Updated on 2024/05/14

 
MASUI Hirokazu
 
Scopus Paper Info  
Total Paper Count: 0  Total Citation Count: 0  h-index: 8

Citation count denotes the number of citations in papers published for a particular year.

Affiliation
Faculty of Engineering Department of Space Systems Engineering
Job
Assistant Professor
External link

Research Interests

  • Space Environment

  • Nano Satellite

  • Environmental Testing

  • Electric Propulsion

Undergraduate Education

  • 2001.03   Kyushu Institute of Technology   Faculty of Engineering   Graduated   Japan

Post Graduate Education

  • 2006.03   Kyushu University   Graduate School, Division of Integrated Science and Engineering   Doctoral Program   Completed   Japan

Degree

  • Kyushu University  -  Doctor of Engineering   2006.03

Biography in Kyutech

  • 2019.04
     

    Kyushu Institute of Technology   Faculty of Engineering   Department of Space Systems Engineering   Assistant Professor  

  • 2014.04
    -
    2019.03
     

    Kyushu Institute of Technology   Faculty of Engineering   Department of Applied Science for Integrated System Engineering   Assistant Professor  

  • 2010.08
    -
    2014.03
     

    Kyushu Institute of Technology   Laboratory of Spacecraft Environment Interaction Engineering   Assistant Professor  

Academic Society Memberships

  • 2013.07   プラズマ・核融合学会   Japan

  • 2004.04   日本航空宇宙学会   Japan

Research Career

  • 超小型衛星の開発と環境試験

    超小型衛星,環境試験,試験標準

    研究期間: 2010.04  - 

  • 宇宙機の帯電,放電に関する地上試験

    宇宙プラズマ,ESD,帯電,太陽電池

    研究期間: 2006.04  -  2010.03

Papers

  • One Year On-Orbit Results of Improved Bus, LoRa Demonstration and Novel Backplane Mission of a 1U CubeSat Constellation Reviewed

    MASKEY Abhas, LEPCHA Pooja, SHRESTHA Hari Ram, CHAMIKA Withanage Dulani, MALMADAYALAGE Tharindu Lakmal Dayarathna, KISHIMOTO Makiko, KAKIMOTO Yuta, SASAKI Yuji, TUMENJARGAL Turtogtokh, MAEDA George, KIM Sangkyun, MASUI Hirokazu, YAMAUCHI Takashi, CHO Mengu

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )   65 ( 5 )   213 - 220   2022.01

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    <p>The BIRDS series from Kyushu Institute of Technology has deployed 1U CubeSat constellations from International Space Station since 2017. BIRDS-3 was deployed in June 2019. Lessons learnt from BIRDS-1 and BIRDS-2 have been used to improve the bus system of BIRDS-3. Improvements have been made in On-Board Computer, Electrical Power and Communication systems. BIRDS-3 has implemented novel Backplane Mission which uses SoftCIB; an in-house designed software defined backplane interface board. The mission has the potential to standardize interface and cut down on development time. BIRDS-3 project has placed a LoRa module to check its performance in space. The module has the potential for future low-cost, low-powered Store and Forward mission and CubeSat communication system. This paper provides detailed information on the improved BIRDS bus system, LoRa Demonstration and Backplane Mission designs, and on-orbit results since its deployment in June 2019. The results presented are based on cumulative operation time of three years for three satellites operating each for a year. The satellites are functional and will remain in orbit until summer of 2021.</p>

    DOI: 10.2322/tjsass.65.213

    CiNii Research

  • Application of Small Satellites for Low-Cost Remote Data Collection Using LoRa Transmitters Reviewed International journal

    LEPCHA Pooja, KIM Sankyun, MASUI Hirokazu, CHO Mengu

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )   19 ( 2 )   224 - 230   2021.01

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    <p>The advancement of small satellites has greatly reduced the overall cost and development time of the satellite compared to conventional satellites fulfilling similar missions. Although there have been many developments on the satellite side, for missions like remote data collection the sensor nodes on the ground have been insubstantial because of its limitations in standalone operability and higher power consumption leading to higher cost and sparse area coverage. In this paper, we designed and developed a low power, low-cost remote sensor station with LoRa transmitters, which has the standalone operating capability. It is compact, mobile and it has a simple design. It is equipped with a self-sustaining power supply, LoRa transmitters, processors, antenna and sensors; mainly focusing on the weather monitoring parameters like humidity and temperature. The basic mechanism of data relay is to sense and transmit sensor data packets in real-time. The feasibility of the sensor station has been studied in terms of power budget, link budget, its operation outdoors and the overall development costs. The sensor station can be placed in areas where there are no ground infrastructures for communication.</p>

    DOI: 10.2322/tastj.19.224

    CiNii Article

    CiNii Research

    Other Link: https://www.jstage.jst.go.jp/article/tastj/19/2/19_19.224/_pdf

  • Cubesat interface standardization to achieve faster delivery and mission success Reviewed

    Cho M., Yamauchi T., Sejera M., Kim S., Masui H.

    Proceedings of the International Astronautical Congress, IAC   2020-October   2020.01

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    Copyright © 2020 by Mengu Cho. In 2019, a new project to standardize the CubeSat interface started. Discussion has been made utilizing various gathering opportunities of the CubeSat community. A survey on the CubeSat interface has been distributed the CubeSat community to collect the satellite developers' experience and desires regarding the interface, and the CubeSat vendors' reality and desires. A research work to identify the difficulties associated integrating CubeSat components from different vendors is on-going. Initial finding suggests that clear definition of interface related information, especially the digital data communication, in the user manual is really needed. A table of content of the standard has been drafted, which is mainly made of four parts. (1) Interface among components, (2) Interface between CubeSat bus (platform) and mission payloads, (3) Document specification to describe the information related to component interface, (4)Document specification to describe the information related to CubeSat bus (platform) interface. The project aims at submitting a new work item proposal to ISO/TC20/SC14 in summer 2021 and publish the standard by 2024.

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  • Horyu-VI: International cubesat mission to investigate lunar horizon glow Reviewed

    Orger N.C., Cho M., Iskender O.B., Lim W.S., Chandran A., Ling K.V., Holden K.H.L., Chow C.L., Bellardo J., Faure P., Santoni F., Circi C., Marzioli P., de Grossi F., Frezza L., Toyoda K., Masui H., Mariko T., Alarcon J.R.C., Yamauchi T., Kim S., Lim J.W.M., Potrivitu G., Laterza M.

    Proceedings of the International Astronautical Congress, IAC   2020-October   2020.01

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    Copyright © 2020 by International Astronautical Federation (IAF). All rights reserved. Interaction with the solar wind and UV/X-ray irradiation can cause the lunar dust to be electrostatically charged and mobilized all around the Moon, and light scattering by this dust cloud can be observed over the lunar terminator. This phenomenon, which has also been called the lunar horizon glow (LHG), still remains unexplained. The LHG observations using conventional lunar probes have limited observation opportunities and do not cover varying space weather conditions in cislunar environment such as strong upstream plasma flow and micrometeoroid flux that could enhance the lunar dust presence in the exosphere. The nanosatellite “HORYU-6” specialized in LHG observations will be put into lunar orbit to detect the light scattering above the lunar terminator. The proposed payload will perform multi-spectral imaging to monitor the lunar horizon several minutes before orbital sunrise or after orbital sunset for light scattering analysis. We show that we can obtain scientific results of lunar and planetary exploration using CubeSat at low cost and in a short period of time, and contribute to the development of lunar and planetary exploration in the future. The spacecraft will be developed jointly with universities in Singapore, the United States and Italy under the supervision of Kyushu Institute of Technology, with the aim of launching the SLS-2 rocket in the second half of 2022. Together with its own scientific objectives, the HORYU-6 mission will demonstrate the low thrust trajectory optimization by utilizing electric propulsion system together with other novel embedded technology demonstrations such as atomic clock, deep space navigation and communication with CubeSats.

