Faculty Profiles - TOYODA kazuhiro

Papers - TOYODA kazuhiro

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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

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

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.

DOI： 10.2322/tastj.17.1

CiNii Article

CiNii Research

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

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

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

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

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

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

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.

DOI： 10.2322/tastj.16.556

CiNii Article

CiNii Research

Other Link： https://ci.nii.ac.jp/naid/130007481369

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

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

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

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

Solar Array Electrostatic Discharge Current and Image Captured in Orbit Reviewed

54 ( 2 ) 1 - 3 2016.10

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

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

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

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.

DOI： 10.2322/tastj.14.Pb_91

CiNii Article

CiNii Research

Other Link： http://ci.nii.ac.jp/naid/130005172062

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

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

43 ( 9 ) 3027 - 3040 2015.09

Effects of Space Environmental Exposure on Photoemission Yield of Polyimide Reviewed

22 ( 2 ) 1204 - 1212 2015.04

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

2015.03

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

52 ( 2 ) 544 - 552 2015.03

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

52 ( 2 ) 553 - 559 2015.03

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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Papers - TOYODA kazuhiro