电脉冲除冰系统设计研究
|
摘要
飞机电脉冲除冰是利用高压电容器向脉冲线圈瞬间放电,在线圈周围建立起快速形成并迅速衰减的磁场,金属蒙皮内将出现涡流,产生一类似“锤击”的脉冲作用力,使冰破裂、脱离蒙皮并弹走。电脉冲除冰的显著特点是低能耗、高可靠性且几乎不需进行维护。
本文着重围绕电脉冲除冰系统设计制作展开研究,选择利用地面除冰试验来检验自制电脉冲除冰系统除冰效果的方案。自行设计制造出电脉冲除冰系统样机一套,其中包括非金属板的设计制作、脉冲线圈的绕制、充电电容器及快速晶闸管的选择、固定安装架的设计制作、控制箱制作及试验系统电路图设计等细节;搭建成地面电脉冲除冰试验台一个,通过试验测量出电容器放电瞬间脉冲线圈中产生的峰值电流和试验蒙皮上出现的振动加速度峰值,得出了放电电压与峰值电流之间的关系曲线、放电电压与振动加速度峰值之间的关系图像;建立了电脉冲除冰系统瞬间放电理想二阶RLC振荡回路模型,通过进行Matlab仿真,得出峰值电流随线圈电感、线圈电阻及时间的变化关系曲线;利用Visual C++编写了电脉冲除冰电气参数计算程序,并制作出相应的计算软件;通过人工结冰试验验证了电脉冲除冰方法的可行性,并为试验研究的深入进行提出展望。
De-icing of aircraft by using electro-impulse is accomplished by rapidly discharging high voltage capacitor into a wire coil rigidly supported just insided the aircraft skin.The discharge of capacitor through the impulse coil creates a rapidly forming and collapsing electro-magnetic field which induces eddy currents in the skin and creates a repulsive force resulting in a hammer-like force which cracks,debonds and expels ice on the skin surface. The promised advantages are very low engery,high reliability of de-icing and low maintenance.
This paper mainly focuses on the design of electro-impulse de-icing (EIDI) system, verifying the de-icing effect of a self-made electro-impulse de-icing system by several ground tests. The author managed to design and make a set of components of the electro-impulse de-icing system, including the non-metallic plate, the impulse coil, the choice of capacitor and fast thyristor, the fixed mount of the coil, a power supply-and-control box and the circuit diagram. A ground EIDI test-bed was built. In the test the peak current in the coil and the vibration peak acceleration on the skin could be got when the capacitor discharged. Then can get. the“discharge voltage-peak current”diagram and the“discharge voltage-vibration peak acceleration”diagram.The ideal second-order R-L-C current model of the EIDI system was built, and simulated the peak current changing with the coil inductor, coil resistance and time by using Matlab. The calculation program of the electrical parameters of the EIDI system has been completed with Visual C++, and corresponding software has been set up.Through the artificial icing test, it has been proved that the EIDI method is feasible and reliable.At last, based on the research conclusion , some prospect for further study on the test are given.
本文着重围绕电脉冲除冰系统设计制作展开研究,选择利用地面除冰试验来检验自制电脉冲除冰系统除冰效果的方案。自行设计制造出电脉冲除冰系统样机一套,其中包括非金属板的设计制作、脉冲线圈的绕制、充电电容器及快速晶闸管的选择、固定安装架的设计制作、控制箱制作及试验系统电路图设计等细节;搭建成地面电脉冲除冰试验台一个,通过试验测量出电容器放电瞬间脉冲线圈中产生的峰值电流和试验蒙皮上出现的振动加速度峰值,得出了放电电压与峰值电流之间的关系曲线、放电电压与振动加速度峰值之间的关系图像;建立了电脉冲除冰系统瞬间放电理想二阶RLC振荡回路模型,通过进行Matlab仿真,得出峰值电流随线圈电感、线圈电阻及时间的变化关系曲线;利用Visual C++编写了电脉冲除冰电气参数计算程序,并制作出相应的计算软件;通过人工结冰试验验证了电脉冲除冰方法的可行性,并为试验研究的深入进行提出展望。
De-icing of aircraft by using electro-impulse is accomplished by rapidly discharging high voltage capacitor into a wire coil rigidly supported just insided the aircraft skin.The discharge of capacitor through the impulse coil creates a rapidly forming and collapsing electro-magnetic field which induces eddy currents in the skin and creates a repulsive force resulting in a hammer-like force which cracks,debonds and expels ice on the skin surface. The promised advantages are very low engery,high reliability of de-icing and low maintenance.
