Updated on 2022/08/03

 
TOYODA kazuhiro
 
Scopus Paper Info  
Total Paper Count: 0  Total Citation Count: 0  h-index: 9

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

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

Research Interests

  • satellite

  • charging

  • discharge

  • plasma

  • solar array

  • spacecraft

Research Areas

  • Frontier Technology (Aerospace Engineering, Marine and Maritime Engineering) / Aerospace engineering

  • Energy Engineering / Fundamental plasma

Degree

  • The University of Tokyo  -  Doctor of Engineering   2001.03

Biography in Kyutech

  • 2021.04
     

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

  • 2019.04
    -
    2021.03
     

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

  • 2010.04
    -
    2019.03
     

    Kyushu Institute of Technology   Faculty of Engineering   Department of Electrical Engineering and Electronics   Associate Professor  

Papers

  • Multicomponent Plasma Expansion Model for Arc Discharges on Large-Area Solar Arrays Reviewed International journal

    Katz I., Hoang B., Toyoda K.

    Journal of Spacecraft and Rockets   59 ( 1 )   324 - 332   2022.09

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    Authorship:Last author   Language:English   Publishing type:Research paper (scientific journal)

    DOI: 10.2514/1.A35163

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  • Difference in threshold voltage of arc inception between electron beam and ultraviolet environment: surface potential measurement with Pockels effect Reviewed

    Toyoda K., Kose S., Cho M.

    AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022   2022.01

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

    DOI: 10.2514/6.2022-1989

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  • Difference in discharge threshold voltage between electron beam and ultraviolet environment Reviewed

    Toyoda K., Sasaki T., Cho M., Ohkubo M., Seki K.

    Journal of Spacecraft and Rockets   58 ( 3 )   619 - 627   2021.01

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    DOI: 10.2514/1.A34880

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  • Development of a Direct Drive Vacuum Arc Thruster Passively Ignited for Nano-satellite Reviewed

    CHO MENGU

    IEEE Transactions on Plasma Science   44   100 - 106   2016.01

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    CiNii Research

  • On-Orbit Experimental Result of a Non-Deployable 430-MHz-Band Antenna Using a 1U CubeSat Structure Reviewed International journal

    Nakayama D., Yamauchi T., Masui H., Kim S., Toyoda K., Malmadayalage T.L.D., Cho M.

    Electronics (Switzerland)   11 ( 7 )   2022.04

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

    DOI: 10.3390/electronics11071163

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  • Experimental investigation on particle size and launch angle distribution of lofted dust particles by electrostatic forces Reviewed

    Orger N.C., Toyoda K., Masui H., Cho M.

    Advances in Space Research   68 ( 3 )   1568 - 1581   2021.08

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    Electrostatic dust transportation is one of the fundamental sources for dust activity on airless planetary bodies. Even though a series of laboratory experiments have been performed to improve our understanding of the physics behind the electrostatic dust mobilization, there are several factors to investigate such as the launch angles, the lofted particle sizes, the traveling distance of the lofted grains, the initial acceleration to the launching velocities and so on. In this experimental study, an electron beam is used with 450 eV energy to produce secondary electrons to initiate lofting of the silica microspheres in the vacuum chamber, and the particle trajectories are recorded with a microscopic telescope and a high-speed camera. The dust samples are prepared as a mixture of particles with sizes from several micrometers to approximately 90.0 μm in radius. In addition, a polyimide tape with the adhesive surface is placed around the dust sample to collect the lofted particles up to approximately 10.0 cm distance. The collected silica microspheres are studied under the microscope to measure the size variation over the distance from the dust source. The experiment results show that spherical particles and residues effortlessly reach up to 10 cm distance, whereas the fluffy dust aggregates are observed particularly near the dust sample. In addition, the analysis of trajectories shows that the dust grains accelerate rapidly to their launching velocities below 12.0 ms due to the repulsion between the neighboring dust particles. Finally, the peak of the dust launching angle distribution is determined to be around 43.5–45° from the surface normal.

    DOI: 10.1016/j.asr.2021.03.037

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  • Sulphur‑fuelled Surface Arc Thruster for Propelling Nanosatellites Reviewed International journal

    Senior Shimhanda, Kotaro Hiraka, Taro Inoue, Kazuhiro Toyoda, Mengu Cho

    Advances in Astronautics Science and Technology ( Springer )   4   39 - 46   2021.03

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    DOI: 10.1007/s42423-021-00074-5

  • Difference in discharge threshold voltage between electron beam and ultraviolet environment Reviewed International journal

    Kazuhiro Toyoda, Takaaki Sasaki, Mengu Cho, Mitsuru Okubo, and Kazuyoshi Seki

    Journal of Spacecraft and Rockets   2020.10

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  • Consideration on voltage rising in spacecrafts during flashover discharge Reviewed International journal

    Kazuhiro Toyoda

    Journal of Spacecraft and Rockets   2020.07

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    DOI: 10.2514/1.A34798

  • Sulphur-fuelled surface arc thruster for propelling nanosatellites Reviewed

    Shimhanda S., Hiraka K., Inoue T., Toyoda K., Cho M.

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

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    Pulsed electrothermal thrusters use kiloampere discharge currents for polytetrafluoroethylene (PTFE) ablation and sublimation. However, higher arc currents cause higher electromagnetic interference (EMI). A 10 J surface arc thruster (SAT), which adopts current regulating diodes (CRD), was developed that enables significant reduction in EMI. A CRD limits the discharge currents to 5 A in spite of the applied voltage. A low-melting-point sulphur propellant has been used that enables low discharge currents to efficiently ablate it and accelerate it electrothermally. In this paper, the near-term potential for elemental sulphur propellant in SAT is investigated. The advantages of sulphur with respect to PTFE are presented. First, we measured the pulse width of the main discharge. Then sulphur propellant proved superior to PTFE propellant in discharge duration. The mean pulse widths of PTFE and sulphur are 3.38 ms and 22.1 ms, respectively. Secondly, we measured the pressure rise in the vacuum chamber after each discharge. The mean pressure rises of PTFE, sulphur powder and sulphur solid are 0.43 mPa, 0.94 mPa and 1.9 mPa, respectively. Sulphur powder experienced the least intensity of discoloration in comparison with other propellants. The discharge initiator misfired frequently during PTFE ablation, but it ignited successively during sulphur ablation. Experimental results indicate sulphur is a suitable propellant for surface discharge propulsion, and for low arc currents is superior to PTFE.

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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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    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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  • Difference in threshold voltage of arc inception between electron beam and ultraviolet environment Reviewed

    Toyoda K., Kose S., Sasaki T., Cho M.

    AIAA Scitech 2020 Forum   1 PartF   2020.01

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    As a charging method in ground experiments, an electron beam is often used to simulate high energy particles. In addition to this, a charging method using ultraviolet has been devised because charging by sunlight also occur in the space environment. Accordingly, ultraviolet were used for the discharge threshold measurement experiment of the solar cell, but the large difference of the threshold voltage was seen in two charging methods. The purpose of this research is to find out the cause of this large difference and to apply ultraviolet to charging and discharge experiment of space solar cell. We assumed that the charging potential of the cover glass edge of the solar cell was different in two charging methods and it caused the difference of the discharge threshold voltage. Therefore, we measured the surface potential focusing on the cover glass edge. In the experiment, a sample simulating the structure of the space solar cell was prepared and irradiated with ultraviolet or electron beam until the potential of the cover glass surface did not change overall. The surface potential of the cover glass edge at this time was measured with a contactless surface electrometer, and the results by two charging methods were compared. As a result, it was found that the surface potential at the cover glass edge was different in two charging methods. On the other hand, it was also found that measurement accuracy was low. We devised measurement method using Pockels effect which can measure potential directly or plan to improve measurement accuracy by improving sample because higher measurement accuracy is required to clarify the difference in charging.

    DOI: 10.2514/6.2020-2012

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  • Consideration on voltage rising in spacecrafts during flashover discharge Reviewed

    Toyoda K.

    AIAA Scitech 2020 Forum   1 PartF   1 - 6   2020.01

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    An electrostatic discharge can cause a flashover discharge propagating on a solar array paddle. The flashover electron current flows from a solar cell (cathode) to coverglasses charged positively with respect to the cells. The return current flows from solar array circuits into spacecraft power unit via power cables. This is caused by blocking diodes connected on the positive side of solar array circuit. In the end, the flashover current passes through a bus capacitance inside the spacecraft. The amount charge of flashover current can increase the voltage in the bus capacitance. In this paper, the voltage rising due to flashover current is considered with the combination of flashover current and bus capacitance value.