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  • SS27 Radiation protection and monitoring experiment on-board a 1U CubeSat and its ground verification Reviewed

    Murase T., Masui H., Cho M., Wei S.

    Proceedings - IEEE International Symposium on Circuits and Systems   2020-October   2020.01

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  • AOBA VELOX-IV: 2U CubeSat for the technological demonstration of lunar horizon glow mission Reviewed

    161   328 - 337   2019.08

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    DOI: 10.1016/j.actaastro.2019.05.046

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  • CubeSat bus interface with Complex Programmable Logic Device Reviewed

    160   331 - 342   2019.07

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    DOI: 10.1016/j.actaastro.2019.04.047

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  • Demonstration of lean satellite (1U CubeSat) testing using PeTT vacuum chamber Reviewed

    Bonsu B., Masui H., Cho M.

    Proceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019   959 - 966   2019.06

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    DOI: 10.1109/RAST.2019.8767775

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  • Experimental investigation on silica dust lofting due to charging within micro-cavities and surface electric field in the vacuum chamber Reviewed

    63 ( 10 )   3270 - 3288   2019.05

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    Language:English   Publishing type:Research paper (scientific journal)

    DOI: 10.1016/j.asr.2019.01.045

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  • BIRDS-2: A Constellation of Joint Global Multi-Nation 1U CubeSats Reviewed

    1152 ( 1 )   2019.03

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    Language:English   Publishing type:Research paper (international conference proceedings)

    DOI: 10.1088/1742-6596/1152/1/012008

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  • Design, Analysis and Testing of Monopole Antenna Deployment Mechanism for BIRDS-2 CubeSat Applications Reviewed

    1152 ( 1 )   2019.03

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    Language:English   Publishing type:Research paper (international conference proceedings)

    DOI: 10.1088/1742-6596/1152/1/012007

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  • BIRDS-3 satellite project including the first satellites of Sri Lanka and Nepal Reviewed

    Chamika W.D., Cho M., Maeda G., Kim S., Masui H., Yamauchi T., Panawannege S., Shrestha S.B.

    Proceedings of the International Astronautical Congress, IAC   2019-October   2019.01

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    Copyright © 2019 by the International Astronautical Federation (IAF). All rights reserved. The Joint Global Multi-National Birds also known as BIRDS, is a multinational small satellite program led by Kyushu Institute of Technology (Japan). BIRDS program gives opportunity to non-space fairing nations to design, integrate, build, test, launch and operate their nation's first satellite. This paper focuses on BIRDS-3 which is the third batch under BIRDS program. BIRDS-3 is a constellation of three 1U CubeSats belonging to Japan (Uguisu), Nepal (NepaliSat-1: Nepal's first satellite) and Sri Lanka (Raavana-1: Sri Lanka's first satellite). BIRDS-3 has two members (students) from Nepal, three from Japan, and two from Sri Lanka and one from Bhutan. These students have been enrolled in Space Engineering International Course (SEIC) in Kyushu Institute of Technology. External dimensions of one satellite is 113.5mm x 100mm x 100mm and the weight is approximately 1.05kg. This constellation executes four missions: Imaging Mission (CAM), Attitude Determination and Control System mission (ADCS), LoRa Demonstration Mission (LDM), Software Configurable Backplane Board Mission (BPB). The CubeSats were deployed to the orbit on 17th June 2019 from International Space Station (ISS). After deployment CubeSats are being operated through BIRDS ground station network. This paper describes the background, missions, stakeholders and initial operational results after the deployment from International Space Station (ISS).

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  • Ionosphere observation and 3D mapping mission via CubeSat constellation; in-orbit operation results of the SPATIUM-I CubeSat Reviewed

    Aheieva K., Rahmatillah R., Ninagawa R., Adebolu I.O., Kim S., Kakimoto Y., Nakayama D., Kishimoto M., Elmegharbel H.A., Yamauchi T., Masui H., Cho M., Lap C.C., Ying Z., Siu T.M., Holden L.K.H.

    Proceedings of the International Astronautical Congress, IAC   2019-October   2019.01

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    Copyright © 2019 by the International Astronautical Federation (IAF). All rights reserved. This paper will describe the progress in the SPATIUM satellite project, developed to do the global three-dimensional ionosphere mapping via CubeSat constellation equipped with an atomic clock and will show the result of the on-orbit operation of about 1 year of the first path-finder satellite SPATIUM-I. The SPATIUM-I satellite, launched in October 2018, validated the key technologies that are based on the clock-signal phase-shift sent from the satellite carried Chip-Scale Atomic Clock (CSAC). The satellite did the on-orbit demonstration of Chip Scale Atomic Clock (CSAC) as well as the evaluation of the signal time delay due to ionosphere and atmosphere. SPATIUM-I satellite on-orbit operation results will be presented. Knowing the precise satellite location and the signal delay from each satellite that transmits the signal with two UHF frequencies, by solving the inverse problem we can derive the ionosphere density and atmosphere water vapor. This data can be used to improve the accuracy of the earth and space weather forecast. This concept will then be implemented for the evaluation of Ionosphere Observation and Ionosphere 3D mapping via SPATIUM-II and SPATIUM-III projects. The SPATIUM project is under development by the Laboratory of Spacecraft Environmental Interaction Engineering (LaSEINE) of Kyushu Institute of Technology in collaboration with Nanyang Technological University, Singapore.

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  • How seven emerging nations entered the space age via BIRDS Projects 1 through 4 Reviewed

    Maeda G., Cho M., Masui H., Kim S., Yamauchi T.

    Proceedings of the International Astronautical Congress, IAC   2019-October   2019.01

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    Copyright © 2019 by the International Astronautical Federation (IAF). All rights reserved. Operating on the basis that "one cannot learn how to build satellites by reading books", Kyushu Institute of Technology (Kyutech) launched its BIRDS Project in 2015 with Ghana, Bangladesh, Mongolia, Nigeria, and Japan. The main purpose was to help most of them launch their first satellites, and then somehow make satellite development sustainable in their own countries after the return of their students. Subsequently, Kyutech started BIRDS-2 in 2016, BIRDS-3 in 2017, and BIRDS-4 in 2018, involving the nations of Bhutan, Malaysia, Philippines, Nepal, Sri Lanka, and Paraguay. BIRDS-5 will start in October of 2019. In this paper we discuss the various capacity building results in these countries. We believe the seeds have been sown in these countries for sustained national space development via the activities of launching their first satellites - a crucial step. The seven nations who did (or are doing) their first satellites are: (1) Ghana, (2) Bangladesh, (3) Mongolia, (4) Bhutan, (5) Nepal, (6) Sri Lanka, and (7) Paraguay. Every nation participating in BIRDS pays its own way - there are no subsidies from Japan. They end up with their first space borne satellites but much more importantly they have engineers who know how to build a CubeSat.

