研究者詳細 - 趙　孟佑

論文 - 趙　孟佑

分割表示643 件中 281 - 300 件目／全件表示 >>

Thermal distribution of typical structure specialized in 50cm class satellite（共著）査読有り

Yuki Seri, Toru Hatamura, Hirokazu Masui, Mengu Cho

The 5th Nano-Satellite Symposium 2013年11月

Distribution measurement of Nano-Satellite components for shock level estimation（共著）査読有り

Shingo Kimoto, Toru Hatamura, Hirokazu Masui, Mengu Cho

5th Nano-Satellite Symposium 2013年11月

Horyu-V the Space Environment Explorer Satellite ? Strategic Auditing, United Nations/United Arab Emirates Symposium on Basic Space Technology（共著）査読有り

Mohamed Mahmoud Ibrahim, Horyu-V team, Mengu Cho

Small Satellite Missions for Developing Space Nations 2013年10月

Development of Vacuum Arc Thruster for Nano-Satellite（共著）査読有り

Shingo Fuchikami, Masayoshi Nakamoto, Kazuhiro Toyoda, Mengu Cho

33rd International Electric Propulsion Conference 2013年10月

Evaluation of SRAM based FPGA performance by simulating SEU through fault injection 査読有り

Ibrahim M., Asami K., Cho M.

RAST 2013 - Proceedings of 6th International Conference on Recent Advances in Space Technologies 649 - 654 2013年09月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

This paper presents the technique and results of Single Event Upsets fault injection in the configuration bit-stream of SRAM-based FPGAs through partial reconfiguration of configuration frames. The Xilinx Virtex5 LX50 is used in the experiments. The Single Event Upset controller macro is used injecting faults to random locations of the FPGA bit-stream. The effects were studied on a design consisting of 4 embedded processor systems implemented in the FPGA. MATLAB is used for developing the external fault injection control environment. © 2013 IEEE.

DOI： 10.1109/RAST.2013.6581290

Scopus

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Nano-satellite development project and space engineering education at Kyushu Institute of Technology 査読有り

Cho M., Masui H., Satellite K.

RAST 2013 - Proceedings of 6th International Conference on Recent Advances in Space Technologies 1059 - 1063 2013年09月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

Students of Kyushu Institute of Technology successfully developed a 7kg nanosatellite, HORYU-II. The satellite was tested extensively at Center for Nanosatellite Testing. There are many lessons learned through its designing, development, testing and operation to be shared among the university satellite community. Since 2013, the university will launch a new post-graduate program, Space Engineering International Course, where Japanese and foreign students learn the basic space technology through hands-on experience gained by participating in a satellite project utilizing space engineering research infrastructure within the campus. The program is also carried out as United Nations/Japan long term fellowship programme to assist capacity building of basic space technology in countries that have little experience in satellite development. Selected students will be awarded Japanese government scholarship. This paper describes the space engineering education at Kyushu Institute of Technology. © 2013 IEEE.

DOI： 10.1109/RAST.2013.6581159

Scopus

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Peripheral electronics prototype of super-capacitor energy storage for small satellites 査読有り

Shimizu T., Underwood C., Cho M.

11th International Energy Conversion Engineering Conference 2013年09月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

Small satellites, weighting between 100 to 200 kg, were considered as a case study and their use of super-capacitors was assessed in this paper. Such satellites have witnessed an increasing use for various space applications including remote sensing constellations and technology demonstrations. However, their current maximum power supply capability ranges between 70 and 200W. This power range has become insufficient for accommodating wide range of recent payloads on small satellites, and this low power has become a limitation of such small satellites. Super-capacitors are low mass and low volume energy storage mediums that have an ability to supply high electrical power. Compared with conventional chemical batteries, they are able to supply high power at high efficiency without damaging its life. This is an order of magnitude better than the power delivery capability of conventional batteries, and would enable micro-satellites to operate payload with l-2kw power consumptions for a minute or so. This high power capability makes small satellites more attractive to wider applications such as radar imaging and new technology demonstrations which used to operate on a larger satellite platform, and may leads to a breakthrough in terms of platform choice for payloads. This paper discusses feasibility of the super-capacitor based power system through a prototype development.

Scopus

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Anomaly investigation of HORYU-II and lessons learned（共著）査読有り

Yuta Okumura, Kyutech Satellite Project, Hirokazu Masui, Mengu Cho

The 64th International Astronautical Cogress 2013年09月

Lessons Learned and a New Project: Measurement of arcing current on HORYU-III" satellite"( 共著）査読有り

Yuta Okumura,Kyutech Satellite Team, Tatsuo Shimizu, Hirokazu Masui, Mengu Cho

Tsinghua University IAF-SUAC International Student Workshop 2013年09月

Mission Results of High Voltage Technology Demonstration Statellite Horyu-2""（共著）査読有り

Shunsuke Iwai, Kyutech Satellite Project, Arifur Rahaman Khan, Hirokazu Masui, Minoru Iwata,Kazuhiro Toyoda, Mengu Cho

64th International Astronautical Congress 2013年09月

MITIGATION METHOD OF PREVENTING SECONDARY ARCING ON SOLAR ARRAY BY USING CAPACITOR AND INDUCTOR（共著）査読有り

Ishio Haruta, Tatsuo Shimizu, Kazuhiro Toyoda, Mengu Cho

64th International Astronautical Congress 2013年09月

High voltage Flight Experiment In Low Earth Orbit（共著）査読有り

Shunsuke Iwai, Justin J Likar, Teppei Okumura, Hirokazu Masui, Kazuhiro toyoda, Mengu Cho

Tsinghua University IAF-SUAC International Student Workshop 2013年09月

300V direct drive vacuum arc thruster for nano-satellite 査読有り

Nakamoto M., Fuchikami S., Toyoda K., Cho M.

