Faculty Profiles - TOYODA kazuhiro

Papers - TOYODA kazuhiro

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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

Experimental investigation of total electron emission yield of polyimide film under various temperatures Reviewed International journal

Wu J., Li S., Zhang B., Cao W., Li Y., Toyoda K.

AIP Advances 12 ( 7 ) 2022.07

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

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

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

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

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

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

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

Scopus

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Sulphur-fuelled Surface Arc Thruster for Propelling Nanosatellites Reviewed International journal

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

Advances in Astronautics Science and Technology 4 ( 1 ) 39 - 46 2021.03

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

Consideration on voltage rising in spacecraft during flashover discharge Reviewed International journal

Toyoda K.

Journal of Spacecraft and Rockets 57 ( 6 ) 1419 - 1421 2020.07

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

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

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.

Scopus

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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

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

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.

Scopus

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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

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

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

Scopus

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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

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

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

Scopus

Other Link： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85092416924&origin=inward

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

Electrostatic discharge experiment results on ground using experiment model of Horyu-IV Reviewed International journal

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

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

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

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

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

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

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

Discharge Propagation in Normal Potential Gradient on Spacecraft Reviewed

12 ( ists29 ) Pr_35 - Pr_39 2014.12

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

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

105 11 - 16 2014.06

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

51 ( 3 ) 922 - 930 2014.05

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

11 8041 - 8046 2014.01

Three Hundred Fifty Volt Photovoltaic Power Generation in Low Earth Orbit Reviewed

51 ( 1 ) 379 - 381 2014.01

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

42 ( 1 ) 191 - 198 2013.12

Investigation on Space Environmental Degradation Effects of Solar Cell Coverglass Reviewed

41 ( 12 ) 3471 - 3476 2013.11

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

41 ( 12 ) 3558 - 3564 2013.11

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

41 ( 12 ) 3477 - 3486 2013.08

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

50 ( 4 ) 853 - 859 2013.06

Special issue on spacecraft charging technology 2013 Reviewed

41 ( 12 ) 2013.01

Measurement of atomic-oxygen flux distribution Reviewed

32 597 - 606 2013.01

Special issue on spacecraft charging technologies Reviewed

40 ( 9 ) 2012.09

Spacecraft Charging Analysis of Large GEO Satellites Using MUSCAT Reviewed

40 ( 4 ) 1248 - 1256 2012.02

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

40 ( 2 ) 351 - 358 2012.01

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

2011.12

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

40 ( 2 ) 359 - 367 2011.11

Development of Electron-emitting Film for Spacecraft Charging Mitigation Reviewed

48 ( 3 ) 546 - 552 2011.05

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

48 ( 2 ) 326 - 335 2011.03

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

130 ( 9 ) 2010.11

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

47 ( 6 ) 966 - 973 2010.11

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

Hirokazu Masui,Kazuhiro Toyoda,Mengu Cho

2008.01

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

4th Space environment symposium 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

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

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

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

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

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

Takayuki Ose,Hirokazu Masui,Kazuhiro Toyoda,Mengu Cho