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  • Project overview of SAPTIUM-I; a technology demonstration mission toward global three-dimensional ionosphere mapping via cubesat constellation equipped with an atomic clock Reviewed

    2018-October   2018.01

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  • Horyu-IV flight results of spacecraft plasma interaction experiments Reviewed

    2018-October   2018.01

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  • Design, development, testing and on-orbit performance results of a low-cost store-and-forward payload onboard a 1u cubesat constellation for remote data collection applications Reviewed

    2018-October   2018.01

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  • Challenges for CubeSats safety design and verification to do lean satellite development Reviewed

    2018-October   2018.01

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  • CubeSat mission for ionosphere mapping and weather forecasting using chip-scale atomic clock Reviewed

    2017-November   761 - 766   2017.11

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    Language:English   Publishing type:Research paper (international conference proceedings)

    DOI: 10.1109/PIERS-FALL.2017.8293237

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  • Screening of nanosatellite microprocessors using californium single-event latch-up test results Reviewed

    126   334 - 341   2016.09

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    Language:English   Publishing type:Research paper (scientific journal)

    DOI: 10.1016/j.actaastro.2016.05.004

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  • Thermal Design and Verification Method and Orbit Data Analysis of Horyu-2

    MASUI Hirokazu, SERI Yuki, HAMADA Akimitsu, CHO Mengu

    JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES   64 ( 5 )   270 - 275   2016.01

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    DOI: 10.2322/jjsass.64.270

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    Other Link: https://ci.nii.ac.jp/naid/130005249170

  • Finite Element Analysis of Vibration Amplification Distribution in Lean Satellites

    14 ( 30 )   Pf_51 - Pf_60   2016.01

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    Language:English   Publishing type:Research paper (scientific journal)

    DOI: 10.2322/tastj.14.Pf_51

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    Other Link: https://ci.nii.ac.jp/naid/130005246080

  • Five-nations CubeSat Constellation; An Inexpensive Test Case for Learning and Capacity Building Reviewed

    A. R. Khan, G. Maeda, H. Masui, JGMNB project members, M. Cho

    3rd AIAA Conference on University Satellite Missions and CubeSat Workshop & International Workshop on Lean Satellite Standardization   2015.11

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    Italy   Rome   2015.11.30  -  2015.12.04

  • Introduction of On-Orbit Experiment for Discharge Phenomena on Spacecraft(3)Demonstration of High Voltage Power Generation by Nano-Satellite (Horyu-2)

    MASUI Hirokazu, CHO Mengu

    91 ( 11 )   735 - 737   2015.11

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    Other Link: https://ci.nii.ac.jp/naid/110010016773

  • Design Considerations and Ground Testing of Electric Double-Layer Capacitors as Energy Storage Components for Nanosatellites Reviewed

    M. Alkali, M. Y. Edries, A. R. Khan, H. Masui, M. Cho

    JOURNAL OF SMALL SATELLITES   2015.10

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  • Discharge Phenomena on Spacecraft

    CHO Mengu, MASUI Hirokazu

    91 ( 9 )   614 - 618   2015.09

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    Other Link: https://ci.nii.ac.jp/naid/110010016667

  • Degradation Acceleration Tests of COTS Lithium-Ion Secondary Battery for Lean Satellites Reviewed

    T. Motohata, T. Shimizu, H. Masui, M. Cho

    30th International Symposium on Space Technology and Science   2015.07

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    Japan   Kobe   2015.07  -  2015.07

  • Thermal Analysis and Testing of Arc Event Generator and Investigation Satellite (AEGIS), HORYU-IV Reviewed

    T. T. Long, T. Yamasaki, H. Masui, M. Cho

    30th International Symposium on Space Technology and Science   2015.07

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    Japan   Kobe   2015.07  -  2015.07

  • Environment Test Campaign of Aluminium Substrate Solar Panel for Lean-satellites Reviewed

    H. O. Almubarak, H. Masui, M. Cho

    30th International Symposium on Space Technology and Science   2015.07

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    Japan   Kobe   2015.07  -  2015.07

  • Design and Testing of Electrical Power Subsystem (EPS) of a Lean Satellite, HORYU-IV Reviewed

    M. Y. Edries, A. Tanaka, E. Dashdondog, H. O. Almubarak, M. Alkali, A. R. Khan, H. Masui, M. Cho

    30th International Symposium on Space Technologies   2015.07

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    Japan   Kobw   2015.07  -  2015.07

  • Anomaly Investigation Using Telemetry Data of Horyu-2's for Single Event Latch-Up Reviewed

    H. Masui, Y. Tanaka, T. Tomioka, KIT satellite project, M. Cho

    30th International Symposium on Space Technology and Science   2015.07

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    Japan   Kobe   2015.07  -  2015.07

  • Research of Radiation Testing Method for Lean-Satellites Using Californium-252 Reviewed

    T. Tomioka, K. Taniwaki, H. Masui, M. Cho, K. Takamiya

    30th International Symposium on Space Technology and Science   2015.07

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    Japan   Kobe   2015.07  -  2015.07

  • Finite Element Analysis of Vibration Amplification Distribution within Lean Satellites Reviewed

    A. Batsuren, T. Hatamura, H. Masui, M. Cho

    30th International Symposium on Space Technology and Science   2015.07

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    Japan   Kobe   2015.07  -  2015.07

  • Activity and Strategy for Lean Satellite in Kyushu Institute of Technology Reviewed

    H. Masui, T. Hatamura, T.Shimizu, M. Cho

    7th Recent Advances Space Technology (RAST) 2015   2015.06

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    Turkey   Istanbul   2015.06  -  2015.06

    DOI: 10.1109/RAST.2015.7208450

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  • Introduction to Lean Satellite and ISO standard for Lean Satellite Reviewed

    M. Cho, H. Masui, F. Graziani

    RAST 2015   2015.06

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    Turkey   Istanbul   2015.06  -  2015.06

    DOI: 10.1109/RAST.2015.7208447

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  • The Simulation about Adjustment Method of Shock Level of Nano Satellites Reviewed

    2015.05

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    Language:Japanese   Publishing type:Research paper (scientific journal)

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  • Flight Results of Arcing Experiment Onboard High-Voltage Technology Demonstration Satellite Horyu-2 Reviewed

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

    Journal of Spacecraft and Rockets   2015.01

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    DOI: 10.2514/1.A33007

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  • The Simulation about Adjustment Method of Shock Level of Nano Satellites Reviewed

    HATAMURA Toru, MASUI Hirokazu, CHO Mengu, MAENO Kazuo

    JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES   63 ( 3 )   117 - 119   2015.01

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    DOI: 10.2322/jjsass.63.117

    Other Link: http://ci.nii.ac.jp/naid/130005072535

  • 5. Summary(Ground and Orbit Experiment of Electro Static Discharge Phenomena Caused by Interactions between Spacecraft and Space Plasma) Reviewed

    MASUI Hirokazu, CHO Mengu

    91 ( 11 )   738 - 739   2015.01

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    Other Link: https://ci.nii.ac.jp/naid/110010016774

  • Low Cost Thermal-Vacuum System for the Development of Very Small Spacecraft Reviewed

    Tatsuo Shimizu, Takuya Motohata, Hirokazu Masui, Minoru Iwata, Mengu Cho

    65th International Astronautical Congress   2014.09

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    Canada   Toronto   2014.09  -  2014.09

  • DEVELOPMENT OF A TESTING STANDARD OF COTS LITHIUM-ION BATTERIES FOR NANO-SATELLITE Reviewed

    T. Motohata, T. Shimizu, H. Masui, M. Cho

    65th International Astronautical Congress   2014.09

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    Canada   Toronto   2014.09  -  2014.09

  • Preliminary Study of Electric Double Layer Capacitor as an Energy Storage of Simple Nanosatellite Power System Reviewed

    Alkali, M., Edries, M.Y., Khan, A.R., Masui, H., Cho, M

    65th International Astronautical Congress   2014.09

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    Canada   Toronto   2014.09  -  2014.09

  • Performance evaluation of electric double layer capacitor as energy storage component of micro/nanosatellite on the imposition of varied temperature and vacuum conditions Reviewed

    ALKALI, M., Edries, M., Almubarak, H., Khan, A.R., Masui, H., Cho, M.