51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 2013年08月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

Vacuum arc thruster is very light and small for installed nano-satellite, and it operates without igniter. The thruster takes use of discharging in triple (insulator, conductor and vacuum) junction. The vacuum arc discharge releases the metal vapor, which can result in producing thrust. This research investigated on basic performance of vacuum arc thruster and EM development. © 2013 by the American Institute of Aeronautics and Astronautics, Inc.

Scopus

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On-orbit data analysis of high voltage technology demonstration satellite HORYU-II 査読有り

Iwai S., Yoke T., Masui H., Iwata M., Toyoda K., Cho M.

51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 2013年08月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

The High Voltage Technology Demonstration Satellite named HORYU-II is a nano-satellite (30cm cubic shape, 7kg) successfully developed by students at Kyushu Institute of Technology. The main purpose of this satellite is orbital demonstration of the feasibility the forthcoming space high voltage technologies. The International Space Station (ISS) generates the highest voltage, 160V, among all of the current active space systems. HORYU-II aims at being the world's first satellite to generate a voltage of 300V by using solar array, which is significantly higher voltage than the one generated on board the ISS. However, due to the generation of the high voltage, Electrostatic Discharges (ESDs) are more likely to occur. Therefore, HORYU-II also aims at performing a demonstration of ESD mitigation technology. HORYU-II was launched by a H-2A rocket on May 18, 2012. HORYU-II is functioning normally and data from orbit have recently been recorded and data analysis is under way. Results of the analysis will be presented in detail at the conference. © 2013 by Kyushu Institute of Technology.

Scopus

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Testing of Micro/Nano Satellites and Their On-orbit Performance（共著）査読有り

Hirokazu Masui, Toru Hatamura, Mengu Cho

27th Small Satellite Conference 2013年08月

Mission Results and Anomaly Investigation of HORYU-II（共著）査読有り

Yuki Seri, KIT Satellite Project, Hirokazu Masui, Mengu Cho

Annual AIAA/USU Conference on Small Satellites, Utah State University 2013年08月

Peripheral Electronics Prototype of Super-Capacitor Energy Storage for Small Satellites（共著）査読有り

Tatsuo Shimizu, Craig Underwood, Mengu Cho

11th International Energy Conversion Engineering Conference 2013年07月

Reconfigurable fault tolerant avionics system 査読有り

Ibrahim M., Asami K., Cho M.

IEEE Aerospace Conference Proceedings 2013年06月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

This paper presents the design of a reconfigurable avionics system based on modern Static Random Access Memory (SRAM)-based Field Programmable Gate Array (FPGA) to be used in future generations of nano satellites. A major concern in satellite systems and especially nano satellites is to build robust systems with low-power consumption profiles. The system is designed to be flexible by providing the capability of reconfiguring itself based on its orbital position. As Single Event Upsets (SEU) do not have the same severity and intensity in all orbital locations, having the maximum at the South Atlantic Anomaly (SAA) and the polar cusps, the system does not have to be fully protected all the time in its orbit. An acceptable level of protection against high-energy cosmic rays and charged particles roaming in space is provided within the majority of the orbit through software fault tolerance. Check pointing and roll back, besides control flow assertions, is used for that level of protection. In the minority part of the orbit where severe SEUs are expected to exist, a reconfiguration for the system FPGA is initiated where the processor systems are triplicated and protection through Triple Modular Redundancy (TMR) with feedback is provided. This technique of reconfiguring the system as per the level of the threat expected from SEU-induced faults helps in reducing the average dynamic power consumption of the system to one-third of its maximum. This technique can be viewed as a smart protection through system reconfiguration. The system is built on the commercial version of the (XC5VLX50) Xilinx Virtex5 FPGA on bulk silicon with 324 IO. Simulations of orbit SEU rates were carried out using the SPENVIS web-based software package. © 2013 IEEE.

DOI： 10.1109/AERO.2013.6497203

Scopus

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Performance Inprovement of Electron-emitting Film for Spacecraft Charging Mitigation（共著）査読有り

Atomu Tanaka, Naoki Matsumoto, Arifur Rahman Khan, Minoru Iwata, Kazuhiro Toyoda, Mengu Cho

29th International Symposium on Space Technology and Science 2013年06月

Total Electron Emission Yield Measurement of Polyimide at Different Temperatures (共著）査読有り

Akira Miyahara, Jiang Wu, Minoru Iwata, Kazuhiro Toyoda, Mengu Cho

29th International Symposium on Space Technology and Science 2013年06月

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