    DOI: 10.2514/6.2020-2011

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  • Attitude Testing Platform in a Vacuum Environment for a Lean Satellite with an Electric Thruster Reviewed

    Marcos Hernandez-Herrera, Phongsakorn Meemak, Hiroki Hisatsugu, Kotaro Hiraka, Jose Rodrigo Cordova-Alarcon, Sangkyun Kim, Kazuhiro Toyoda, and Mengu Cho

    Journal of Small Satellites   8 ( 2 )   849 - 858   2019.09

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  • Electrostatic Discharge Experiment Results on Ground Using Experiment Model of HORYU-IV Reviewed International journal

    Hiroshi Fukuda, Tatsuo Shimizu, Kazuhiro Toyoda, and Mengu Cho

    Journal of Spacecraft and Rockets   56 ( 6 )   1809 - 1815   2019.08

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    DOI: 10.2514/1.A34497

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

    Kim S., Orger N.C., Cordova-Alarcon J.R., Hernandez-Herrera M., Masui H., Yamauchi T., Toyoda K., Cho M., Duy Vu B.T., Vinh T.Q., Seng L.W., Hiang C.T.

    Acta Astronautica   161   328 - 337   2019.08

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

    DOI: 10.1016/j.actaastro.2019.05.046

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  • Guest Editorial Spacecraft Charging Technology Reviewed

    Andersen A., Bodeau M., Cho M., Davis V.A., Dennison J., Donegan M., Ferguson D.C., Green N., Inguimbert V., Jun I., Lai S.T., Likar J.J., Minow J., Parker L.N., Roussel J.F., Toyoda K., Garrett H.B., Usui H.

    IEEE Transactions on Plasma Science   47 ( 8 )   3629 - 3630   2019.08

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

    DOI: 10.1109/TPS.2019.2925231

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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

    Orger N.C., Toyoda K., Masui H., Cho M.

    Advances in Space Research   63 ( 10 )   3270 - 3288   2019.05

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    DOI: 10.1016/j.asr.2019.01.045

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  • Electrostatic Discharge Threshold on Coverglass Used to Protect Solar Cells in the Low Earth Orbit Reviewed

    Khan A.R., Minh N.D., Toyoda K., Cho M.

    IEEE Transactions on Plasma Science   47 ( 2 )   1445 - 1452   2019.02

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    DOI: 10.1109/TPS.2018.2885926

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  • Evaluation of Electron-emitting Film for Spacecraft Charging Mitigation (ELFs Charm) Reviewed

    TANAKA Atomu, MATEO VELEZ Jean-Charles, DADOUCH Sarah, OKUMURA Teppei, SAKAMOTO Kenji, IWATA Minoru, TOYODA Kazuhiro, CHO Mengu

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )   17 ( 1 )   1 - 6   2019.01

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    <p>To protect a satellite from accidents due to spacecraft charging, Kyushu Institute of Technology (Kyutech) is developing a device called ELFs-Charm, which stands for ELectron-emitting Film for Spacecraft CHARging Mitigation. Electron emission from ELFs-Charm was already confirmed in Polar Earth Orbit in 2012 via flight experiment onboard HORYU-II. As a next step, we are considering the practical operation for spacecraft charging mitigation. The present emission level is not enough to increase the satellite potential. We focus our efforts on improving two properties, charging property and the emission threshold. The charging property is measured by how well the differential voltage between the ELFs-charm insulator surface and the satellite chassis increases. The emission threshold is measured by the differential voltage when the electron emission starts. This paper reports the laboratory experimental results to measure the two properties of various samples. The sample made of fluorin resin coating had a good combination of the charging property and the emission threshold that makes it possible to emit electron under realistic ambient electron current density in orbit.</p>

    DOI: 10.2322/tastj.17.1

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    Other Link: https://ci.nii.ac.jp/naid/130007542851

  • On-Orbit Demonstration of Vacuum Arc Thruster(VAT-pi2)on HORYU-IV Satellite

    TOYODA Kazuhiro, AHEIEVA Kateryna, MURAKAMI Yayoi, FUKUDA Hiroshi, SHIMIZU Tatsuo, HORYU-Ⅳ Project Team, CHO Meng

    Aeronautical and Space Sciences Japan ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )   67 ( 5 )   158 - 160   2019.01

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    Authorship:Lead author   Language:English   Publishing type:Research paper (scientific journal)

    DOI: 10.14822/kjsass.67.5_158

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    Other Link: https://ci.nii.ac.jp/naid/130007642572

  • Lunar dust lofting due to surface electric field and charging within Micro-cavities between dust grains above the terminator region Reviewed International journal

    Orger N.C., Cordova Alarcon J.R., Toyoda K., Cho M.

    Advances in Space Research   62 ( 4 )   896 - 911   2018.08

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    DOI: 10.1016/j.asr.2018.05.027

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  • High-Voltage Power Generation on Spacecraft Reviewed

    Toyoda K.

    Electrical Engineering in Japan (English translation of Denki Gakkai Ronbunshi)   203 ( 4 )   25 - 30   2018.06

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    Authorship:Lead author   Language:English   Publishing type:Article, review, commentary, editorial, etc. (other)

    DOI: 10.1002/eej.23077

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

    Fukuda H., Masui H., Iwata M., Toyoda K., Cho M.

    Proceedings of the International Astronautical Congress, IAC   2018-October   2018.01

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  • Assessment of Worst GEO Plasma Environmental Models for Spacecraft Surface Charging by SPIS Reviewed

    NAKAMURA Masao, NAKAMURA Shinya, KAWACHI Ryota, TOYODA Kazuhiro

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )   16 ( 6 )   556 - 560   2018.01

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    <p>Assessment of the worst plasma environment for spacecraft surface charging in the geosynchronous Earth orbits (GEO) is important for spacecraft designs and operations, because it could cause spacecraft anomalies due to surface charging with resultant discharging arcs. The differential charging potential of spacecraft surfaces is considered to generate the harmful discharging arcs. There was no common standard of the worst GEO plasma environment for analysis of differential surface charging to prevent and mitigate the anomalies. Therefore in order to determine a new International Organization for Standardization (ISO) document for the purpose, a round-robin simulation was performed using the NASCAP-2k and MUSCAT. We perform surface charging simulations by Spacecraft Plasma Interaction Software (SPIS) as same as the round-robin simulation and evaluate the worst GEO plasma environmental models showing the detailed results. This study will contribute to a revision of the ISO document and also apply spacecraft charging risk estimations as space weather forecast.</p>

    DOI: 10.2322/tastj.16.556

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  • Initial Results from an In-Orbit High-Voltage Experimental Platform: HORYU-IV Reviewed International journal

    Shimizu T., Fukuda H., Su N.T., Toyoda K., Iwata M., Cho M.

    IEEE Transactions on Plasma Science   45 ( 8 )   1853 - 1863   2017.08

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    DOI: 10.1109/TPS.2017.2688725

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  • Mission Results Analysis of High-Voltage Technology Demonstration Satellite HORYU-II Reviewed International journal

    Fukuda H., Toyoda K., Cho M.

    IEEE Transactions on Plasma Science   45 ( 8 )   1871 - 1879   2017.08

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    DOI: 10.1109/TPS.2017.2705726

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  • Dielectric temperature spectroscopy of degraded solar cell coverglass due to ground-based space environmental irradiation Reviewed

    Chen Y., Chen L., Toyoda K., Cho M., Cheng Y.

    Astrophysics and Space Science Proceedings   47   113 - 122   2017.01

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

    DOI: 10.1007/978-3-319-19309-0_12

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  • Photoelectron current measurement in low earth orbit using a lean satellite, horyu-iv Reviewed International journal

    Ewang E., Miyahara A., Khan A.R., Toyoda K., Cho M.

    International Review of Aerospace Engineering   10 ( 3 )   140 - 153   2017.01

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    DOI: 10.15866/irease.v10i3.12394

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  • Solar Array Electrostatic Discharge Current and Image Captured in Orbit Reviewed

    54 ( 2 )   1 - 3   2016.10

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    DOI: 10.2514/1.A33622

  • Aoba Velox-IV camera system design for lunar horizon glow imaging in a future lunar mission Reviewed

    Örger N.C., Cordova-Alarcon J.R., Toyoda K., Soon L.K., Cho M.