    50th AIAA/ASME/SAE/ASEE Joint Propulsion conference   2014.07

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    USA   Cleveland   2014.07  -  2014.07

    DOI: 10.2514/6.2014-3420

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  • On-orbit Potential Measurement of H-II Transfer Vehicle Reviewed

    T. Okumura, D. Tsujita, Y. Kobayashi, K. Koga, M. Takahashi, H. Kusawake, T. Kasai, H. Uematsu, H. Masui, A. Khan, M. Cho

    13th Spacecraft Charging Technology Conference   2014.06

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    USA   Pasadena   2014.06  -  2014.06

  • Flight Results of High Voltage Technology Demonstration Satellite HORYU-II Reviewed

    M. Cho, H. Masui, A. R. Khan, M. Iwata, K. Toyoda, Kyutech Satellite Project

    13th Spacecraft Charging Technology Conference   2014.06

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    USA   Pasadena   2014.06  -  2014.06

  • Laboratory Tests to Standardize Environment Test Conditions of Micro/Nano Satellite Units Reviewed

    A. Batsuren, K. Tomida, T. Hatamura, H. Masui M. Cho

    Transactions of JSASS, Aerospace Technology Japan   2014.04

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  • Environmental Tests of Lithium-ion Capacitor for Very High Power In-Orbit Applications Reviewed

    Shimizu, T., Finnholm, J., Motohata, T., Masui, H., Coronius, T., Kestila, A., Cho, M

    10th European Space Power Conference   2014.04

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    Noordwijkerhout   Netherlands   2014.04  -  2014.04

  • Three hundred fifty volt photovoltaic power generation in low Earth orbit Reviewed

    51 ( 1 )   379 - 381   2014.01

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    DOI: 10.2514/1.A32559

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  • Low cost thermal-vacuum system for the development of very small spacecraft Reviewed

    8   5903 - 5906   2014.01

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  • Basic research on radiation tests suitable for nano-satellites Reviewed

    11   8048 - 8051   2014.01

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  • Laboratory Tests to Standardize Environment Test Conditions of Micro/Nano Satellite Units Reviewed

    BATSUREN Amgalanbat, TOMIDA Kenta, HATAMURA Toru, MASUI Hirokazu, CHO Mengu

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   12 ( 29 )   Pf_1 - Pf_10   2014.01

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    DOI: 10.2322/tastj.12.Pf_1

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  • Ground Tests and In-Orbit Results for the Horyu-II Nanosatellite Power System Reviewed

    OKADA Kazuya, SERI Yuki, SHIBAGAKI Ryunosuke, Satellite Project Kyutech, MASUI Hirokazu, CHO Mengu

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   12 ( 29 )   Tf_49 - Tf_56   2014.01

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    DOI: 10.2322/tastj.12.Tf_49

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  • Erratum for "Laboratory Tests to Standardize Environment Test Conditions of Micro/Nano Satellite Units" [Trans. JSASS Aerospace Tech. Japan Vol. 12, No. ists29, pp. Pf_1-Pf_10, 2014] Reviewed

    BATSUREN Amgalanbat, TOMIDA Kenta, HATAMURA Toru, MASUI Hirokazu, CHO Mengu

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   12 ( 29 )   Pf_39 - Pf_40   2014.01

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    DOI: 10.2322/tastj.12.Pf_39

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  • Discharge Observation on Antenna Surface Radiating High-power Microwaves in Simulated Space Environment Reviewed

    WOO Hyounggwan, KHAN Arifur R., MASUI Hirokazu, CHO Mengu, MIYAKAWA Takehiro, FUJITA Tatsuhito

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   12 ( 0 )   11 - 19   2014.01

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    DOI: 10.2322/tastj.12.11

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  • 350-V Photovoltaic Power Generation in Low Earth Orbit Reviewed

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

    Journal of Spacecraft and Rockets   2013.12

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  • Nano-satellite development project and space engineering education at Kyushu Institute of Technology Reviewed

    1059 - 1063   2013.09

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    DOI: 10.1109/RAST.2013.6581159

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  • On-orbit data analysis of high voltage technology demonstration satellite HORYU-II Reviewed

    2013.08

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  • 超小型衛星「鳳龍弐号」の試験・検証と軌道上不具合原因究明 Reviewed

    M. Cho, H. Masui, Kyutech Satellite Project

    Aerospace Technology   2013.04

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  • On-Orbit Data Analysis of High Voltage Technology Demonstration Satellite HORYU-II Reviewed

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

    51st AIAA Aerospace Sciences Meeting   2013.01

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    USA   Grapevine   2013.01.07  -  2013.01.10

  • Mission results of high voltage technology demonstration satellite "HORYU-2 Reviewed

    12   9377 - 9391   2013.01

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  • Measurement of atomic-oxygen flux distribution Reviewed

    32   597 - 606   2013.01

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    DOI: 10.1007/978-3-642-30229-9_56

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  • Anomaly investigation of HORYU-II and lessons learned Reviewed

    6   4211 - 4218   2013.01

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  • Preliminary report on on-orbit experiment on high voltage technology demonstration satellite, HORYU-II Reviewed

    12   9657 - 9667   2012.12

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  • Discharge observation on antenna surface radiating high power microwave in plasma environment Reviewed

    9   7029 - 7037   2012.12

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  • Development of mission payloads onboard high voltage technology demonstration satellite HORYU-II Reviewed

    2012.12

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    DOI: 10.2514/6.2012-719

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  • Environment Test Campaign of Micro/Nano-Satellite Power Control Unit Reviewed

    K. Okada, T. Motohata, T. Hatamura, S. Obata, H. Masui, M. Cho

    4th UN-Japan Nano-Satellite Symposium   2012.10

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    Japan   Nagoya   2012.10  -  2012.10

  • Discharge observation on antenna surface radiating high power microwave in plasma environment Reviewed

    H. Woo, A. R. Khan, H. Masui, M. Cho, T. Miyakawa, T. Fujita

    63rd International Astronautical Congress   2012.10

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    Italy   Naples   2012.10  -  2012.10

  • Preliminary Report on On-orbit Experiment on High Voltage Technology Demonstration Satellite, HORYU-II Reviewed

    A. Takahashi, A. R. Khan, M. Hirokazu, M. Iwata, K. Toyoda, M. Cho,

    63rd International Astronautical Congress   2012.10

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    Italy   Naples   2012.10  -  2012.10

  • nvironment Test Campaign of Micro/Nano-Satellite Radio Frequency Components Reviewed

    K. Tomida, T. Hatamura, H. Masui, M. Cho

    4th UN-Japan Nano-Satellite Symposium   2012.10

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    Japan   Nagoya   2012.10  -  2012.10

  • On-orbit Demonstration of High Voltage Technology Mission in HORYU-II Reviewed

    A. Takahashi, A. R. Khan, M. Hirokazu, M. Iwata, K. Toyoda, M. Cho

    4th UN-Japan Nano-Satellite Symposium   2012.10

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    Japan   Nagoya   2012.10  -  2012.10

  • Path finder radiation test suitable for micro or nano satellite Reviewed

    Y. Okumura, M. Cho, H. Masui

    4th UN-Japan Nano-Satellite Symposium   2012.10

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    Japan   Nagoya   2012.10  -  2012.10

  • Measurement of vibration acceleration distribution within micro/nano satellites for environment test standardization Reviewed

    A. Batsuren, T. Hatamura, H. Masui, M. Cho

    4th UN-Japan Nano-Satellite Symposium   2012.10

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    Japan   Nagoya   2012.10  -  2012.10

