研究者詳細 - 増井　博一

論文 - 増井　博一

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Statistical Number of Primary Discharges Required for Solar Array Secondary Arc Tests 査読有り

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

Journal of Spacecraft and Rockets 2009年03月

Statistical number of primary discharges required for solar array secondary-arc tests 査読有り

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

Journal of Spacecraft and Rockets 46 ( 2 ) 438 - 448 2009年03月

記述言語：英語掲載種別：研究論文（学術雑誌）

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

DOI： 10.2514/1.37798

Scopus

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

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

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN ( 社団法人日本航空宇宙学会 ) ( 7 ) 11 - 17 2009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）

High-efficiency triple-junction (TJ) solar cells with monolithic diodes (MD) are being used for recent spacecraft solar arrays. Because the cell-to-cell inter-connector is usually connected on the MD pad, studying the effects of electrostatic discharge (ESD) on MD is necessary. Laboratory testing of two types of MD functions revealed that the weaker design was damaged by an energy discharge of 0.8J. With an external circuit simulating flight solar array, however, discharge as large as 9.3J didn't destroy the solar cell. Based on the test results, it was concluded that MD solar cells have sufficient resistance against ESD in orbit.

DOI： 10.2322/tstj.7.11

CiNii Article

その他リンク： https://ci.nii.ac.jp/naid/130000151792

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

OSE Takayuki, TOYODA Kazuhiro, MASUI Hirokazu, CHO Mengu

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN ( 社団法人日本航空宇宙学会 ) 7 ( 26 ) Pr_2_41 - Pr_2_46 2009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）

As the power level of Geostationary satellites increases, discharge phenomena on solar array are becoming serious threat to safe operation. Arcs on solar array can short-circuit the satellite circuit, decrease the satellite power, and then cause the satellite permanent failure. To prevent the failure caused by charging and arcing, it is necessary to investigate the mechanism of satellite charging and arcing phenomenon. The purpose of this paper is to investigate the occurrence condition of a secondary arc by measuring arc plasma characteristics in ground test. We measured the arc plasma temperature and identified the materials emitted using spectrometer at arbitrary time during arc occurring. We investigated the difference of secondary arcs occurrence condition during secondary arcs. From the spectroscopic measurement results, we found that it was necessary for shifting to the secondary arc that the metallic vapor same as the cathode material was emitted. In case of primary arc (PA) dimension changes, the probability of secondary arc and TSA occurrence became high. And plasma temperature was not affected by PA dimension, however the metallic vapor emission of silver was greatly affected. Thus, secondary arc occurrence greatly depends on metallic vapor emission from cathode.

DOI： 10.2322/tstj.7.Pr_2_41

CiNii Article

その他リンク： https://ci.nii.ac.jp/naid/130000151973

Generation of LEO-type atomic oxygen environment in laboratory for charging property database 査読有り

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

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

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

Scopus

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Electrostatic discharge plasma propagation speed on solar panel in simulated geosynchronous environment 査読有り

Masui H., Toyoda K., Cho M.

IEEE Transactions on Plasma Science 36 ( 5 PART 2 ) 2387 - 2394 2008年11月

記述言語：英語掲載種別：研究論文（学術雑誌）

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

DOI： 10.1109/TPS.2008.2003191

Scopus

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ESD ground test of solar array coupons for a greenhouse gases observing satellite in PEO 査読有り

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

IEEE Transactions on Plasma Science 36 ( 5 PART 2 ) 2413 - 2424 2008年11月

記述言語：英語掲載種別：研究論文（学術雑誌）

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

DOI： 10.1109/TPS.2008.2002823

Scopus

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Electrostatic Discharge Plasma Propagation Speed on Solar Panel in Simulated Geosynchronous Environment 査読有り

H. Masui, K. Toyoda, M. Cho

IEEE Transactions on Plasma Science 2008年10月

Probability distribution of secondary arc duration on solar array 査読有り

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

46th AIAA Aerospace Sciences Meeting and Exhibit 2008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）

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

DOI： 10.2514/6.2008-455

Scopus

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宇宙用シリコン太陽電池の放電による電気性能劣化査読有り

奥村哲平, 増井博一, 豊田和弘, 趙孟佑, 今泉充

日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences ( 社団法人日本航空宇宙学会 ) 55 ( 647 ) 590 - 596 2007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）

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

DOI： 10.2322/jjsass.55.590

CiNii Article

その他リンク： https://ci.nii.ac.jp/naid/10021152715

Effects of Magnetic Field Configuration on Thrust Performance in A Miniature Microwave Discharge Ion Thruster 査読有り

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

Journal of Applied Physics 2007年12月

宇宙用シリコン太陽電池の放電による電気性能劣化査読有り

奥村哲平, 増井博一, 豊田和弘, 今泉充，趙孟佑

日本航空宇宙学会論文集 2007年12月

Development of electron emitting film for spacecraft charging mitigation 査読有り

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

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

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

Scopus

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Effects of magnetic field configuration on thrust performance in a miniature microwave discharge ion thruster 査読有り

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

Journal of Applied Physics 102 ( 12 ) 2007年12月

記述言語：英語掲載種別：研究論文（学術雑誌）

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

DOI： 10.1063/1.2822456

Scopus

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

山本直嗣, 三好誠，増井博一，宮本尚使, 宗貞伸孝, 中島秀紀

日本航空宇宙学会論文集 2007年11月

Laboratory test campaign for ISO standardization of solar array ESD test methods 査読有り

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

Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting 5 3446 - 3453 2007年07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）

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

Scopus

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Analysis of electron and microwave behavior in microwave discharge neutralizer 査読有り

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

Transactions of the Japan Society for Aeronautical and Space Sciences 49 ( 164 ) 87 - 93 2006年12月

記述言語：英語掲載種別：研究論文（学術雑誌）

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

DOI： 10.2322/tjsass.49.87

Scopus

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Magnetic field design in miniature microwave discharge ion engines 査読有り

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

Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference 10 8172 - 8178 2006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）

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

Scopus

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Performance test of micro ion thruster using microwave discharge 査読有り

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

Vacuum 80 ( 11-12 ) 1239 - 1243 2006年09月

記述言語：英語掲載種別：研究論文（学術雑誌）

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

DOI： 10.1016/j.vacuum.2006.01.071

Scopus

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Analysis of Electron and Microwave Behaviors in Microwave Discharge Neutralizer 査読有り

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

Transactions of the Japan Society for Aeronautical and Space Sciences 2006年08月

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