    Proceedings of the International Astronautical Congress, IAC   0   2016.01

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  • Vacuum Arc Thruster Development and Testing for Micro and Nano Satellites Reviewed International journal

    AHEIEVA Kateryna, TOYODA Kazuhiro, CHO Mengu

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES )   14 ( 30 )   Pb_91 - Pb_97   2016.01

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    <p>This paper will describe the development of the Vacuum Arc thruster (VAT) for micro and nano satellites with the main purposes of: attitude control, maintaining orbit-satellite deorbiting. Firstly, this VAT thruster is integrated on-board student microsatellite Horyu-IV, which was developed at the Kyushu Institute of Technology (KIT), Japan. The satellite will be launched in the fiscal year 2015 by H2A rocket. This paper describes the principles of VAT as a direct drive from High Voltage Solar Array (HVSA). Expected performance of this vacuum arc thruster with passive ignition (space plasma condition) was measured. We propose a method for improving the thruster efficiency. Results show that the impulse bit was of the μNs order, and the thrust–56 nN– and efficiency– 2.5%–were calculated. Moreover, it was found that the impulse bit changes with the applied voltage. A new CFRP material was developed and used as a cathode for the purpose of improving efficiency. Discharge characteristics of current and the arc rate are presented. Measurements of impulse bit were also done for the VAT in configuration with two different propellants (commercial and new CFRP) and with a permanent magnet of 300 mT.</p>

    DOI: 10.2322/tastj.14.Pb_91

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  • Ground Experiment of Discharge Occurred on Spacecrafts(1)Ground Experiment of Discharge Occurred on Solar Array Panel

    TOYODA Kazuhiro

    91 ( 10 )   691 - 693   2015.10

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    Other Link: http://ci.nii.ac.jp/naid/110010016784

  • Development of an In-Orbit High-Voltage Experimental Platform: HORYU-4 Reviewed

    43 ( 9 )   3027 - 3040   2015.09

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

    DOI: 10.1109/TPS.2015.2453330

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  • Effects of Space Environmental Exposure on Photoemission Yield of Polyimide Reviewed

    22 ( 2 )   1204 - 1212   2015.04

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    DOI: 10.1109/TDEI.2015.7076823

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  • Flashover Discharge Measurement With Uniform Surface Charging and Modeling of Current Waveform Reviewed

    2015.03

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

    52 ( 2 )   544 - 552   2015.03

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    DOI: 10.2514/1.A33007

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  • Flight Experiment Results of Electron-Emitting Film for Spacecraft Charging Mitigation Reviewed

    52 ( 2 )   553 - 559   2015.03

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

    DOI: 10.2514/1.A32829

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  • 内之浦宇宙空間観測所見学

    豊田 和弘

    電気学会誌 ( The Institute of Electrical Engineers of Japan )   135 ( 4 )   243 - 243   2015.01

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    2014年度の電気・情報関係学会九州支部連合大会が鹿児島大学で開催され,同じ鹿児島県にある内之浦宇宙空間観測所を見学会で訪れた。ここでは1962年以来多くのロケッ

    DOI: 10.1541/ieejjournal.135.243

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    Other Link: http://ci.nii.ac.jp/naid/130005060632

  • Discharge Propagation in Normal Potential Gradient on Spacecraft Reviewed

    12 ( ists29 )   Pr_35 - Pr_39   2014.12

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  • Effects of Energetic Electron and Proton Irradiation on Electron Emission Yield of Polyimide Induced by Electron and Photon Reviewed

    12 ( ists29 )   Pr_13 - Pr_19   2014.06

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    CiNii Article

  • Influence of atomic oxygen exposure on surface resistivity of silicon doped polyimide affecting spacecraft charging Reviewed

    105   11 - 16   2014.06

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    DOI: 10.1016/j.vacuum.2014.01.030

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  • Characterization Experiments of Secondary Arcs on Solar Arrays: Secondary Arc Physical Parameters Reviewed

    51 ( 3 )   922 - 930   2014.05

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    DOI: 10.2514/1.A32736

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  • In-orbit demonstration of passive electron-emitting film for mitigation of spacecraft charging Reviewed

    11   8041 - 8046   2014.01

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  • 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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  • Effects of Ultraviolet Irradiation and Atomic Oxygen Erosion on Total Electron Emission Yield of Polyimide Reviewed

    42 ( 1 )   191 - 198   2013.12

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    DOI: 10.1109/TPS.2013.2288699

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  • Investigation on Space Environmental Degradation Effects of Solar Cell Coverglass Reviewed

    41 ( 12 )   3471 - 3476   2013.11

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    DOI: 10.1109/TPS.2013.2280287

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  • Total Electron Emission Yield of Solar Cell Coverglass and Optical Solar Reflector Reviewed

    41 ( 12 )   3558 - 3564   2013.11

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    DOI: 10.1109/TPS.2013.2288575

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

    41 ( 12 )   3477 - 3486   2013.08

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    DOI: 10.1109/TPS.2013.2276439

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  • In-orbit Demonstration of Newly Developed Passive Electron-emitting Film for Spacecraft Charging Mitigation Reviewed

    50 ( 4 )   853 - 859   2013.06

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    DOI: 10.2514/1.A32370

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  • Special issue on spacecraft charging technology 2013 Reviewed

    41 ( 12 )   2013.01

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    DOI: 10.1109/TPS.2013.2290251

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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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  • Special issue on spacecraft charging technologies Reviewed

    40 ( 9 )   2012.09

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    DOI: 10.1109/TPS.2012.2216053

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  • Spacecraft Charging Analysis of Large GEO Satellites Using MUSCAT Reviewed

    40 ( 4 )   1248 - 1256   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

    40 ( 2 )   351 - 358   2012.01

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    DOI: 10.1109/TPS.2011.2176754

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  • Evaluation method of solar array panel substrate insulation against sustained arcs Reviewed

    2011.12

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  • Time-Resolved Spectroscopy of Electrostatic Discharge and Secondary Arc Plasma on Spacecraft Solar Array Reviewed

    40 ( 2 )   359 - 367   2011.11

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    DOI: 10.1109/TPS.2011.2173954

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  • Development of Electron-emitting Film for Spacecraft Charging Mitigation Reviewed

    48 ( 3 )   546 - 552   2011.05

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    DOI: 10.2514/1.50735

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  • Flashover discharge on solar arrays: Analysis of discharge current and image Reviewed

    48 ( 2 )   326 - 335   2011.03

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    DOI: 10.2514/1.50907

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  • Propagation area of flashover on solar array under electron environment simulating geosynchronous orbit Reviewed

    130 ( 9 )   2010.11

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    DOI: 10.1541/ieejfms.130.793

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  • Characterization experiments of secondary arcs on solar arrays: Threshold and duration Reviewed

    47 ( 6 )   966 - 973   2010.11

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    DOI: 10.2514/1.49571

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

    Yukishige Nozaki,Hirokazu Masui,Kazuhiro Toyoda,Mengu Cho,Hirokazu Watabe

    Space Technology Japan, Trans. JSASS Space Technology Japan   7   11 - 17   2009.03

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    Kyutacar

  • Development of Electron-emitting Film for Spacecraft Charging Mitigation: Observation, Endurance and Simulations Reviewed

    M.Cho,T.Okumura,M.Iwata,K.Toyoda,H.Igawa,Y.Fujiwara,S.Hatta,T.Satou,T.Fujita

    the 47th AIAA Aerospace Science Meeting   2009.01

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    オーランド   2009.01.05  -  2009.01.08

  • Secondary Arc Threshold Meaurement on Solar Arrays for Japanese Spacecraft Charging Guideline Reviewed

    Hirokazu Masui,Kazuhiro Toyoda,Mengu Cho

    the 47th AIAA Aerospace Science Meeting   2009.01

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    オーランド   2009.01.05  -  2009.01.08

  • Generation of LEO-Type Atomic Oxygen Environment in Laboratory for Charging Property Database Reviewed

    N.Danish,Teppei Okumura,Hirokazu Masui,Minoru Iwata,Kazuhiro Toyoda,Mengu Cho

    the 59th International Astronautical Congress   2008.10

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    グラスゴー   2008.09.29  -  2008.10.30

  • Development of Electron Emitting Film for Spacecraft Charging Mitigation II. Improvement of Performance Reviewed

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

    the 59th International Astronautical Congress   2008.10

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    グラスゴー   2008.09.29  -  2008.10.30

  • Sustained Arc Test for Formulating Design Guideline of Solar Array Panel Reviewed

    Hirokazu Masui,Takayuki Ose,Kazuhiro Toyoda,Mengu Cho

    26th International Symposium on Space Technology and Science   2008.06

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    浜松   2008.06.01  -  2008.06.08

  • Preliminary Study of Development of Space Debris Removal Method Using Electrostatic Force Reviewed

    Yasunori Furukawa,Hiriokazu Masui,Kazuhiro Toyoda,Mengu Cho

    26th International Symposium on Space Technology and Science   2008.06

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    浜松   2008.06.01  -  2008.06.08

  • Spectroscopic Measurement of Secondary Arc Plasma on Solar Array Reviewed

    Takayuki Ose,Kazuhiro Toyoda,Hirokazu Masui,Mengu Cho

    26th International Symposium on Space Technology and Science   2008.06

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    浜松   2008.06.01  -  2008.06.08

  • ESD Test for Triple-Junction Solar Cells with Monolithic Diode Reviewed

    Yukishie Nozaki,Hirokazu Masui,Kazuhiro Toyoda,Mengu Cho

    26th International Symposium on Space Technology and Science   2008.06

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    浜松   2008.06.01  -  2008.06.08