  • Status of Micro/Nano satellite Environmental Tests Standardization Project: Test Campaign and Standard Draft Reviewed

    M. Cho, H. Masui, T. Hatamura, K. Date, S. Horii, S. Obata

    4th Nanosatellite Symposium   2012.10

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    Japan   Nagoya   2012.10  -  2012.10

  • Overview of Nano-satellite Environmental Tests Standardization Project: Test Campaign and Standard Draft Reviewed

    M. Cho, H. Masui, T. Hatamura, K. Date, S. Horii, S. Obata

    26th Small Satellite Conference   2012.08

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    USA   Utah   2012.08  -  2012.08

  • Research on mitigation method against secondary arcing on solar array by capacitor and inductance Reviewed

    I. Haruta, H. Masui, K. Toyoda, M. Cho

    12th Spacecraft Charging Technology Conference   2012.05

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    Japan   Kitakyushu   2012.05  -  2012.05

  • Research on mitigation method against secondary arcing on solar array by capacitor and inductance Reviewed

    I. Haruta, H. Masui, K. Toyoda, M. Cho

    12th Spacecraft Charging Technology Conference   2012.05

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    Japan   Kitakshu   2012.05  -  2012.05

  • Principle Verification of Space Debris Removal Method Using Interaction between Space Plasma and Electrode Reviewed

    R. Sasaki, H. Masui, K. Toyoda, M. Cho,

    12th Spacecraft Charging Technology Conference   2012.05

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    Japan   Kitakyushu   2012.05  -  2012.05

  • Experimental investigation of mitigation method of flashover discharge on solar array Reviewed

    S. Miyazaki, H. Masui, K. Toyoda, M. Cho

    12th Spacecraft Charging Technology Conference   2012.05

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    Japan   Kitakyushu   2012.05  -  2012.05

  • Discharge phenomena on antenna surface radiating microwave in plasma environment Reviewed

    12th Spacecraft Charging Technology Conference   2012.05

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    Japan   Kitakyushu   2012.05  -  2012.05

  • Development of Mission Payloads onboard High Voltage Technology Demonstration Satellite HORYU-II Reviewed

    T. Yoke, A. R. Khan, H. Masui, M. Iwata, K. Toyoda, M. Cho

    12th Spacecraft Charging Technology Conference   2012.05

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    Japan   Kitakyushu   2012.05  -  2012.05

  • Measurement of Atomic Oxygen Flux Distribution Reviewed

    T. Hisashiba, H. Masui, M. Iwata, K. Toyoda, M. Cho

    12th Spacecraft Charging Technology Conference   2012.05

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    Japan   Kitakyushu   2012.05  -  2012.05

  • Development of flashover current simulator for ESD ground testing simulating GEO environment Reviewed

    K. Toyoda, T. Suzuki, T. Endo, H. Masui, M. Cho

    IEEE Trans on Plasma Science   2012.02

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    DOI: 10.1109/TPS.2011.2179813

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  • Spacecraft Charging Analysis of Large GEO Satellites Using MUSCAT Reviewed

    M. Cho, T. Sumida, H. Masui, K. Toyoda, J. Kim, S. Hatta, F. Wong, B. Hoang

    IEEE Trans on Plasma Science   2012.02

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    DOI: 10.1109/TPS.2012.2187074

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  • Electrostatic Discharge Tests of Solar Array Coupons With Different String-to-String Gaps without RTV Adhesive Grout Reviewed

    H. Masui, T. Endo, K. Toyoda, M. Cho, F. Wong, B. Hoang, T. Redick

    IEEE Trans on Plasma Science   2012.02

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    DOI: 10.1109/TPS.2011.2176754

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  • Research and Development of a Debris Removal Method Using Interaction between Space and Electrode with Applied Voltage Reviewed

    SASAKI Reiso, MASUI Hirokazu, TOYODA Kazuhiro, CHO Mengu

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   10 ( 28 )   Tr_47 - Tr_51   2012.01

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    DOI: 10.2322/tastj.10.Tr_47

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  • B3 Activity of Laboratory of Spacecraft Environment Interaction Engineering in Kyushu Institute of Technology : Spacecraft charging, Space Debris and Small Satellite Development Reviewed

    Masui Hirokazu, Cho Mengu, Akahoshi Yasuhiro, Toyoda Kazuhiro, Iwata Minoru, Khan Arifur Rahman, Chen Yu, Endo Taishi

    The Proceedings of the Space Engineering Conference ( The Japan Society of Mechanical Engineers )   2010 ( 0 )   _B3 - 1_-_B3-4_   2011.01

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    Laboratory of Spacecraft Environment Interaction Engineering (LaSEINE) in Kyushu Institute of Technology in researching spacecraft charging and arcing, space debris and small satellite. Laboratory of Spacecraft Environment Interaction Engineering has test facilities specialized space environment and provides the education for the space environment. In particular to spacecraft charging and arcing, the solar array panel made in Japan and abroad were tested. The laboratory is one of the world's leading authorities on spacecraft charging and arcing. Recently, the environment test facilities for a small satellite are developed. These facilities can provide most of test environments required small satellites. In this presentation, our past results and future plan will be reported.

    DOI: 10.1299/jsmesec.2010.19._B3-1_

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  • Development of a Numerical Simulation Code for Microwave Discharge Ion Thrusters Reviewed

    YAMAMOTO Naoji, MASUI Hirokazu, KANAGAWA Takayasu, SHINTANI Syo, NAKASHIMA Hideki

    Aeronautical and Space Sciences Japan ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )   59 ( 691 )   238 - 243   2011.01

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    DOI: 10.14822/kjsass.59.691_238

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  • Effect of Atomic Oxygen Exposure on Surface Resistivity Change of Spacecraft Insulator Material Reviewed

    MUNDARI Noor Danish Ahrar, KHAN Arifur Rahman, CHIGA Masaru, OKUMURA Teppei, MASUI Hirokazu, IWATA Minoru, TOYODA Kazuhiro, CHO Mengu

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   ( 9 )   1 - 8   2011.01

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    DOI: 10.2322/tastj.9.1

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  • Electrostatic discharge test with simulated coverglass flashover for multi-junction GaAs/Ge solar array design Reviewed

    1118 - 1123   2010.12

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    DOI: 10.1109/PVSC.2010.5614721

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  • Preliminary experiments for establishing an ESD ground testing method of solar array Reviewed

    2010.12

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  • Characterization Experiments of Secondary Arcs on Solar Arrays: Threshold and Duration Reviewed

    H. Masui, T. Kitamura, T. Ose, K. Toyoda, M. Cho

    Journal of Spacecraft and Rockets   2010.06

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    DOI: 10.2514/1.49571

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  • Effect of atomic oxygen exposure on resistivity change on spacecraft insulator materials Reviewed

    N. Mundari, A. R. Khan, M. Chiga, T. Okumura, H. Masui, M. Iwata, K. Toyoda, M. Cho

    Trans. JSASS Aerospace Tech. Japan   2010.02

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  • Research on Mitigation Method against Secondary Arcing on Solar Array Reviewed

    WADA Tomohiro, MASUI Hirokazu, TOYODA Kazuhiro, CHO Mengu

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN   8 ( 27 )   Pr_2_19 - Pr_2_24   2010.01

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    DOI: 10.2322/tastj.8.Pr_2_19

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  • Preliminary investigation of space debris removal method using electrostatic force in space plasma Reviewed

    Toyoda K., Furukawa Y., Okumura T., Masui H., Cho M.

