To meet the high power demand of More-Electric-Aircraft (MEA), the system voltage needs to be increased, consequently increasing the insulation failure risk of related components. In this paper, on the basis of specific working scenarios and parameters of MEA, an experimental platform was built to simulate the insulation fault between windings in aircraft electric actuators, and several repetitive tests were conducted for partial discharge measurement within the range of 1 kHz. With sine voltage and square pulse voltage wave, the influence of frequency on Partial Discharge (PD) statistical parameters, including amplitude, repetition rate and phase, was compared and evaluated. Experimental results show that the PD Inception Voltage (PDIV) of the square pulse voltage wave is lower than that of sine wave in the specific frequency domain. With the increase of frequency, the PD amplitude decreases gradually, while the PD repetition rate increases almost linearly. The discharge is always concentrated at the end of the rising/falling edge. Compared with the values at 50 Hz, the discharge amplitude decreases by 80% and discharge repetition rate increases to 11.92 times at 1 kHz. The multiple cumulative breakdowns at a high frequency appear to be the main threat to the insulation failure. It is also unveiled that the decrease of the discharge delay time and the increase of the number of cycles resulted from the change of the space charge field intensity at a high frequency explain the decrease of the pulse amplitude and the increase of the discharge repetition rate. These experimental results contribute to the insulation testing and evaluation of related equipment in MEA, and are expected to provide reference for the design of high-power and high-voltage electric system in aircraft.
[1] 张卓然, 李进才, 韩建斌, 等. 多电飞机大功率高压直流起动发电机系统研究与实现[J]. 航空学报, 2020, 41(2):323537. ZHANG Z R, LI J C, HAN J B, et al. Research and implementation of high-power high-voltage DC brushless starter generator system for more-electric-aircraft application[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(2):323537(in Chinese).
[2] 张栋善, 谭涛. 基于多电飞机概念下的飞机电气发展方向[J]. 电子测试, 2018(6):125, 124. ZHANG D S, TAN T. Lectric development direction of aircraft based on the concept of multi electric aircraft[J]. Electronic Test, 2018(6):125, 124(in Chinese).
[3] SARLIOGLU B, MORRIS C T. More electric aircraft:Review, challenges, and opportunities for commercial transport aircraft[J]. IEEE Transactions on Transportation Electrification, 2015, 1(1):54-64.
[4] 严仰光, 秦海鸿, 龚春英. 多电飞机与电力电子[J]. 南京航空航天大学学报, 2014, 46(1):11-18. YAN Y G, QIN H H, GONG C Y. More electric aircraft and power electronics[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2014, 46(1):11-18(in Chinese).
[5] 王莉, 戴泽华, 杨善水, 等. 电气化飞机电力系统智能化设计研究综述[J]. 航空学报, 2019, 40(2):522405. WANG L, DAI Z H, YANG S S, et al. Review of intelligent design of electrified aircraft power system[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(2):522405(in Chinese).
[6] 牟成铭. 多电飞机电力系统稳定性分析[D]. 成都:电子科技大学, 2019. MOU C M. Stability study for a multi-electric aircraft power system[D]. Chengdu:University of Electronic Science and Technology of China, 2019(in Chinese).
[7] WHEELER P. Technology for the more and all electric aircraft of the future[C]//2016 IEEE International Conference on Automatica (ICA-ACCA). Piscataway:IEEE Press, 2016:1-5.
[8] GUASTAVINO F, DARDANO A. Life tests on twisted pairs in presence of partial discharges influence of the voltage waveform[J]. IEEE Transactions on Dielectrics and Electrical Insulation, 2012, 19(1):141-148.
[9] 李陈莹, 李鸿泽, 陈杰, 等. 高压XLPE电力电缆缓冲层放电问题分析[J]. 电力工程技术, 2018, 37(2):61-66. LI C Y, LI H Z, CHEN J, et al. Analysis of high voltage XLPE power cable buffer layer discharge problem[J]. Power Engineering Technology, 2018,37(2):61-66(in Chinese).