  • Arc tracking between space cables due to electrostatic discharge Reviewed

    Hikaru kayano,Syunitirou Ninomiya,Teppei Okumura,Hirokazu Masui,Kazuhiro Toyoda,Mengu Cho

    26th International Symposium on Space Technology and Science   2008.06

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    浜松   2008.06.01  -  2008.06.08

  • Development of an Atomic Oxygen Irradiation System for the Charging Property Database Reviewed

    N. Danish,Hirokazu Masui,Minoru Iwata,Kazuhiro Toyoda,Mengu Cho

    26th International Symposium on Space Technology and Science   2008.06

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    浜松   2008.06.01  -  2008.06.08

  • Investigation of Sustained Arc Under Solar Cell Reviewed

    Kazuhiro Toyoda,Mengu Cho,Shirou Kawakita,Masato Takahashi

    26th International Symposium on Space Technology and Science   2008.06

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    浜松   2008.06.01  -  2008.06.08

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

    Hirokazu Masui,Takayuki Ose,Kazuhiro Toyoda,Mengu Cho

    IEEE Transactions on Plasma Science   36   2387 - 2394   2008.04

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  • ESD Ground Test of Solar Array Coupons for a Greenhouse Gases Observing Satellite in PEO Reviewed

    Kazuhiro Toyoda,Hirokazu Masui,Takanobu Muranaka,Mengu Cho,Tomoyuki Urabe,Takeshi Miura,Yuichiro Gonohe,Tooru Kikuchi

    IEEE Transactions on Plasma Science   36   2413 - 2424   2008.04

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  • Preliminary ESD Ground Tests on Meter-Class Solar panels in Simulated GEO Environments Reviewed

    H. Mashidori,M. Iwasa,A. Wada,K. Nitta,M. Nomura,K. Toyoda

    4th Space environment symposium   2008.01

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    東京   2008.01  -  2008.01

  • Metal halide lamps - Simulation of power generating solar arrays for secondary arc investigation Reviewed

    Andreas Kroier,Teppei Okumura,Kazuhiro Toyoda,Mengu Cho,Erich Leitgeb

    4th Space environment symposium   2008.01

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    東京   2008.01  -  2008.01

  • Experimental measurement of secondary arc plasma parameter on solar array Reviewed

    Takayuki Ose,Hirokazu Masui,Kazuhiro Toyoda,Mengu Cho

    4th Space environment symposium   2008.01

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    東京   2008.01  -  2008.01

  • Preliminary study of the influence of solar cell degradation due to ESD on solar array power generation Reviewed

    Teppei Okumura,Kazuhiro Toyoda,Shirou Kawakita,Mitsuru Imaizumi,Mengu Cho

    4th Space environment symposium   2008.01

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    東京   2008.01  -  2008.01

  • ISO Standardization of Electrostatic Discharge (ESD) Test of Satellite Solar Array Reviewed

    Hirokazu Masui,Kazuhiro Toyoda,Mengu Cho

    2008.01

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    東京   2008.01  -  2008.01

  • ESD Test for Triple-Junction solar cells with monolithic diode Reviewed

    4th Space environment symposium   2008.01

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    東京   2008.01  -  2008.01

  • Probability Distribution of Secondary Arc Duration on Solar Array Reviewed

    Mengu Cho,Tomoki Kitamura,Takayuki Ose,Hirokazu Masui,Kazuhiro Toyoda

    46th AIAA Aerospace Sciences Meeting and Exhibit   AIAA 2008-455   2008.01

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    アメリカ   リノ   2008.01  -  2008.01

  • Threshold measurement of secondary arc on solar arrays for Japanese spacecraft charging guideline Reviewed

    Kazuhiro Toyoda,Takayuki Ose,Hirokazu Masui,Mengu Cho

    4th Space environment symposium   2008.01

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    東京   2008.01  -  2008.01

  • Analysis of solar cell degradation mechanism due to ESD Reviewed

    Teppei Okumura,Kazuhiro Toyoda,Mitsuru Imaizumi,Mengu Cho

    17th International Photovoltaic Science and Engineering Conference   2007.12

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    福岡   2007.12  -  2007.12

  • Development of Electron Emitting Film for Spacecraft Charging Mitigation, Reviewed

    Minoru IWATA,Hideyuki IGAWA,Takayuki OSE,Yuki HARAGUCHI,Yuya SANMARU,Hirokazu MASUI,Satoshi HOSODA,Kazuhiro TOYODA,Mengu CHO,Tatsuhiro FUJITA

    58th International Astronautical Congress   2007.09

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    India   2007.09  -  2007.09

  • Degradation of, solar cell electric performance due to electrostatic discharge Reviewed

    Teppei Okumura,Andreas Kroier,Kazuhiro Toyoda,Mitsuru Imaizumi,Mengu Cho

    20th Space Photovoltaic Research and Technology Conference   2007.09

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    America   2007.09  -  2007.09

  • EXPERIMENTAL INVESTIGATION OF SECONDARY ARC PLASMA ON SOLAR ARRAY IN GEO ENVIRONMENT BY SPECTROSCOPY Reviewed

    Takayuki Ose,Hirokazu Masui,Kazuhiro Toyoda,Mengu Cho

    10th Spacecraft Charging Technology Conference   2007.06

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    France   2007.06  -  2007.06

  • Secondary arc tests on solar arrays for international standardization of ESD test and Japanese spacecraft charging guideline Reviewed

    T. KITAMURA,H. MASUI,K. TOYODA,M. CHO

    10th Spacecraft Charging Technology Conference   2007.06

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    Franc   2007.06  -  2007.06

  • Plasma interaction tests on Cu(In, Ga)Se2 thin film solar cell Reviewed

    Teppei Okumura,Hirokazu Masui,Shirou Kawakita,Kazuhiro Toyoda,Mitsuru Imaizumi,Mengu Cho

    10th Spacecraft Charging Technology Conference   2007.06

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    France   2007.06  -  2007.06

  • ESD ground test of solar array coupons for a Greenhouse gases Observing SATellite in PEO Reviewed

    K. TOYODA,H. MASUI,T. MARANAKA,M. CHO,T. URABE,T. MIURA,S. KAWAKITA,Y. GONOHE,T. KIKUCHI

    10th Spacecraft Charging Technology Conference   2007.06

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    France   2007.06  -  2007.06

  • Solar cell degradation due to ESD for international standardization of solar array ESD test Reviewed

    Teppei Okumura,Shunichiro Ninomiya,Hirokazu Masui,Kazuhiro Toyoda,Mitsuru Imaizumi,Mengu Cho

    10th Spacecraft Charging Technology Conference   2007.06

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    France   2007.06  -  2007.06

  • Development of flashover current simulation circuit for ESD ground test of solar array paddle Reviewed

    M. NOMURA,H. MASUI,K. TOYODA,M. CHO

    10th Spacecraft Charging Technology Conference   2007.06

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    France   2007.06  -  2007.06

  • Development of a Method for Generating a Discharge at an Arbitrary Position and Time for ESD Ground Tests of Solar Arrays Reviewed

    Yuta Sakamoto,Kazuhiro Toyoda,Mengu Cho

    10th Spacecraft Charging Technology Conference   2007.06

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    France   2007.06  -  2007.06

  • Mitigation of Surface Charging on Solar Array in Geostationary Earth Orbit Reviewed

    M. Iwata,H. Igawa,T. Ose,Y. Haraguchi,Y. Sanmaru,H. Masui,S. Hosoda,K. Toyoda,M. Cho,T. Fujita

    10th Space Charging Technology Conference   2007.06

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    France   2007.06  -  2007.06

  • Preliminary ESD Ground Tests Using a Large-scale Solar Array Reviewed

    Hideto Mashidori,Kumi Nitta,Shiro Kawakita,Jiro Harada,Yusuke Miki,Suetsugu Shinohara,Kazuhiro Toyoda

    10th Spacecraft Charging Technology Conference   2007.06

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    France   2007.06  -  2007.06

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

    Hirokazu Masui,Kazuhiro Toyoda,Mengu Cho

    10th Spacecraft Charging Technology Conference   2007.06

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    France   2007.06  -  2007.06

  • Development of solar array paddle for GOSAT: verification of charging and discharging effects Reviewed

    T. MIURA,T. URABE,S. KAWAKITA,T. KIKUCHI,Y. GONOHE,H. MASUI,K. TOYODA,M. CHO

    10th Spacecraft Charging Technology Conference   2007.06

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    Franc   2007.06  -  2007.06

  • Laboratory Test Campaign for ISO Standardization of Solar Array ESD Test Methods Reviewed

    Kazuhiro Toyoda,Motoki Kitamura,Teppei Okumura,Hirokazu Masui,Mengu Cho,Mitsuru Imaizumi