    47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition   2009.12

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    Space debris is a space object which is not useful and can cause accident in space. Space debris is moving with high speed with average velocity of 10km/s, which can cause damages to the spacecraft and the astronaut operating outside satellite. The method of removing the debris is demanded for our safety operation in space. In this paper, a debris removal method was proposed for small diameter less than 1mm. This method utilizes the interaction between the electrode biased in positive and space ambient plasma in LEO. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.

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  • Secondary arc threshold meaurement on solar arrays for Japanese spacecraft charging guideline Reviewed

    Masui H., Toyoda K., Cho M.

    47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition   2009.12

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    In this paper, we report about the test results on coupons made for Working Group 1(WG1), which was established to make a Japanese guideline for spacecraft charging design. In particular, the test for a sustained arc was conducted. The sustained arc is one of problem in present satellites. Laboratory tests were carried out with an external circuit simulating a spacecraft power system. The solar array coupon panels simulating the hot and return ends of a string circuit were tested under various combinations of string voltage and string current. We revealed that the threshold conditions for sustained arc were different in string voltage. We show the rating sheet of threshold for sustained arc. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.

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  • Preliminary study of development of space debris removal method using electrostatic force Reviewed

    Furukawa Y., Masui H., Toyoda K., Cho M.

    60th International Astronautical Congress 2009, IAC 2009   7   5772 - 5776   2009.12

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    It was verified that the copper powder is charged negatively using plasma. We analyzed the negative charging of the particle in an electron sheath in plasma. It was confirmed that copper powder is charged negatively in electron sheath making by net biased positively. Further, it was also confirmed that negatively charged copper powder is dragged by electrostatic force.

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  • Spectroscopic Measurement of Secondary Arc Plasma on Solar Array Reviewed

    T. Ose, K. Toyoda, H. Masui, M. Cho

    Transactions of JSASS, Space Technology Japan   2009.11

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  • Environmental Effects on Solar Array Electrostatic Discharge Current Waveforms and Test Results Reviewed

    T. Okumura, H. Masui, K. Toyoda, K. Nitta, M. Imaizumi, M. Cho

    Journal of Spacecraft and Rockets   2009.05

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  • Environmental effects on solar array electrostatic discharge current waveforms and test results Reviewed

    Okumura T., Masui H., Toyoda K., Cho M., Nitta K., Imaizumi M.

    Journal of Spacecraft and Rockets   46 ( 3 )   697 - 705   2009.05

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    A solar array electrostatic discharge ground test is necessary to assure spacecraft reliability in orbit. Laboratory experiments were carried out to characterize an electrostatic discharge current waveform with different background pressures and charging environments to identify the importance of the test setup. The waveform strongly depended on the background pressure. This difference can affect the result of the solar cell degradation test. However, in the case of the secondary arc test, the difference of the primary arc current waveform did not affect the duration of the secondary arc. The current available from a power supply mostly determined the duration of the secondary, irrespective of the test environment. Methods to control the primary arc current supplied by an external capacitance are proposed. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

    DOI: 10.2514/1.41696

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  • ESD Ground Testing of Triple-Junction Solar Cells with Monolithic Diodes Reviewed

    Y. Nozaki, H. Masui, K. Toyoda, M. Cho, H. Watabe

    Transactions of JSASS, Space Technology Japan   2009.03

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  • Statistical Number of Primary Discharges Required for Solar Array Secondary Arc Tests Reviewed

    M. Cho, T. Kitamura, T. Ose, H. Masui, K. Toyoda

    Journal of Spacecraft and Rockets   2009.03

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  • Statistical number of primary discharges required for solar array secondary-arc tests Reviewed

    Cho M., Kitamura T., Ose T., Masui H., Toyoda K.

    Journal of Spacecraft and Rockets   46 ( 2 )   438 - 448   2009.03

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    In the present paper, we propose a method to assess the risk of a secondary arc on a solar array in orbit based on statistical theory. Ground experiments have been carried out to investigate the statistics of temporary-sustained-arc duration. We have found that secondary-arc duration can be modeled as a combination of multiple Poisson distributions. Once we know the formula of the Poisson distribution, we can easily calculate the probability of a secondary arc lasting longer than an acceptable l imit. The quantity of secondary-arc- duration data needed to define the Poisson distribution formula has been discussed. Assuming that thousands or tens of thousands of primary arcs occur in orbit, if the average duration of secondary arcs in the test is less than 5% of the acceptable limit for secondary-arc duration, we can greatly reduce the number of experimental trials to 10 or less in most cases. © 2008 by the American Institute of Aeronautics and Astronautics, Inc.

    DOI: 10.2514/1.37798

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  • ESD Ground Testing of Triple-Junction Space Solar Cells with Monolithic Diodes Reviewed

    NOZAKI Yukishige, MASUI Hirokazu, TOYODA Kazuhiro, CHO Mengu, WATABE Hirokazu

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN   ( 7 )   11 - 17   2009.01

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    DOI: 10.2322/tstj.7.11

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  • Spectroscopic Measurement of Secondary Arc Plasma on Solar Array Reviewed

    OSE Takayuki, TOYODA Kazuhiro, MASUI Hirokazu, CHO Mengu

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN   7 ( 26 )   Pr_2_41 - Pr_2_46   2009.01

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    DOI: 10.2322/tstj.7.Pr_2_41

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  • Generation of LEO-type atomic oxygen environment in laboratory for charging property database Reviewed

    Danish N., Okumura T., Masui H., Iwata M., Toyoda K., Cho M.

    International Astronautical Federation - 59th International Astronautical Congress 2008, IAC 2008   9   5874 - 5878   2008.12

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    Spacecraft in LEO sweep through a rarefied atmosphere composed primarily of atomic oxygen. Even though the densities are low at these altitudes, the spacecraft surface can experience relatively high incident flux (1019 to 1021 m-2 s-1) of energetic (5 eV translational energy) oxygen atom because of high orbital velocities (8kms -1). Most hydrocarbon polymer and active metals are highly reactive towards the atomic oxygen which affects their chemical, electrical, optical and mechanical properties. We are in the process of designing a facility to simulate the space environment of atomic oxygen. Our aim is to simulate the quick degradation of materials and study the secondary electron emission co-efficient, bulk conductivity and photoelectron emission of degraded materials as they play an important role in discharging and arching phenomenon observed on surface of solar panel. We get high velocity of oxygen in an evacuated hypersonic nozzle. The oxygen is broken down in atomic oxygen using high power C02 laser. The energy of the atomic oxygen is measured using TOF QMAS technique. The flux of oxygen atom is measured using Quartz Crystal Microbalance (QCM). The O- atom source is used to irradiate the sample material used in spacecraft surface.

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  • Electrostatic discharge plasma propagation speed on solar panel in simulated geosynchronous environment Reviewed

    Masui H., Toyoda K., Cho M.

    IEEE Transactions on Plasma Science   36 ( 5 PART 2 )   2387 - 2394   2008.11

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    An international project has started to establish an International organization for standardization standard for the electrostatic discharge (ESD) on the solar array panel. For the ESD ground test of satellite solar panel, it is important to understand the characteristics of a primary arc discharge. A solar array coupon made of triple-junction cells is used to understand the primary arc characteristics. In particular, the experiment focuses on the measurement of the propagation speed of plasma generated by the primary arc. The plasma propagation is analyzed using images captured by a high-speed video camera and an image intensified camera. The plasma propagation speed derived from discharge images decreases in proportion to the inverse of the square root of time. The arc current waveform assuming the decreasing speed agreed with the experiment waveform very well. © 2008 IEEE.