This paper mainly focuses on the design of electro-impulse de-icing (EIDI) system, verifying the de-icing effect of a self-made electro-impulse de-icing system by several ground tests. The author managed to design and make a set of components of the electro-impulse de-icing system, including the non-metallic plate, the impulse coil, the choice of capacitor and fast thyristor, the fixed mount of the coil, a power supply-and-control box and the circuit diagram. A ground EIDI test-bed was built. In the test the peak current in the coil and the vibration peak acceleration on the skin could be got when the capacitor discharged. Then can get. the“discharge voltage-peak current”diagram and the“discharge voltage-vibration peak acceleration”diagram.The ideal second-order R-L-C current model of the EIDI system was built, and simulated the peak current changing with the coil inductor, coil resistance and time by using Matlab. The calculation program of the electrical parameters of the EIDI system has been completed with Visual C++, and corresponding software has been set up.Through the artificial icing test, it has been proved that the EIDI method is feasible and reliable.At last, based on the research conclusion , some prospect for further study on the test are given.
引文
[1]裘燮纲,韩凤华.飞机防冰系统[M].南京航空航天大学,2006年,60~81.
[2]裘燮纲,郭宪民.电脉冲系统参数的合理选择[J],南京航空学院学报,1993年4月,第25卷第2期,211~217.
[3]裘燮纲.电脉冲除冰系统(EIDI)电气参数计算,南京航空航天大学科技报告,1993年10月.
[4]姚远,林贵平.电脉冲除冰系统的建模与计算分析[J],飞机设计,2008年2月,第28卷第1期,64~75.
[5]秦曾煌.电工学(第五版)[M],高等教育出版社,1999年6月,220~276.
[6]樊尚春,吕俊芳,张庆荣,等.航空测试系统[M],北京航空航天大学出版社,2005年7月,120~158.
[7] Goldschmidt Rudolf. British Patent Specification No.505,433,May 5, 1939.
[8] Aircraft Icing Handbook Volume 1 of 3.AD-A238 040. March 1991,341~423.
[9] R.L.Schrag,G.W.Zunwalt. Electro-Impulse Deicing:Concept and Electrodynamic Studies,AIAA Paper NO.84-0021, Reno, Nevada, Jan. 9-12, 1984.
[10]W.D.Bernhart, G.W.Zumwalt. Electro-Impulse Deicing: Structural Dynamic Studies,Icing Tunnel Tests and Applications, AIAA Paper NO.84-0022, Reno, Nevada, January 9-12,1984.
[11]G.W.Zuniwalt. Icing Tunnel Tests of Electro-Impulse De-Icing of an Engine Inlet and High-Speed Wings, AIAA Paper No.85-0446, Reno, Nevada, January 14-17,1985.
[12]G.W.Zuniwalt.Electromagnetic Impulse De-icing Applied to a Nacelle Nose Lip,AIAA Paper No.85-1118, Reno, Nevada, January 14-17, 1985.
[13]G.W. Zumwalt, A.A. Mueller. Flight and Wind Tunnel Tests of an Electro-Impulse De-Icing System, AIAA Paper No. 84-2234,July 10-12, 1984.
[14]A.A.Mueller, D.R.Ellis, D.C.Bassett.Fliqht Evaluation of an Electro-Impulse De-Icinq System on a Liqht General Aviation Airplane,AIAA Paper No.84-2495, San Diego CA, Oct. 31-Nov. 7, 1984.
[15]G.W.Zurwalt, R.L.Schrag, W.D.Bernhart, R.A.Friedberg. Analysis and Tests for Design of an Electro-Impulse De-Icing System.NASA CR-174919, May 1985.
[16]Levin I.A..USSR Electric Impulse De-Icing System Design, Aircraft Engineering,July 1972,pp. 7.
[17]Levin I.A.An electric impulse de-icing system, Tech.Air,No.9,1971.
[18]Levin I.A.,etc. A device for removing ice from surfaces of thin-walled structures, U.S.Patent 3,809,341,May,1974.
[19]Robert I.Egbert.An Investigation of Power Line De-Icing by Electro-Impulse Methods,89WM094—4PWRD.
[20]Peter.B.Zieve. Low Voltage Electromagic Riveter,Ph.D.dissertation,University of Washington,Seattle,1986.
[21]Walsh, J.L.Predicting Transient Skin Pressure in Electro-Impulse Deicing of Airfoils, Masters Thesis, Wichita State University, May,1986.
[22]Gien, Peter Hilton.Structural dynamics of plates and shells subjected to electro-impulse de-icing forces,Ph.D. dissertation, Wichita State University,1989.
[23]Hartmann,J.,Zieve,P. Electromagnetic robotic end effector tool, Proceedings of the 14th Conference on production research and technology, SME/NSF, October,1987.