    Space Power Workshop   2007.04

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    America   2007.04  -  2007.04

  • Laboratory Test Campaign for ISO Standardization of Solar Array ESD Test Methods Reviewed

    Hirokazu Masui,Tomoki Kitamura,Teppei Okumura,Kazuhiro Toyoda,Mengu Cho

    The 45th AIAA Aerospace Sciences Meeting and Exhibit   2007.01

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    アメリカ   リノ   2007.01  -  2007.01

  • Proposal of a Current Regulative Diode for Power Supply in Sustained Arc Test Reviewed

    Kazuhiro Toyoda,Seiji Aso,Tokuro Kyoku,Tomoki Kitamura,Mengu Cho

    IEEE Transactions on Plasma Science   34 ( 5 )   1967 - 1972   2006.10

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  • Charge Neutralization via Arcing on a Large Solar Array in the GEO Plasma Environment Reviewed

    Takashi Kawasaki,Satoshi Hosoda,Jeongho Kim,Kazuhiro Toyoda,Mengu Cho

    IEEE Transactions on Plasma Science   34 ( 5 )   1979 - 1985   2006.10

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  • Development of 400V Solar Array Technology for Low Earth Orbit Plasma Environment Reviewed

    Satoshi Hosoda,Teppei Okumura,Jeongho Kim,Kazuhiro Toyoda,Mengu Cho

    IEEE Transactions of Plasma Science   34 ( 5 )   1986 - 1996   2006.10

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  • ADEOS-IIにおけるケーブル間持続放電現象の地上検証 Reviewed

    細田聡史,金正浩,趙孟佑,豊田和弘,川北史朗,艸分宏昌,高橋真人,前島弘則

    航空宇宙学会論文誌   154 ( 633 )   427 - 433   2006.10

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    主要雑誌

  • Development of High voltage Power System for SSPS Reviewed

    K. Toyoda,M. Iwata,M. Cho

    The 57th International Astronautical Congress   2006.10

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    スペイン   2006.10  -  2006.10

  • Discharge phenomenon on solar array surface due to RF irradiation Reviewed

    Kohei Kasedo,Satoshi Hosoda,Kazuhiro Toyoda,Mengu Cho,Yasumasa Hisada

    The 22nd International Symposium on Discharges and Electrical Insulation in Vacuum,   2006.09

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    金沢   2006.09  -  2006.09

  • Basic Experiment on Charging Mitigation of Solar Array in Geostationary Orbit Environment Reviewed

    Y. Sanmaru,T. Ose,T. Kawasaki,Y. Sikata,S. Hosoda,M. Iwata,K. Toyoda,M. Cho,T. Fujita

    The 22nd International Symposium on Discharges and Electrical Insulation in Vacuum   2006.09

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    松江   2006.09  -  2006.09

  • Activities of Laboratory of Spacecraft Environment Interaction Engineering in Kyushu Institute of Technology Reviewed

    K.Toyoda,M.Iwata,M.Cho

    The 22nd International Symposium on Discharges and Electrical Insulation in Vacuum   2006.09

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    松江   2006.09  -  2006.09

  • Dependence of sustained arc formation on charging environment of satellite solar array Reviewed

    Tomoki Kitamura,Yuya Sanmaru,Takashi Kawasaki,Satoshi Hosoda,Kazuhiro Toyoda,Mengu Cho

    The 22nd International Symposium on Discharges and Electrical Insulation in Vacuum   2006.09

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    松江   2006.09  -  2006.09

  • Emission Spectral Analysis of Arc Plasma on Solar Array in GEO Environment Reviewed

    Takayuki Ose,Yuya Sanmaru,Tomoki Kitamura,Satoshi Hosoda,Kazuhiro Toyoda,Mengu Cho

    The 22nd International Symposium on Discharges and Electrical Insulation in Vacuum   2006.09

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    松江   2006.09  -  2006.09

  • Mitigation of Geo Satellite Solar Array Surface charging: Laboratory Experiment Reviewed

    Mengu Cho,Yuya Sanmaru,Satoshi Hosoda,Minoru Iwata,Kazuhiro Toyoda,Tatsuhito Fujita,Yasumasa Hisada

    Proceedings of 10th International Symposium on Materials in a Space Environment   2006.06

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    フランス   2006.06  -  2006.06

  • ESD Tests On Cu(In, Ga)Se2 Thin-Film Solar Cell In Simulated LEO Environment Reviewed

    Teppei Okumura,Satoshi Hosoda,Jeongho Kim,Kazuhiro Toyoda,Shirou Kawakita,Mengu Cho

    The 25th International Symposium on Space Technology and Science   2006.06

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    金沢   2006.06  -  2006.06

  • Emission Spectroscopy Of Arc Plasma On Solar Array In GEO Environment Reviewed

    Takayuki Ose,Yuya Sanmaru,Tomoki Kitamura,Satoshi Hosoda,Kazuhiro Toyoda,Mengu Cho

    The 25th International Symposium on Space Technology and Science   2006.06

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    金沢   2006.06  -  2006.06

  • Mitigation of GEO Satellite Solar Array Surface Charging: Laboratory Experiment Reviewed

    M. Cho,S. Hosoda,M. Iwata,K. Toyoda

    Proceedings of 10th International Symposium on Materials in a Space Environment   2006.06

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    フランス   2006.06  -  2006.06

  • Effect of Substrate on Sustained Arc between Electrodes Reviewed

    Kazuhiro Toyoda ,Leon Levy

    Proceedings of 25th ISTS   2006.04

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  • Primary Arc Propagation with Neutralizing Coverglass Surface on GEO Satellite Solar Array Reviewed

    Jeongho Kim,Takashi Kawasaki,Yuya Sanmaru,Satoshi Hosoda,Kazuhiro Toyoda

    44th AIAA Aerospace Sciences Meeting and Exhibit   2006.01

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    2006.01  -  2006.01

  • ESD Ground Test of ITO-Coated Back Surface of Solar Paddle for a Polar Satellite Reviewed

    S. Hosoda,K. Toyoda,M. Cho,M. Mokuno,M. Takahashi,S. Kawakita,Y. Nozaki

    44th AIAA Aerospace Sciences Meeting and Exhibit   2006.01

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    America   2006.01  -  2006.01

  • Development of high voltage solar array for large space platforms Reviewed

    S. Hosoda,T. Okumura,J. Kim,M. Cho ,K. Toyoda

    56th International Astronautical Congress   2005.10

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    2005.10  -  2005.10

  • Degradation of High Voltage Solar Array due to Arcing in LEO plasma Environment Reviewed

    Kazuhiro Toyoda,Teppei Okumura,Satoshi Hosoda,Mengu Cho

    Journal of Spacecraft and Rockets   42 ( 5 )   947 - 947   2005.09

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  • 超高速インターネット衛星搭載用太陽電池アレイの地上試験 Reviewed

    豊田和弘,松本利明,志方吉夫,趙孟佑,佐藤哲夫 ,野崎幸重

    日本航空宇宙学会論文誌   52 ( 606 )   328 - 336   2005.07

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  • Development of 400V solar array technology for LEO spa Reviewed

    S. Hosoda,T. Okumura,J. Kim,M. Cho ,K. Toyoda

    9th Spacecraft Charging Technology Conference   2005.04

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    2005.04  -  2005.04

  • Power Reduction of Solar Arrays by Arcing Under Simulated Geosynchronous Orbit Environment Reviewed International journal

    K. Toyoda, T. Matsumoto, M. Cho, Y. Nozaki, and M. Takahashi

    Journal of Spacecraft and Rockets   41   854 - 861   2004.10

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  • Laboratory Tests on 110-Volt Solar Arrays in Ion Thruster Plasma Environment Reviewed International journal

    M. Cho, R. Ramasamy, K. Toyoda, Y. Nozaki, and M. Takahashi

    Journal of Spacecraft and Rockets   40 ( 2 )   221 - 229   2003.03

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  • Laboratory Tests on 110V Solar Arrays in a Simulated Geo-synchronous Orbit Environment Reviewed International journal

    M. Cho, R. Ramasamy, T. Matusmoto, K. Toyoda, Y. Nozaki, and M. Takahashi

    Journal of Spacecraft and Rockets   40 ( 2 )   221 - 220   2003.03

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  • Thrust Performance of a CW Laser Thruster in Vacuum Reviewed International journal

    K. Toyoda, K. Komurasaki, and Y. Arakawa

    Vacuum   65   383 - 388   2002.05

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Conference Prsentations (Oral, Poster)

  • Deorbit system based on vacuum ARC thruster for microsatellite

    Aheieva K., Toyoda K., Cho M.