    DOI: 10.1109/TPS.2008.2003191

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  • ESD ground test of solar array coupons for a greenhouse gases observing satellite in PEO Reviewed

    Toyoda K., Masui H., Muranaka T., Cho M., Urabe T., Miura T., Kawakita S., Gonohe Y., Kikuchi T.

    IEEE Transactions on Plasma Science   36 ( 5 PART 2 )   2413 - 2424   2008.11

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    An electrostatic discharge test was carried out on a solar array paddle (SAP) for the Greenhouse gases Observing SATellite (GOSAT) on a simulated polar Earth orbit (PEO) environment. To simulate the spacecraft charging conditions in a PEO with an auroral band, when electrons with higher energy than LEO plasma flow to the Earth, three conditions of dielectric charging can be considered on each side of the SAP. At first, the threshold voltage differences of discharge inception were measured experimentally using solar array coupons simulating both the beginning and the end of life under six charging conditions. Next, the Multiutility Spacecraft Charging Analysis Tool was employed to analyze the spacecraft surface potential and the time needed for charging. From the threshold value and the charging analysis, the probability and the number of discharges were estimated in each charging condition during a lifetime of the GOSAT. Finally, the performance of the coupons against discharges was evaluated for each charging condition. All coupons had no sustained arc during these tests; however, there was some electrical degradation of the solar cell. The power degradation during the lifetime of the GOSAT was estimated from these results, and the design of the solar array coupon was confirmed to satisfy the power demand even if the estimated number of discharges occurs in the lifetime. © 2008 IEEE.

    DOI: 10.1109/TPS.2008.2002823

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  • Electrostatic Discharge Plasma Propagation Speed on Solar Panel in Simulated Geosynchronous Environment Reviewed

    H. Masui, K. Toyoda, M. Cho

    IEEE Transactions on Plasma Science   2008.10

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  • Probability distribution of secondary arc duration on solar array Reviewed

    Cho M., Kitamura T., Ose T., Masui H., Toyoda K.

    46th AIAA Aerospace Sciences Meeting and Exhibit   2008.01

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    Secondary arc on satellite solar array is sometimes fatal to spacecraft operation by damaging insulation of solar array string circuit. A proper ground test method is necessary to correctly assess the risk of secondary arc from the probability of occurrence in orbit. Ground experiments are carried out to investigate the statistics of temporary sustained arc duration. It is found that the secondary arc duration can be modeled as a combination of multiple Poisson distributions. Once we know the formula of the Poisson distribution, we can easily calculate the probability of secondary arc lasting longer than an acceptable limit, drastically reducing the testing cost. The number of secondary arc duration data to define the Poisson distribution formula is also discussed. Copyright © 2008 by the American Institute of Aeronautics and Astronautics, Inc.

    DOI: 10.2514/6.2008-455

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  • Degradation of Electric Performance Due to Electrostatic Discharge on Silicon Solar Cell for Space Reviewed

    OKUMURA Teppei, MASUI Hirokazu, TOYODA Kazuhiro, CHO Mengu, IMAIZUMI Mitsuru

    JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )   55 ( 647 )   590 - 596   2007.12

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    Electrostatic discharge (ESD) occurs on the solar array due to space plasma interaction. It is considered that solar cell suffers degradation of electric performance, once ESD occurs at the solar cell edge. In order to study the degradation of solar cell electrical performance, we performed ESD tests on Si solar cell in a vacuum chamber. After the ESD tests the solar cell maximum power decreased. We found the damage on surface electrode in the vicinity of ESD spot. Infrared emission due to current leak was found at the spot. The solar cell degraded due to the leak resistance produced by ESD.

    DOI: 10.2322/jjsass.55.590

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  • Effects of Magnetic Field Configuration on Thrust Performance in A Miniature Microwave Discharge Ion Thruster Reviewed

    N. Yamamoto, S. Kondo, T. Chikaoka, H. Masui, H. Nakashima

    Journal of Applied Physics   2007.12

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  • 宇宙用シリコン太陽電池の放電による電気性能劣化 Reviewed

    奥村哲平, 増井博一, 豊田和弘, 今泉充, 趙孟佑

    日本航空宇宙学会論文集   2007.12

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  • Development of electron emitting film for spacecraft charging mitigation Reviewed

    Iwata M., Igawa H., Sanmaru Y., Masui H., Toyoda K., Cho M., Sato T., Hatta S., Fujita T., Hisada Y.

    International Astronautical Federation - 58th International Astronautical Congress 2007   8   5225 - 5230   2007.12

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    Electrostatic discharge on solar array is one of the primary causes of spacecraft anomalies. Such discharges occur due to anomalous surface charging, which means that parts of the dielectric surface on a satellite have different potential from the satellite body potential. Therefore, by preventing to making the potential of the spacecraft negative, we can avoid the discharges on solar array. In this paper, we present the mitigation strategy of spacecraft negative charging via electron emitting film. The electron emission device emits electrons from the spacecraft structure via field emission. The electron emission device prevents the spacecraft potential from falling negative. We have evaluated the mitigation performance of the device and confirmed that the field emission device mitigates the negative charging. Copyright IAF/IAA. All rights reserved.

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  • Effects of magnetic field configuration on thrust performance in a miniature microwave discharge ion thruster Reviewed

    Yamamoto N., Kondo S., Chikaoka T., Nakashima H., Masui H.

    Journal of Applied Physics   102 ( 12 )   2007.12

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    The effects of magnetic field configuration on thrust performance in a miniature microwave discharge ion thruster were investigated in order to improve thrust performance. First, the extracted ion beam current was measured for various levels of strength of the magnetic field. It was found that there is an optimum magnitude of the magnetic field. That this is due to the tradeoff between magnetic mirror confinement and microwave-plasma coupling was confirmed by measurement of the ion saturation current into the antenna of the ion thruster. The ion saturation current was found to decrease with an increase in magnetic field strength, due to the improvement in magnetic mirror confinement. The estimated electron temperature also decreases with an increase in magnetic field strength. This result shows that the increase in magnetic field strength leads to a decrease in microwave-plasma coupling. Next, the ion beam current for three magnetic field shapes was measured by changing the length of the central yoke. The results show that the optimum magnetic field shape depends on the mass flow rate because of the tradeoff between magnetic confinement and ionization probability. For the configurations tested, the 3 mm length central yoke is optimal for low mass flow, whereas 7 mm is the best for high mass flow. Overall, the extracted ion beam current is 21.4 mA, at a xenon mass flow rate of 0.036 mg/s, beam voltage of 1500 V, and incident microwave power of 16 W. © 2007 American Institute of Physics.

    DOI: 10.1063/1.2822456

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  • 均一・高密度プラズマ生成アンテナを用いたマイクロ波放電型イオンスラスタの高性能化 Reviewed

    山本直嗣, 三好誠,増井博一,宮本尚使, 宗貞伸孝, 中島秀紀

    日本航空宇宙学会論文集   2007.11

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  • Laboratory test campaign for ISO standardization of solar array ESD test methods Reviewed

    Masui H., Kitamura T., Okumura T., Toyoda K., Cho M.

    Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting   5   3446 - 3453   2007.07

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    An electrostatic discharge (ESD) on a solar array causes a serious damage for a satellite. The effective ground test is required to ensure a safety of the satellite. To establish the ground test method, an international project is being proceeding by Japan, Europe and US. In the project three types of test coupons are used for verification of plasma propagation, degradation of cell and occurrence of secondary arc, respectively. This paper introduces ESD test methods, experimental systems and experimental results in Kyushu Institute of Technology of Japan.

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  • Analysis of electron and microwave behavior in microwave discharge neutralizer Reviewed

    Masui H., Tashiro Y., Yamamoto N., Nakashima H., Funaki I.

