミックレンジ、長寿命、高信頼性を有する慣性基準装置(IRU)が求められている。光ファイバジャイロ(FOG)はこれらの要求を満足する有力候補の一つであり、2012年度打上げのASTRO-Gへの搭載を目標に高精度FOG-IRUを開発中である。本稿ではその開発状況について報告することを目的とし、目標仕様やEM検討モデルの評価結果、FOG EM設計結果、IRU基本設計結果等を示す。
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電子情報通信学会技術研究報告. SANE, 宇宙・航行エレクトロニクス 2007年11月23日 一般社団法人電子情報通信学会本稿では初めに干渉型光ファイバジャイロ(IFOG)の原理と構成を紹介し,次いで宇宙分野におけるこれまでの応用例を概観する.IFOGは従来型のコマ式ジャイロと比べ,可動部が全くなく振動擾乱を生じない,あるいはスケールファクタ安定性に優れるといった利点を有しており,このため例えば人工衛星の分野では,姿勢制御用の超高性能ジャイロセンサとしても期待されている.また,コマ式ジャイロセンサと比べ構造がシンプルなIFOGは,小型なものであっても適度な性能が得られる利点も有しており,このため小型衛星の姿勢制御用としても適している.本稿の後半では,これら最新の研究開発動向について具体例を示しながら述べる.
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Proceedings of the SICE Annual Conference 2007年
共同研究・競争的資金等の研究課題
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日本学術振興会 科学研究費助成事業 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 2011年 - 2013年
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日本学術振興会 科学研究費助成事業 2004年 - 2008年
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日本学術振興会 科学研究費助成事業 2005年 - 2006年
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日本学術振興会 科学研究費助成事業 2003年 - 2004年