    Proceedings of the International Astronautical Congress, IAC 

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    Event date: 2015.01.01   Language:English  

    In this article presented Vacuum Arc Thruster (VAT), which was designed and manufactured in Kyushu Institute of Technology. Presented principle of work and design. Thruster, firstly, will be operating onboard satellite Horyu-4, which will be launch in 2015 and demonstrate work with direct power source-High Voltage Solar Array (300 V). For VAT presented main discharge and power characteristics measured in experiments. Was calculated thrust (56 nN) and efficiency (2.5 %). Specific impulse is 1200 sec, impulse bit 2 uNs. The total weight of the system including circuit and mounts to satellite is 32 grams. Presented results for efficiency improving methods, such as new type of propellant use in the thruster and magnet system. Calculated deorbit time dependence to satellite mass and power consumption for Vacuum Arc Thruster.

  • Development of mission payloads for arc event generator and investigation satellite HORYU-IV

    Fukuda H., Shimizu T., Toyoda K., Cho M.

    Proceedings of the International Astronautical Congress, IAC 

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    Event date: 2015.01.01   Language:English  

    Copyright © 2015 by the International Astronautical Federation. A nano-satellite "HORYU-4" is under development in Kyushu Institute of Technology (Kyutech) and is planed to be launched in FY 2015. The main mission of HORYU-4 is measurement of discharge phenomenon (e.g. discharge current, discharge point) on orbit. The one of the submission of this satellite is demonstrate of discharge mitigation method. The discharge experiment system is needed for this mission. This paper introduces the over view of HORYU-4, and discusses following contents: 1, Development of EM of the discharge experiment system. 2, Ground-based discharge tests at Kyutech. This mission will be first measurement of arcing current in space orbit. It will be able to evaluate the validity of ground-based test systems by comparing the result of ground-based tests with experiments conducted in space.

  • Role of aging on the threshold of electrostatic discharge on solar array coverglass

    Khan A., Hughes R., Chen Y., Toyoda K., Cho M., Gray A.

    Proceedings of the International Astronautical Congress, IAC 

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    Event date: 2014.01.01   Language:English  

    Copyright © 2014 by the International Astronautical Federation. All rights reserved. Coverglass has been widely used to cover the solar cells of satellite solar arrays. This acts to protect the arrays from damage due to irradiation by UV, protons, electrons, etc. However, charge accumulation due to high-energy proton/electron irradiation or ageing due to thermal cycling may degrade the quality and affect the threshold for electrostatic discharge (ESD) from the coverglass. In order to reveal the effect of aging on the threshold for ESD in an inverted potential gradient (IPG) condition, several coverglass samples (CMG100-AR) produced by Qioptiq Ltd. have been aged by thermal cycling (-160 to +110 C) and high-energy (500 keV) electron beam irradiation. A ground experiment was conducted by placing virgin and exposed (aged) samples in vacuum, irradiating the samples with a beam of energetic electrons to generate an artificial ESD, and measuring the sample's surface potential by a non-contact method before and after the discharge occurred. Statistical analysis and Weibull distribution confirms that the ESD threshold for aged coverglass is higher than that of virgin.

  • Total electron emission yield measurement of insulating materials due to different temperatures

    Miyahara A., Wu J., Khan A., Toyoda K., Cho M.

    Proceedings of the International Astronautical Congress, IAC 

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    Event date: 2014.01.01   Language:English  

    Copyright © 2014 by KYUSHU INSTITUTE OF TECHNOLOGY. Electron induced secondary electron emission from space insulator is a very important factor in understanding spacecraft charging behaviour. Due to the injection of primary electrons and the emission of secondary electrons in the surface layer of insulator, the target surface will be negatively or positively charged. Additionally, the electron emission yield of the spacecraft surface materials is highly dependent on space environments, such as the temperature variation. In our tests, we chose the polyimide film (Kapton 100H) as the research object, and used a single short, low-density pulsed beam, and also developed a scanning method for the total electron emission yield (TEEY) measurement, which can avoid surface potential influence for insulating materials. Moreover for the TEEY system, we installed a heater for high temperature (around 100°C) and the shroud by using liquid nitrogen for low temperature (around -50°C). Under this experimental situation, TEEY of polyimide films of room, high and low temperature was tested respectively. The conductivity variation of the polyimide film due to the different temperatures was considered to influence TEEY.

  • Performance of electroconductive bonded lubricant films in space environment for electrodynamic tether of debris removal system

    Matsumoto K., Takahashi A., Shiomi H., Kawamoto S., Ohkawa Y., Kawamura M., Toyoda K.

    European Space Agency, (Special Publication) ESA SP 

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    Event date: 2013.12.01   Language:English  

    Several types of electroconductive solid lubricant films, developed as bonded films for the electrodynamic tether (EDT) of an active space debris removal system, were evaluated. These films used molybdenum disulfide or graphite as lubricants, and additives to obtain conductivity. Examination of tribological properties using a pin-on-disk tribometer in vacuum conditions showed that the tested bonded films had low friction and slight wear, but differences in tribological properties were observed especially for different counterpart materials. Details of the evaluation results of the electroconductive solid lubricant films, including tribological behaviors, the effects of atomic oxygen and performance of electron collection from space plasma are reported. Copyright © 2013 European Space Agency.

  • Total electron emission yields of typical polymers

    Chen Y., Wu J., Cho M., Toyoda K.

    Proceedings of IEEE International Conference on Solid Dielectrics, ICSD 

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    Event date: 2013.12.01   Language:English  

    In this paper, a pulsed scanning method for the total electron emission yield measurement of insulating materials is proposed. A total electron detector with big hollow space and insulating spacer, and a pulsed yield scanning measurement system is recommended. This method can avoid influence from the charged surface of the insulating material. Using the system, the total secondary electron emission yields of several typical polymers, such as, PA, PS, PI, PTFE, HDPE, PC, PMMA, PEEK, PET, UHMW-PE, have been reported, as induced by a 30 microsecond pulse of primary electrons with ∼ 20 nA incident beam current and energies up to 2500 eV. © 2013 IEEE.

  • 300V direct drive vacuum arc thruster for nano-satellite

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

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

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    Event date: 2013.08.19   Language:English  

    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.

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

    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 

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    Event date: 2013.08.19   Language:English  

    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.

  • Initial results from Primary Arc effects on solar cells at LEO (PASCAL) flight experiment

    Likar J., Okumura T., Iwai S., Stone S., Gasner S., Jenkins P., Trautz K., Cho M., Lombardi R., Toyoda K.

    Conference Record of the IEEE Photovoltaic Specialists Conference 

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    Event date: 2013.01.01   Language:English  

    Repeated low power, or primary arcing, may adversely affect the performance of space solar cells. The cumulative effects of primary arcing on common solar cell performance parameters has been the subject of numerous ground studies in simulated plasma environments. The Primary Arc effects on Solar Cells At LEO (PASCAL) flight experiment is presently active aboard in the International Space Station (ISS) and characterizing such effects in-orbit for numerous state-of-the-art space solar cells with initial results presented herein. © 2013 IEEE.

  • Mitigation method of preventing secondary arcing on solar array by using capacitor and inductor

    Haruta I., Shimizu T., Toyoda K., Cho M.

    Proceedings of the International Astronautical Congress, IAC 

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    Event date: 2013.01.01   Language:English  

    Recently, the trend of spacecraft designers has led to the tendency of making larger and multifunctional satellites. In order to achieve the growing demands, the development of a large satellite bus is indispensable. However, electrical discharge accidents have increasingly come to occur on the solar arrays due to the higher bus voltage of any satellite. An electrical discharge on the solar array not only decreases the generating power but also can even halt operation of the satellite entirely. During electrical discharges, various arcing are possible, among which sustained arc is the most detrimental to the satellite. At present, grouting (adhesive is buried between solar cells to which high voltage is applied) is practiced as a mitigation method of sustained arc. However, this method has several disadvantages. Therefore, the development of a new mitigation method is requested. In this paper, we report the effect of mitigation method for sustained arc on solar array, by inserting capacitor and inductor into sustained arc circuit. It is confirmed that sustained arcs were oscillated by the capacitor (i.e. several hundred nF). Therefore, if the oscillation is sufficiently big, sustained arcs can be mitigated. In addition, this paper discusses a relation between flashover current and secondary arc. From the experimental results, when flashover is short, arc current to vibrate and it is suppressed. When flashover is long, arc current can't cut and it isn't suppressed. But, by increasing the capacitance of the capacitor, it was possible to accommodate long flashover discharge. Copyright ©2013 by the International Astronautical Federation.