    Transactions of the Japan Society for Aeronautical and Space Sciences   49 ( 164 )   87 - 93   2006.12

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    In the MUCES-C mission conducted by JAXA (Japan Aero Exploration Agency), a microwave neutralizer is mounted with a microwave ion engine on the HAYABUSA space probe. The neutralizer consists of an L-shaped antenna to inject microwaves and samarium cobalt magnets to provide ECR (electron cyclotron resonance). Plasma production of a higher density than the cutoff density is expected in the discharge chamber, but the neutralizer is so small that high-precision measurements using a probe are difficult. To clarify the plasma production mechanism in the microwave neutralizer, numerical analysis was conducted using u code coupling PIC (particle-in-cell) method, and a FDTD (finite-difference-time-domain) method. This paper describes effects caused by varying magnetic field configuration and antenna position in the neutralizer. The calculation results show that bringing the antenna closer to the ECR region is effective for plasma production. © 2006 The Japan Society for Aeronautical and Space Sciences.

    DOI: 10.2322/tjsass.49.87

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  • Magnetic field design in miniature microwave discharge ion engines Reviewed

    Yamamoto N., Chikaoka T., Kondo S., Masui H., Nakashima H., Yoshiyuki T.

    Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference   10   8172 - 8178   2006.12

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    The effect of magnetic field configuration on thrust performance in a 30 W class miniature microwave discharge ion engine was investigated with the objective of improving its thrust performance. The ion beam current with various magnitude of magnetic field was measured, since magnetic confinement and microwave - plasma coupling could be affected by the magnetic field configuration. The ion beam current is increased with the increase in the number of magnets and there is an optimum magnitude of magnetic field. The thrust performance of the miniature microwave discharge ion engine, propellant utilization, and ion beam production cost were 0.67 and 660 W/A, respectively at mass flow rate =0.02 mg/s, and incident microwave power= 8 W.

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  • Performance test of micro ion thruster using microwave discharge Reviewed

    Takao Y., Kataharada H., Miyamoto T., Masui H., Yamamoto N., Nakashima H.

    Vacuum   80 ( 11-12 )   1239 - 1243   2006.09

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    Several types of electric propulsions have been developed and used for artificial satellites on geostationary orbit keeping or planetary exploration. A series of small-scale satellites is recently expected to be used instead of traditional large-scale satellites for reducing launch cost and risk. The trend towards needs of small spacecraft requires micro thrusters with high specific impulse. In this study, a micro ion engine utilizing a microwave discharge plasma was fabricated and was tested. This ion engine comprises some components, such as electrostatic grids, antenna, and microwave power supply, which decide its performance. The performance dependence on the components was examined under several experimental conditions. The typical performance parameters of the engine were ion production cost of 770 V, propellant utilization efficiency of 72%, and thrust of 0.66 mN in conditions of input 2.45 GHz microwave power of 8 W and propellant (xenon gas) flow rate of 0.2 sccm with a star type antenna. © 2006 Elsevier Ltd. All rights reserved.

    DOI: 10.1016/j.vacuum.2006.01.071

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  • Analysis of Electron and Microwave Behaviors in Microwave Discharge Neutralizer Reviewed

    H. Masui, Y. Tashiro, N. Yamamoto, H. Nakashima, I. Funaki

    Transactions of the Japan Society for Aeronautical and Space Sciences   2006.08

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  • Antenna configuration effects on thrust performance of miniature microwave discharge ion engine Reviewed

    Yamamoto N., Masui H., Kataharada H., Nakashima H., Takao Y.

    Journal of Propulsion and Power   22 ( 4 )   925 - 928   2006.07

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    The effects of antenna configuration on the thrust performance of a 30-W-class miniature microwave discharge ion engine were investigated. The ion beam currents were measured for three different antenna configurations such as disc, star, and cross antennas. The ion beam current of the star antenna was the largest among the three configurations and that of the disc antenna was the smallest. The effect of good coupling with plasma exceeded the effect of large losses on the antenna surface under low mass flow rate with low plasma density. The effect of large losses on the antenna surface also exceeded the effect of good coupling with plasma under high mass flow rate. The results showed that the optimum antenna shape depends on the desired mass flow level due to the tradeoff between microwave plasma coupling efficiency and surface-area recombination. It was also found that the disc antenna was the best at low mass flow rate and the star antenna was the best at high mass flow rate.

    DOI: 10.2514/1.18833

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  • Antenna Configuration Effects on Thrust Performance of Miniature Microwave Discharge Ion Engine Reviewed

    N. Yamamoto, H. Masui, H. Kataharada, Y. Takao and H. Nakashima

    Journal of Propulsion and Power   2006.06

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  • Numerical analysis of microwave ion engine using electromagnetic particle code Reviewed

    Masui H., Tanoue T., Nakashima H., Funaki I.

    Thin Solid Films   506-507   609 - 612   2006.05

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    A simulation code has been developed for analyzing plasma behavior and microwave propagation in a microwave ion engine. The code consists of PIC (particle-in-cell) method and FDTD (finite-difference-time-domain) method. In the present study, 10-cm-class microwave ion engine developed by the Japan Aerospace Exploration Agency (JAXA) is adopted as a calculation model. The microwave propagations in the discharge chamber are compared under boundary conditions such as absorption and reflection. In the calculation with plasma, effect of boundary condition on electron energy is investigated. As a result, it is found that increase of electron energy is larger for reflection boundary condition than absorption one. © 2005 Elsevier B.V. All rights reserved.

    DOI: 10.1016/j.tsf.2005.08.046

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  • Numerical Analysis of Microwave Ion Engine Using Electromagnetic Particle Code Reviewed

    2006.05

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  • Electromagnetic field analysis for microwave discharge ion engine using multi mono-poles antenna system Reviewed

    Izumi K., Masui H., Shinyashiki K., Yamamoto N., Nakashima H.

    International Astronautical Federation - 56th International Astronautical Congress 2005   7   4703 - 4707   2005.12

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    We report here on an optimal configuration of antennas using multi mono-pole systems. In order to optimize the position and length of antenna, the transmission efficiency are analyzed by finite difference time domain (FDTD) method, which is known for its usefulness and simplicity to calculate to electromagnetic field. The relation between the antenna length and transmission efficiency was investigated. First this report shows that experimental data up to now. Then the microwave transmission is calculated by using poynting vector. When transmission value of microwave is calculated, we varied the parameters such as antenna length, yoke length and number of antennas respectively. Finally, we obtain on guiding design principle of ion engines by comparing experimental data and numerical calculation conclusions.

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  • Development of small-scale microwave discharge ion thruster Reviewed

    Takao Y., Masui H., Miyamoto T., Kataharada H., Ijiri H., Nakashima H.

    Vacuum   73 ( 3-4 )   449 - 454   2004.04

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    Study of a small-scale ion engine (diameter of 2.5 cm, input microwave power up to 25 W) utilizing microwave-discharged plasma for space propulsion is reported. The ion extraction tests are conducted under several conditions such as the input microwave power range of 15-25 W, the Ar gas (as propellant) flow rate range of 1.5-3.5 sccm, and two types of antenna shape (L-type or disk antenna). In the tests, ion beam currents and distributions of ion beam current density are measured. As a result, maximum ion current of 8.2 mA is attained at input power of 25 W and Ar gas flow rate of 3.15 sccm with the L-type antenna. Ion production cost and propellant utilization efficiency are estimated from the ion current measurements to examine performances of the thruster. The plasma parameter measurements of electron temperature and density in the plasma source are also carried out. © 2004 Elsevier Ltd. All rights reserved.

    DOI: 10.1016/j.vacuum.2003.12.066

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