[10] 周凯, 吴广宁, 邓桃, 等. PWM脉冲电压下电磁线绝缘老化机理分析[J]. 中国电机工程学报, 2007, 27(24):24-29. ZHOU K, WU G N, DENG T, et al. Study on insulation aging properties of magnet wire under PWM voltages[J]. Proceedings of the CSEE, 2007, 27(24):24-29(in Chinese).
[11] WANG K, MENG G, DONG C, et al. The design of automatic test system used for PDIV measurement of inverter-fed motor[C]//20171st International Conference on Electrical Materials and Power Equipment (ICEMPE), 2017:651-654.
[12] WANG P, MONTANARI G C, CAVALLINI A. Partial discharge phenomenology and induced aging behavior in rotating machines controlled by power electronics[J]. IEEE Transactions on Industrial Electronics, 2014, 61(12):7105-7112.
[13] MAUSSION P, PICOT A, CHABERT M, et al. Lifespan and aging modeling methods for insulation systems in electrical machines:A survey[C]//2015 IEEE Workshop on Electrical Machines Design, Control and Diagnosis (WEMDCD). Piscataway:IEEE Press, 2015:279-288.
[14] 王莉, 曹璐, 严仰光. 航空交流故障电弧特性的研究[J]. 低压电器, 2011(2):19-23. WANG L, CAO L, YAN Y G. Research on arc fault characteristic for AC power system in aircraft[J]. Low Voltage Apparatus, 2011(2):19-23(in Chinese).
[15] AUBERT E, DIAW E N, URY V, et al. Preliminary measurements and simulations for space charges in aeronautical cables[C]//2018 IEEE International Conference on High Voltage Engineering and Application (ICHVE). Piscataway:IEEE Press, 2018:1-5.
[16] 张瑶佳, 王莉, 尹振东, 等. 基于HHT的航空直流串行电弧特征提取方法[J]. 航空学报, 2019, 40(1):522404. ZHANG Y J, WANG L, YIN Z D, et al. Research on characteristics extraction method of aviation DC serial arc fault based on HHT[J]. Acta Aeronautica et Astronautica Sinica, 2019, 40(1):522404(in Chinese).
[17] RADMANESH H, KAVOUSI A. Aircraft electrical power distribution system protection using smart circuit breaker[J]. IEEE Aerospace and Electronic Systems Magazine, 2017, 32(1):30-40.
[18] JIANG J, ZHAO M X, WEN Z, et al. Detection of DC series arc in more electric aircraft power system based on optical spectrometry[J]. High Voltage, 2020, 5(1):24-29.
[19] KARADJIAN M, IMBERT N, MUNIER C, et al. Partial discharge detection in an aeronautical power cable[C]//2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS), 2018:1-9.
[20] TAGHIA B, BILLARD T, CARAYON J, et al. Investigations on partial discharges risk in aeronautical rotating machine fed by HV DC 540VDC network[C]//2018 IEEE Electrical Insulation Conference (EIC). Piscataway:IEEE Press, 2018:491-494.
[21] XIN W, MAHMOUDI R, LENTS C E. A study of partial discharge in high voltage DC distribution systems for hybrid electric aircraft[C]//2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS), 2018:1-9.
[22] SILI E, CAMBRONNE J P, NAUDE N, et al. Polyimide lifetime under partial discharge aging:Effects of temperature, pressure and humidity[J]. IEEE Transactions on Dielectrics and Electrical Insulation, 2013, 20(2):435-442.
[23] SILI E, CAMBRONNE J P. About the validity of lifetime models of polymers under electrical discharge in aeronautical environment[C]//2013 Annual Report Conference on Electrical Insulation and Dielectric Phenomena, 2013:1306-1309.
[24] RUI R, COTTON I. Impact of low pressure aerospace environment on machine winding insulation[C]//2010 IEEE International Symposium on Electrical Insulation. Piscataway:IEEE Press, 2010:1-5.
[25] 武亮亮. 三电平变流器谐波特性分析与调制策略改进[D]. 北京:北京交通大学, 2019. WU L L. Harmonic characteristic analysis and modulation strategy improvement of three-level converters[D]. Beijing:Beijing Jiaotong University, 2019(in Chinese).
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