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

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

    Proceedings of the International Astronautical Congress, IAC 

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    Event date: 2013.01.01   Language:English  

    The World's largest spacecraft bus voltage is the International Space Station (ISS) with a bias voltage of 160V. We have investigated a power bus able to handle higher voltage than the ISS. Electro-static discharges (ESDs) are more likely to occur when a satellite generates power at a high voltage rather than low voltage in low Earth orbit (LEO). However, high voltage generation is essential for building large space systems. Therefore, Kyushu Institute of Technology (Kyutech) is developing a high voltage generation technology that could counteract ESDs. This could be considered as a key technology for next generation spacecraft. Nano-satellites are useful and less risky tools for technology demonstration since they are faster and less expensive to develop than large satellites. Therefore, we focused on nano-satellite development to demonstrate Kyutech's advanced high voltage generation technology. All of the on-orbit high voltage tests have been demonstrated by using a DC/DC converter to adapt the high voltage generated by the solar array. This was a World premiere as no high voltage tests had previously been performed in space using solar arrays. To demonstrate the feasibility of on-orbit high voltage generation, we developed a High Voltage Technology Demonstration Satellite named HORYU-2. The mission consisted of 300V generation without causing arcing, and contribution to the practical development of 1MW class spacecraft. On May 18, 2012, HORYU-2 was launched by the H-2A rocket number 21. HORYU-2 has been operated from Kyutech's ground station, and HORYU-2's orbit was confirmed and the mission successful. For the first time in the World, 350V have been generated on-orbit without arc creation. Using two specially designed solar arrays arcing was mitigated. Regarding the sub-missions, ELF was proven to work well on-orbit, Trek measurements are currently under investigation, the SCAMP camera successfully imaged Earth, and the debris sensor has not yet detected debris impact. During the conference, we will present all mission analysis in further detail. Copyright ©2013 by the International Astronautical Federation.

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

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

    50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 

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    Event date: 2012.12.01   Language:English  

    High Voltage Technology Demonstration Satellite HORYU-II is a Nano-Satellite (30cm cubic shape, 7kg) being developed by the students in Kyushu Institute of Technology. One of the objectives of this satellite is orbital demonstration of forthcoming space high-voltage technologies. The satellite with the highest voltage generation in Low Earth Orbit has been ISS, generating 160V. On orbit, especially LEO, high-voltage (over about 200V) generally induces electro-static discharges (ESD). HORYU-II is aimed to demonstrate new designs of solar array that can generate power, free of ESD, by producing 300V via a specially designed solar array itself, not via a conventional DC/DC converter. If successful, HORYU-II will become the first spacecraft in the world that achieved 300V photovoltaic power generation in space. Copyright © 2012 by the American Institute of Aeronautics and Astronautics, Inc.

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

    Takahashi A., Khan A., Masui H., Iwata M., Toyoda K., Cho M.

    Proceedings of the International Astronautical Congress, IAC 

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    Event date: 2012.12.01   Language:English  

    A cubic nano-satellite with a length of 30 cm, named HORYU-II, was developed at Kyushu Institute of Technology in Japan. HORYU-II is a demonstration satellite for high voltage technology and its two main advantages are its low cost and short time development. HORYU-II's main mission is to demonstrate the possible generation of 300V on-orbit by using spherical solar cells connected in series. This mission can be considered as the first high voltage technology demonstration in the world. To control arcing under negative 300V in space plasma, ETFE (ethylene tetra flouro ethylene) cover and semi-conductive coated solar array efficiency will be demonstrated. Along with this, charging mitigation of spacecraft by using electron emitting film, operation of commercial-off-the-shelf (COT) surface potentiometer will also be demonstrated. HORYU-II was launched by a H-IIA rocket on May 18, 2012. We have been acquiring on-orbit data and monitoring the satellite conditions. HORYU-II succeeded in generating the highest 300V photovoltaic voltage in space for the first time in the world. However, many problems were found during data collection. In this paper, the result of HORYU-II's missions is described.

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

    Toyoda K., Sasaki R., Cho M.

    50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 

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    Event date: 2012.12.01   Language:English  

    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. The verification experiment of charging and moving debris was performed in a vacuum chamber simulating LEO plasma environment. A space potential and floating potential were also measured. A pseudo debris was charged and attracted to biased net electrode in plasma environment. Copyright © 2012 by the American Institute of Aeronautics and Astronautics, Inc.

  • Characterization of solar cell degradation due to electrostatic discharge on multi-junction solar cell

    Okumura T., Imaizumi M., Toyoda K., Cho M.

    Conference Record of the IEEE Photovoltaic Specialists Conference 

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    Event date: 2010.12.20   Language:English  

    A shunt resistance on the solar cell edge which is made by an electrostatic discharge (discharge) causes the degradation of multi-junction solar cell (MJ cell). To prevent the degradation, a trench was formed along the edge of multi-junction solar cell (AD MJ cell). The degradation characterization tests were performed on state-of art MJ cell and AD MJ cell to investigate the effect of trench in plasma environment. © 2010 IEEE.

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

    Hoang B., Wong F., Funderburk V., Cho M., Toyoda K., Masui H.

    Conference Record of the IEEE Photovoltaic Specialists Conference 

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    Event date: 2010.12.20   Language:English  

    Space Systems/Loral (SS/L) successfully completed electrostatic discharge (ESD) tests of Multi-junction (MJ) GaAs/Ge solar array design in geosynchronous space environment. This ESD test was based on ISO-11221, Space systems - Space solar panels -Spacecraft Charging Induced Electrostatic Discharge Test Methods. In addition to the ISO reference for the test schematic, SS/L implemented modified test circuitry to better simulate the on-orbit operational conditions of our solar array design. The ESD test circuit also included simulated solar array panel coverglass flashover. The ESD test program utilized a 25-cell coupon that had been subjected to 2,000 thermal cycles caused by earth eclipses in GEO orbit and > 12,000 thermal cycles caused by the shadow of the spacecraft antennas. Other ESD test coupons are 4-cell coupons that, after baseline ESD experiments, can later be subjected to combined space environmental exposures tests. To demonstrate design robustness, we performed ESD tests to voltages and currents that are higher than that of on-orbit solar array operational voltages and currents. This paper discusses the coverglass flashover simulation, ESD test setup, the importance of the electrical test design in simulating the on-orbit operational conditions, and the test results. © 2010 IEEE.

  • Development of Electron-Emitting Film for Spacecraft Charging Mitigation: Environment exposure tests

    Khan A., Sumida T., Iwata M., Toyoda K., Cho M., Fujita T.

    48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 

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    Event date: 2010.12.13   Language:English  

    Prevention of spacecraft charging and discharging has become increasingly important as GEO satellites employ higher bus voltage. There are numerous mitigation techniques against spacecraft charging including electron emission from the spacecraft chassis. A new electron emission device operating in completely passive manner has been developed which utilizes the field enhancement at the triple junction formed at the interface of metal and insulator exposed to space. It is named as Electron Emitting Film for Spacecraft Charging Mitigation (ELF's CHARM). Micro-etching was applied to polyimide-copper (PI-Cu) laminated film to manufacture a laboratory prototype. ELF utilizes pre-breakdown electron emission current leading to arcing at the triple junction keeping the current at the steady state. The electric field at the triple junction is macroscopically enhanced by charging of the polyimide film and microscopically by dielectric impurity on the copper surface. Theoretical rough estimate gives a current of 100 to 1,000μA. The laboratory experiment confirmed stable current emission from 10 to 100 μA from a sample of several centimeters square for 4 hours. Its robustness against ground handling and in-orbit contamination has already been demonstrated. To prepare for flight demonstration as early as 2011, the research and development have been accelerated. To ensure the endurance, recently 100 accumulated hours emission test and effect of high energy electron and proton and thermal cycling have been investigated on recently developed ELF. Post-emission of this electron emitting film confirms the durability under those harsh environments. Copyright © 2010 by the American Institute of Aeronautics and Astronautics, Inc.

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

    Toyoda K., Wada T., Yoke T., Suzuki T., Masui H., Cho M.

    48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 

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    Event date: 2010.12.13   Language:English  

    ESD ground testing on satellite solar array paddle is performed to mitigate catastrophic accidents. An international standard is desired to perform international satellite business smoothly. A standard has been developed in laboratory of spacecraft environment interactions. The draft has been applied. In this paper, preliminary experiments were performed to improve the testing method. Copyright © 2010 by the American Institute of Aeronautics and Astronautics, Inc.

  • Flashover plasma characteristics on 5m<sup>2</sup> solar array panels in a simulated plasma environment of geostationary orbit and low earth orbit

    Okumura T., Nitta K., Takahashi M., Suzuki T., Toyoda K.

    48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 

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    Event date: 2010.12.13   Language:English  

    Electrostatic discharge may cause an anomaly on a solar array. Nowadays, an electrostatic discharge test on solar array panels is required to ensure the durability of the solar arrays against electrostatic discharge. To perform a realistic electrostatic discharge test, the electrostatic discharge current must be simulated accurately. As the current of the electrostatic discharge is mainly supplied by flashover discharge, it is necessary to investigate the characteristics of flashover discharge such as the propagation area and velocity of flashover plasma. We performed the electrostatic discharge test on large solar array panels in a simulated plasma environment of geostationary orbit and low earth orbit. In this paper, we discuss the propagation area and velocity of flashover plasma.

