1
國立成功大學「邁向頂尖大學計畫」
延攬優秀人才工作報告表
NCKU’s “Aim for the Top University Project”
Work Report Form for Distinguished Scholars
□續聘continuation of employment ■離職resignation
100 年 7 月 13 日更新 受聘者姓名
Name of the Employee 方惠寬 ■男 □女
Male Female
聘 期 Period of Employment
From 104 年(y) 6 月(m) 17 日(d) to 104 年(y) 12 月(m) 31 日(d) 研究或教學或科技研發與
管理計畫名稱 The project title of research,
teaching, technology development and management
邁向頂尖大學計畫
計畫主持人
（申請單位主管）
Project Investigator (Head of Department/Center)
談永頤
補助延聘編號
Grant Number HUA 104 - 3 - 2 - 233
一、 研究、教學、科技研發與管理工作全程經過概述。（由受聘人填寫）
Please summarize the entire research, teaching, or science and technology R&D and management work process (To be completed by the employee)
1. Work with Prof. Oyama on the development of TeNeP (electron temperature and density probe) for small satellites and performance verification in the space plasma operation chamber (SPOC).
Results of this research have been published in SCI journal “Review of Scientific Instruments”:
K.-I. Oyama, Y. W. Hsu, G. S. Jiang, W. H. Chen, C. Z. Cheng, H. K. Fang and W. T. Liu,
“Electron temperature and density probe for small aeronomy satellites”, Rev. Sci. Instrum. 86, 084703 (2015)
A compact and low power consumption instrument for measuring the electron density and temperature in the ionosphere has been developed by modifying the previously developed Electron Temperature Probe (ETP). A circuit block which controls frequency of the sinusoidal signal is added to the ETP so that the instrument can measure both Te in low frequency mode and Ne in high frequency mode from the floating potential shift of the electrode. The floating potential shift shows a minimum at the upper hybrid resonance frequency (fUHR). The instrument which is named
“TeNeP” can be used for tiny satellites which do not have enough conductive surface area for conventional DC Langmuir probe measurements. The instrument also eliminates the serious problems associated with the contamination of satellite surface as well as the sensor electrode.
2. Work with Prof. Nishida on the experiments of hydrogen generation by plasma discharge. Results of this research have been reported in international conference “Asia-Pacific International Symposium on the Basics and Applications of Plasma Technology, 2015”
Y. Nishida, H.C. Chaing, T. C. Chen, H. K. Fang, C.M. Liu and C. Z. Cheng, “Effect of Discharge Pulse Width on Decomposition of Hydrocarbons”, APSPT-9, Nagasaki University, Dec.12-15 (2015)
Hydrogen production system working on board using plasma discharges in high pressure condition over 1.5 atm. is under development. The produced hydrogen will be directly supplied to the fuel cell on vehicle. The original fuel for the system is hydrocarbons such as methane (CH4) or propane (C3H8). For those purposes mainly dielectric barrier discharge (DBD) non-thermal plasma system is employed herewith. Decomposition of hydrocarbons will make hydrogen and carbon powder, without producing COx. Decomposed carbon powder is attached fully on the electrodes and no contamination on the surrounding vacuum chamber wall is observed. For these discharges, high voltage pulse with width 5-30 μsec and maximum amplitude 15 kV is employed. At present, the pulse repetition is 4 kHz. Clear decompositions of hydrocarbons, at present ~70% of H2 in
2
comparison with the residual CH4 or 60% in case of C3H8, have been observed with input energy 110kJ/L (p=1.5 atm.) ~130 kJ/L (p=2.5 atm.) for CH4. In case of C3H8, 96 kJ/L at p=1.5 atm. is observed. The decomposition rate on the input pulse width applied to DBD electrode is investigated.
So far 20 μsec pulse showed the best efficiency for decomposition.
3. Work with Prof. Tam on the simulation of ion motion in microwave electron cyclotron resonance (ECR) ion thruster. Part of this research results will be reported in conference “Annual Meeting of the Physical Society of the Republic of China, 2016”
M. H. Shen, H. K. Fang, Sunny W. Y. Tam, Y. C. Chao and Y. H. Li, “Ion Pitch Angle Effects in Microwave ECR Ion Thruster”, PSROC-2016, Department of Physics, NSYSU, Jan 25-27 (2016) Ion thruster is a form of electric propulsion by generating thrust from ion acceleration. Unlike higher thrust chemical propulsions, electric propulsion, especially ion thruster, has strength of higher specific impulse (ISP), which means higher propulsion efficiency. Thus it has good fit for deep space explorations. Ion thrusters have been used for many space missions, such as Deep Space 1 in 1998 from NASA, Artemis in 2001 from ESA, Hayabusa 2 in 2014 from JAXA etc.