[24]Goehner,R.D.,Glover,N.I.,Hensley,G., Electro-Impulse De-Icing System for Aircraft, U.S.Patent 4,678,144,July,1987.
[25]Hassllm,L.A.,Lee,R.D. Electro-expulsive Separation System, U.S.Patent 4,690,353,September,1987.
[26]Ingram R.B.,Codner G.W.,Gerardi J.J. U.S. Patent 5,782,435, Electro-magnetic expulsion de-icing system, May 24, 1995.
[27]Shin J., Bond T.. Surface Roughness Due to Residual Ice in the Use of Low Power Deicing Systems,AIAA Paper 93-0031, Reno, NV, Jan. 1993.
[28]G.W.Zumwalt, R.L.Schrag, W.D.Bernhart, R.A.Friedberg. Electro-Impulse De-Icing Testing and Design, NASA CR-4175, 1988.
[29]G.W.Zumwalt,R.A.Friedberg. Designing an Electro-Impulse De-Icing System, AIAA Paper No.86-0545, Reno, Nevada,1986.
[30]Don O.Nelepovitz,Herman A. Rosenthal. Electro-Impulse De-Icing of aircraft engine inlets, AIAA Paper No.86-0546, Reno, Nevada,1986.
[31]D.E. Cozby. Effect of recent engine developments on transport aircraft ice protection requirements, The symposium for industry on the EIDI System,NASA Lewis Research Center.June 13,1985.
[32]G.J.Lewis.De-icing of Aerodynamic Surfaces Using Electromechanical Impulse,Ph.D.Thesis,Nottingham University,May 1985.
[33]G.J.Lewis. Electro-Impulse De-Icing Systems, AIAA Paper No.86-0547, Reno, Nevada,1986.
[34]R.Ross. Application of Electro-Impulse De-Icing to the NASA Lewis Altitude Wind Tunnel (AWT) turning vanes, AIAA Paper No.86-0548, Reno, Nevada,1986.
[35]W.D.Bernhart, P.H.Gien. A structural dynamics investigation related to EIDI applications, AIAA Paper No.86-0550, Reno, Nevada,1986.
[36]Peter B. Zieve. Low voltage Electro-Impulse De-Icer, AIAA Paper No.88-0021, Reno, Nevada,1988.
[37]Peter B.Zieve. Low voltage Electromagnetic Riveter, Paper AD86-680,Society of Manufacturing Engineers,October,1986.
[38]Bernhart.W.D., Schrag, R.L. Electro-Impulse De-Icing:Electrodymnamic Solution by Discrete Elements, AIAA Paper No.88-0018, Reno, Nevada,1988.
[39]G.W.Zumwalt. Electro-Impulse De-Icing, AIAA Paper No.88-0019, Reno, Nevada,1988.
[40]Nelepovitz D. Test and Analysis of Electro-Impulse De-Icing Systems in Turbine Engine Inlets,AIAA Paper No.88-0020, Reno, Nevada,1988.
[41]Samuel O.Smith. Modeling and Strain Gauging of Eddy Current Repulsion Deicing System,AIAA Paper No.93-0296, Reno, Nevada,1993.
[42]Kamel Al-Khalil. Thermo-Mechanical Expulsion Deicing System—TMEDS, AIAA Paper No.2007-692, Reno, Nevada,2007.
[43]李红梅,邱景辉,林澍.脉冲电流测量线圈的理论分析与试验研究[J],电子测量与仪器学报,2004年增刊,703~707.
[44]申烛,钱政,罗承沐,等.Rogowski线圈的测量误差分析和估计[J],高电压技术,2003年7月,Vol.29 No.1,5~7.
[45]龚兴根.脉冲大电流的测量[J],爆轰波与冲击波,1999年12月,第4期,158~169.
[46]谢祖荣,周晓正,曾建唐,等。强电流脉冲充磁技术研究与设计问题[C],中国电工技术学会电力电子学会第八届学术年会论文集,901~904.
[2]裘燮纲,郭宪民.电脉冲系统参数的合理选择[J],南京航空学院学报,1993年4月,第25卷第2期,211~217.
[3]裘燮纲.电脉冲除冰系统(EIDI)电气参数计算,南京航空航天大学科技报告,1993年10月.
[4]姚远,林贵平.电脉冲除冰系统的建模与计算分析[J],飞机设计,2008年2月,第28卷第1期,64~75.
[5]秦曾煌.电工学(第五版)[M],高等教育出版社,1999年6月,220~276.
[6]樊尚春,吕俊芳,张庆荣,等.航空测试系统[M],北京航空航天大学出版社,2005年7月,120~158.