  • Development and verification of on-orbit demonstration device for Electron-emitting Film (ELF) for spacecraft charging mitigation

    Sumida T., Shibagaki R., Khan A., Iwata M., Toyoda K., Tomonari S., Cho M.

    61st International Astronautical Congress 2010, IAC 2010 

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    Event date: 2010.12.01   Language:English  

    As geo-stationary (GEO) satellite bus voltage increased due to the increased size of the satellites, the number of solar array failures due to spacecraft charging increased. We are developing an electron emitter that emits electrons from the conductor by using the enhanced electric field at the triple junction which occurs simultaneously while spacecraft charging. The emitter is composed of an insulator on top of cupper plate. Parts of the cupper plate are exposed through the insulator ensuring the triple junctions that are the source of electron emission. This emitter operates in a completely passive fashion. In this paper, the authors conducted the verification test of this emitter after making a measurement circuitry. This time, the surfaces of the emitters were coated with a special material to enhance the electron emission current. In the ground test, the emitters were biased to a highly negative potential with respect to a vacuum chamber ground and exposed to an electron beam. This leaded the simulation of satellite charging. Then the operation of the measurement system had been checked to confirm the emission as well as surface potential. These results permit this electron emitter to be used in actual space environment.

  • Understanding the effect of atomic oxygen exposure on surface and volume resistivity change in LEO

    Mundari N., Khan A., Iwata M., Toyoda K., Cho M.

    61st International Astronautical Congress 2010, IAC 2010 

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    Event date: 2010.12.01   Language:English  

    Spacecraft surface charging can leads to arcing and a loss of electricity generation capability of solar panel or even loss of a satellite. The arcing problem may be further aggravated by the atomic oxygen (AO) exposure in Low Earth orbit, which modify the surface of materials like polyimide, Teflon, anti reflective coating, cover glass etc used on satellite surface affecting materials properties such as resistivity, secondary electron emissivity, photo electron emission which govern the charging behavior. These properties are crucial inputs parameters for spacecraft charging analysis. To study the AO exposure effect on the charging governing properties, an AO exposure facility based on laser detonation of oxygen was built which produce 8-14km atomic oxygen with higher flux than in orbit. After exposing materials to 10years equivalent AO flux at the altitude of 700-800km, surface charging properties like resistivity and secondary electron emission is being measured. Measurement of surface and volume resistivity for AO exposed samples was done for polyimide. The measurement was done using the charge storage decay method at a room temperature, which is considered most appropriate for measuring the resistivity for space application. It was found that the value of surface resistivity increases more than two fold and volume resistivity remains same. Measurement of secondary electron emission characteristics is under progress.

  • パルスレーザを用いた原子状酸素照射装置の開発

    平成20年度衝撃波シンポジウム 

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    Event date: 2009.03.17 - 2009.03.19   Language:Japanese  

  • 宇宙プラズマと網電極の干渉を利用したデブリ除去手法の提案

    平成20年度衝撃波シンポジウム 

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    Event date: 2009.03.17 - 2009.03.19   Language:Japanese  

  • SSPS用高電圧ケーブルの放電現象に関する研究

    第27回宇宙エネルギーシンポジウム 

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    Event date: 2009.01.19 - 2009.01.20   Language:Japanese  

  • 宇宙プラズマ環境下での電圧印加電極を利用したデブリ除去方法の提案

    平成20年度宇宙輸送シンポジウム 

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    Event date: 2009.01.19 - 2009.01.20   Language:Japanese  

  • 低温および室温における太陽電池クーポンパネルの放電頻度の比較

    第5回宇宙環境シンポジウム 

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    Event date: 2008.12.18 - 2008.12.19   Language:Japanese  

  • キャパシタンスを用いた太陽電池アレイ上での持続放電抑制方法に関する研究

    日本航空宇宙学会西部支部講演会(2008) 

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    Event date: 2008.11.14   Language:Japanese  

  • 衛星帯電放電試験への適用を目指した放電発生手法の開発

    第52回宇宙科学技術連合講演会 

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    Event date: 2008.11.05 - 2008.11.07   Language:Japanese  

  • 宇宙用太陽電池アレイでの表面吸着水分量と放電発生の関係

    第52回宇宙科学技術連合講演会 

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    Event date: 2008.11.05 - 2008.11.07   Language:Japanese  

  • 宇宙用太陽電池で発生する放電電流波形模擬回路の開発

    第52回宇宙科学技術連合講演会 

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    Event date: 2008.11.05 - 2008.11.07   Language:Japanese  

  • 宇宙機帯電放電設計標準策定に向けた太陽電池アレイ持続放電発生閾値測定試験

    第52回宇宙科学技術連合講演会 

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    Event date: 2008.11.05 - 2008.11.07   Language:Japanese  

  • Cu (In, Ga) Se2 薄膜太陽電池アレイの実用化に向けた帯電放電試験:放電発生メカニズム

    第52回宇宙科学技術連合講演会 

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    Event date: 2008.11.05 - 2008.11.07   Language:Japanese  

  • 宇宙プラズマと電圧印加電極の干渉を利用したデブリ除去手法の提案

    第52回宇宙科学技術連合講演会 

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    Event date: 2008.11.05 - 2008.11.07   Language:Japanese  

  • Electron-emitting Filmの電界放出電子電流分布測定の基礎研究

    第49回真空に関する連合講演会 

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    Event date: 2008.10.27 - 2008.10.31   Language:Japanese  

  • 静止衛星の帯電抑制用受動型電子エミッタに関する実験的研究

    第49回真空に関する連合講演会 

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    Event date: 2008.10.27 - 2008.10.31   Language:Japanese  

  • SSPS用高電圧ケーブルの宇宙環境適応性に関する基礎研究

    第11回宇宙太陽発電システム(SPS)シンポジウム 

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    Event date: 2008.09.17 - 2008.09.18   Language:Japanese  

  • SSPS用高電圧ケーブルの宇宙環境での適応性

    平成20年電気学会全国大会 

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    Event date: 2008.04   Language:Japanese  

  • 衛星帯電放電用のフラッシュオーバ電流摸擬回路開発

    平成20年電気全国大会, 

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    Event date: 2008.03   Language:Japanese  

  • 放電発生の環境依存性とその統計的解析を目的とした吸着水分量の測定

    平成20年電気学会全国大会 

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    Event date: 2008.03   Language:Japanese  

  • 電界減速によるスペース・デブリ除去方法の基礎研究

    平成20年電気全国大会, 

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    Event date: 2008.03   Language:Japanese  

  • 宇宙用ケーブルにおける持続放電とアークトラッキングの形成に関する研究

    平成20年電気学会全国大会 

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    Event date: 2008.03   Language:Japanese  

  • 太陽電池アレイ地上試験での任意の位置・時間における放電発生手法の開発

    平成20年電気学会全国大会 

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    Event date: 2008.03   Language:Japanese  

  • 高温環境下における宇宙用電力ケーブル被覆の寿命評価とひび割れ現象再現

    日本航空宇宙学会西部支部講演会 

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    Event date: 2007.11   Language:Japanese  

  • 人工衛星地上帯電放電試験用パルス電流発生回路の開発

    日本航空宇宙学会西部支部講演会 

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    Event date: 2007.11   Language:Japanese  

  • 放電発生の環境依存性とその統計的解析を目的とした吸着水分量の測定

    日本航空宇宙学会西部支部講演会 

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    Event date: 2007.11   Language:Japanese  

  • 静止軌道の電子環境模擬電子ビーム照射システムの開発

    第51回宇宙科学技術連合後援会 

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    Event date: 2007.10   Language:Japanese  

  • 静止軌道衛星の帯電・放電抑制電界放出素子の研究

    未入力 

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    Event date: 2007.10   Language:Japanese  

  • 九州工業大学宇宙環境技術研究センターにおける宇宙活動

    第51回宇宙科学技術連合講演会 

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    Event date: 2007.10   Language:Japanese  

  • 宇宙用太陽電池パネルの国内設計標準化に向けた持続放電発生閾値に関する研究

    第51回宇宙科学技術連合講演会 

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    Event date: 2007.10   Language:Japanese  

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Industrial Property

  • 真空アーク推進機

    豊田和弘

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    Announcement no:特開2017-002851  Date announced:2017.01.05

Grants-in-Aid for Scientific Research

  • 超小型衛星搭載用300V発電直接駆動真空アーク推進機の開発

    Grant number:24656521  2012.04 - 2014.03   挑戦的萌芽研究

  • 宇宙プラズマを利用したデブリ除去方法の開発

    Grant number:22656195  2010.04 - 2012.03   挑戦的萌芽研究