研究者詳細 - 増井　博一

論文 - 増井　博一

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Measurement of Atomic Oxygen Flux Distribution 査読有り

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

12th Spacecraft Charging Technology Conference 2012年05月

Development of flashover current simulator for ESD ground testing simulating GEO environment 査読有り

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

IEEE Trans on Plasma Science 2012年02月

Spacecraft Charging Analysis of Large GEO Satellites Using MUSCAT 査読有り

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

IEEE Trans on Plasma Science 2012年02月

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

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

IEEE Trans on Plasma Science 2012年02月

Research and Development of a Debris Removal Method Using Interaction between Space and Electrode with Applied Voltage 査読有り

SASAKI Reiso, MASUI Hirokazu, TOYODA Kazuhiro, CHO Mengu

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( 一般社団法人日本航空宇宙学会 ) 10 ( 28 ) Tr_47 - Tr_51 2012年01月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

There is a lot of debris in space. There are currently about 15,000 individual pieces of space debris that can be observed from the earth, with a likely even greater number existing with a size less than 10cm, the limiting size of earth-based observations. Fears exist that as space debris continues to increase, the Kessler Syndrome will occur, eventually preventing any form of spaceflight. The purpose of this research is to remove the debris to prevent such a situation from happening. For the first time, it is proposed to bias voltage on net electrodes, as the space debris will be charged by the plasma interaction. The charged debris will then be slowed by the electric field surrounding the net electrodes, causing the debris to re-enter the atmosphere. In this research, a 100μm copper powder is used, followed by 2mm Ellenpall. This presentation addresses how much the debris is charged and how far the debris is shifted by the electric field.

DOI： 10.2322/tastj.10.Tr_47

CiNii Article

その他リンク： https://ci.nii.ac.jp/naid/130003373352

B3 九州工業大学宇宙環境技術ラボラトリーの活動について : 宇宙機帯電と宇宙デブリから超小型衛星開発まで(超小型衛星(1)) 査読有り

増井博一, 趙孟佑, 赤星保浩, 豊田和弘, 岩田稔, Khan Arifur Rahman, Chen Yu, 遠藤泰史

スペース・エンジニアリング・コンファレンス講演論文集 ( 一般社団法人日本機械学会 ) 2010 ( 0 ) _B3 - 1_-_B3-4_ 2011年01月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

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

DOI： 10.1299/jsmesec.2010.19._B3-1_

CiNii Article

その他リンク： https://ci.nii.ac.jp/naid/110008743760

マイクロ波放電型イオンスラスタのシミュレーションコードの開発(<特集>電気推進・先端推進の数値シミュレーション) 査読有り

山本直嗣, 増井博一, 金川隆保, 新谷將, 中島秀紀

日本航空宇宙学会誌 ( 一般社団法人日本航空宇宙学会 ) 59 ( 691 ) 238 - 243 2011年01月

Effect of Atomic Oxygen Exposure on Surface Resistivity Change of Spacecraft Insulator Material 査読有り

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

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( 社団法人日本航空宇宙学会 ) ( 9 ) 1 - 8 2011年01月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

Spacecraft surface charging can lead to arcing and a loss of electricity generation capability in solar panels or even loss of a satellite. The charging problem may be further aggravated by atomic oxygen (AO) exposure in Low Earth orbits, which modifies the surface of materials like polyimide, Teflon, anti-reflective coatings, cover glass etc, used on satellite surfaces, affecting materials properties, such as resistivity, secondary electron emissivity and photo emission, which govern the charging behavior. These properties are crucial input parameters for spacecraft charging analysis. To study the AO exposure effect on charging governing properties, an atomic oxygen exposure facility based on laser detonation of oxygen was built. The facility produces AO with a peak velocity value around 10-12km/s and a higher flux than that existing in orbit. After exposing the polyimide test material to the equivalent of 10 years of AO fluence at an altitude of 700-800 km, surface charging properties like surface resistivity and volume resistivity were measured. The measurement was performed in a vacuum using the charge storage decay method at room temperature, which is considered the most appropriate for measuring resistivity for space applications. The results show that the surface resistivity increases and the volume resistivity remains almost the same for the AO exposure fluence of 5.4×10<sup>18</sup> atoms cm<sup>-2</sup>.

DOI： 10.2322/tastj.9.1

CiNii Article

その他リンク： https://ci.nii.ac.jp/naid/130000450582

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

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

Conference Record of the IEEE Photovoltaic Specialists Conference 1118 - 1123 2010年12月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

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.

DOI： 10.1109/PVSC.2010.5614721

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=78650119709&origin=inward

Preliminary experiments for establishing an ESD ground testing method of solar array 査読有り

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 2010年12月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

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.

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=78649827753&origin=inward

Characterization Experiments of Secondary Arcs on Solar Arrays: Threshold and Duration 査読有り

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

Journal of Spacecraft and Rockets 2010年06月

Effect of atomic oxygen exposure on resistivity change on spacecraft insulator materials 査読有り

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

Trans. JSASS Aerospace Tech. Japan 2010年02月

Research on Mitigation Method against Secondary Arcing on Solar Array 査読有り

WADA Tomohiro, MASUI Hirokazu, TOYODA Kazuhiro, CHO Mengu

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( 一般社団法人日本航空宇宙学会 ) 8 ( 27 ) Pr_2_19 - Pr_2_24 2010年01月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

The recent trend of satellite manufacturing is to increase its communication capacity, multi-purpose mission payload, electric power and lifetime. A short-circuit due to discharge on the solar array of the satellite hampers its target by causing serious problems, such as, lowering of power generation that ultimately halts the operation of solar array. In this paper, we have investigated possible mitigation methods against short-circuit due to discharge on solar array by applying coating and by changing the shape of Room Temperature Vulcanization: Silicon adhesive (RTV). The electrostatic discharge is mitigated by obtaining the event of secondary arc generated on each condition.

DOI： 10.2322/tastj.8.Pr_2_19

CiNii Article

その他リンク： https://ci.nii.ac.jp/naid/130001080207

Preliminary investigation of space debris removal method using electrostatic force in space plasma 査読有り

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

47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2009年12月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

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

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=78549291398&origin=inward

Secondary arc threshold meaurement on solar arrays for Japanese spacecraft charging guideline 査読有り

Masui H., Toyoda K., Cho M.

47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2009年12月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

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

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=78549258137&origin=inward

Preliminary study of development of space debris removal method using electrostatic force 査読有り

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

60th International Astronautical Congress 2009, IAC 2009 7 5772 - 5776 2009年12月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

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

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=77953602516&origin=inward

Spectroscopic Measurement of Secondary Arc Plasma on Solar Array 査読有り

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

Transactions of JSASS, Space Technology Japan 2009年11月

Environmental Effects on Solar Array Electrostatic Discharge Current Waveforms and Test Results 査読有り

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

Journal of Spacecraft and Rockets 2009年05月

Environmental effects on solar array electrostatic discharge current waveforms and test results 査読有り

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

Journal of Spacecraft and Rockets 46 ( 3 ) 697 - 705 2009年05月

記述言語：英語掲載種別：研究論文（学術雑誌）

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

DOI： 10.2514/1.41696

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=67650901789&origin=inward

ESD Ground Testing of Triple-Junction Solar Cells with Monolithic Diodes 査読有り

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

Transactions of JSASS, Space Technology Japan 2009年03月

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