In the near future, small, lightweight, low power satellites on a scale of CubeSat with similarly small, lightweight, low power thrusters will be used for deep space explorations. We have designed a micro ion thruster with 2.2 cm in inner diameter and 20 cm in length. Electron Cyclotron Resonance (ECR) Plasma is generated under 875 G background magnetic fields supplied by magnetic coils. The ions are first accelerated from plasma generation region to the pre-acceleration region, and further accelerated to high speed in main acceleration region. Ions are accelerated by parallel electric fields supplied by metal grids. In the thruster, ion gyro-radius is 0.13 cm and temperature is close to room temperature.
To enhance thruster efficiency, ion transparency should be much higher than neutral particle (fuel) transparency in the pre-acceleration region. Ions should also be accelerated to higher initial speed before entering main acceleration region. To investigate the combination effects of electric and magnetic fields on ion motion in this region, single particle motion simulation is done by SIMION software. 3D simulation results show that the ion transparency is higher than 90% at all pitch angles when incident ion position offset is less than 3mm. For offset higher than 5mm, ion transparency is zero for all positive pitch angles, and less than 30% for negative pitch angles. Ion lensing effect, which reduces ion pitch angle effect and increases ion transparency, can be raised by increasing thruster boundary potential. Then the optimum pre-acceleration length can be determined to be the same as ion lensing focal length.
3
二、研究或教學或科技研發與管理成效評估（由計畫主持人或單位主管填寫）
Please evaluate the performance of research, teaching or science and technology R&D and management Work: (To be completed by Project Investigator or Head of Department/Center)
(1)是否達到延攬預期目標？
Has the expected goal of recruitment been achieved?
是。
(2)研究或教學或科技研發與管理的方法、專業知識及進度如何？
What are the methods, professional knowledge, and progress of the research, teaching, or R&D and management work?
受延攬人的研究專長為太空儀器研發、實驗電漿物理與電漿量測，他於補助期間應用其專業知識並與 本所三位教授合作，完成數項任務與階段性任務，分別為：
1. 協助可應用於微衛星之電子溫度密度探針的研發與測試，此成果已與小山孝一郎教授共同發表於國 際知名期刊 Review of Scientific Instruments。
2. 協助研發高電壓脈衝電源系統，並應用於本所西田靖教授之電漿產氫實驗，新建立的系統可產生兩 倍高的脈衝電壓與增進電漿產氫效率。此成果已與西田靖教授共同發表於亞太電漿基礎科學與應用技術國 際研討會(APSPT-2015)。
3. 與本所談永頤教授及成大航太系合作研發電漿離子推進器，階段性研究成果預計將發表於 2016 年 初中華民國物理年會。
綜合以上成果，受延攬人於補助期間之研究方法、專業知識及進度均表現良好且符合預期目標。
(3)受延攬人之研究或教學或科技研發與管理成果對該計畫(或貴單位)助益如何？
How have the research, teaching, or R&D and management results of the employed person given benefit to the project (or your unit)?
受延攬人於補助期間之研發成果對本所發展之助益包含：
1. 未來自主衛星與火箭科學酬載的研發。
2. 電漿推進系統的研發。
3. 電漿實驗、量測與產氫應用的整合。
(4)受延攬人於補助期間對貴單位或國內相關學術科技領域助益如何？
How has the employed person, during his or her term of employment, benefited your unit or the relevant domestic academic field?
受延攬人於補助期間對本所或國內相關學術科技領域發展之助益包含：
1. 未來國內自主衛星與火箭科學酬載的研發。
2. 電漿推進系統的研發。
3. 電漿實驗、量測與產氫應用的整合。
4. 太空電漿實驗腔體之維護、管理與相關實驗操作協助。
(5)具體工作績效或研究或教學或科技研發與管理成果：
Please describe the specific work performance, or the results of research, teaching, or R&D and management work:
1. SCI 期刊一篇。
2. 國際會議發表兩篇（一篇待發表）。
3. 太空電漿實驗腔體之維護、管理與相關實驗操作協助。
(6)是否續聘受聘人? Will you continue hiring the employed person?
□續聘Yes ■不續聘No 轉任科技部計畫「博士後研究」
4
※ 此報告表篇幅以三～四頁為原則。This report form should be limited to 3-4 pages in principle.
※ 此表格可上延攬優秀人才成果報告繳交說明網頁下載。
This report form can be downloaded in http://scholar.lib.ncku.edu.tw/explain/