[7] Goldschmidt Rudolf. British Patent Specification No.505,433,May 5, 1939.
[8] Aircraft Icing Handbook Volume 1 of 3.AD-A238 040. March 1991,341~423.
[9] R.L.Schrag,G.W.Zunwalt. Electro-Impulse Deicing:Concept and Electrodynamic Studies,AIAA Paper NO.84-0021, Reno, Nevada, Jan. 9-12, 1984.
[10]W.D.Bernhart, G.W.Zumwalt. Electro-Impulse Deicing: Structural Dynamic Studies,Icing Tunnel Tests and Applications, AIAA Paper NO.84-0022, Reno, Nevada, January 9-12,1984.
[11]G.W.Zuniwalt. Icing Tunnel Tests of Electro-Impulse De-Icing of an Engine Inlet and High-Speed Wings, AIAA Paper No.85-0446, Reno, Nevada, January 14-17,1985.
[12]G.W.Zuniwalt.Electromagnetic Impulse De-icing Applied to a Nacelle Nose Lip,AIAA Paper No.85-1118, Reno, Nevada, January 14-17, 1985.
[13]G.W. Zumwalt, A.A. Mueller. Flight and Wind Tunnel Tests of an Electro-Impulse De-Icing System, AIAA Paper No. 84-2234,July 10-12, 1984.
[14]A.A.Mueller, D.R.Ellis, D.C.Bassett.Fliqht Evaluation of an Electro-Impulse De-Icinq System on a Liqht General Aviation Airplane,AIAA Paper No.84-2495, San Diego CA, Oct. 31-Nov. 7, 1984.
[15]G.W.Zurwalt, R.L.Schrag, W.D.Bernhart, R.A.Friedberg. Analysis and Tests for Design of an Electro-Impulse De-Icing System.NASA CR-174919, May 1985.
[16]Levin I.A..USSR Electric Impulse De-Icing System Design, Aircraft Engineering,July 1972,pp. 7.
[17]Levin I.A.An electric impulse de-icing system, Tech.Air,No.9,1971.
[18]Levin I.A.,etc. A device for removing ice from surfaces of thin-walled structures, U.S.Patent 3,809,341,May,1974.
[19]Robert I.Egbert.An Investigation of Power Line De-Icing by Electro-Impulse Methods,89WM094—4PWRD.
[20]Peter.B.Zieve. Low Voltage Electromagic Riveter,Ph.D.dissertation,University of Washington,Seattle,1986.
[21]Walsh, J.L.Predicting Transient Skin Pressure in Electro-Impulse Deicing of Airfoils, Masters Thesis, Wichita State University, May,1986.
[22]Gien, Peter Hilton.Structural dynamics of plates and shells subjected to electro-impulse de-icing forces,Ph.D. dissertation, Wichita State University,1989.
[23]Hartmann,J.,Zieve,P. Electromagnetic robotic end effector tool, Proceedings of the 14th Conference on production research and technology, SME/NSF, October,1987.
[24]Goehner,R.D.,Glover,N.I.,Hensley,G., Electro-Impulse De-Icing System for Aircraft, U.S.Patent 4,678,144,July,1987.
[25]Hassllm,L.A.,Lee,R.D. Electro-expulsive Separation System, U.S.Patent 4,690,353,September,1987.
[26]Ingram R.B.,Codner G.W.,Gerardi J.J. U.S. Patent 5,782,435, Electro-magnetic expulsion de-icing system, May 24, 1995.
[27]Shin J., Bond T.. Surface Roughness Due to Residual Ice in the Use of Low Power Deicing Systems,AIAA Paper 93-0031, Reno, NV, Jan. 1993.
[28]G.W.Zumwalt, R.L.Schrag, W.D.Bernhart, R.A.Friedberg. Electro-Impulse De-Icing Testing and Design, NASA CR-4175, 1988.
[29]G.W.Zumwalt,R.A.Friedberg. Designing an Electro-Impulse De-Icing System, AIAA Paper No.86-0545, Reno, Nevada,1986.
[30]Don O.Nelepovitz,Herman A. Rosenthal. Electro-Impulse De-Icing of aircraft engine inlets, AIAA Paper No.86-0546, Reno, Nevada,1986.
[31]D.E. Cozby. Effect of recent engine developments on transport aircraft ice protection requirements, The symposium for industry on the EIDI System,NASA Lewis Research Center.June 13,1985.
[32]G.J.Lewis.De-icing of Aerodynamic Surfaces Using Electromechanical Impulse,Ph.D.Thesis,Nottingham University,May 1985.
[33]G.J.Lewis. Electro-Impulse De-Icing Systems, AIAA Paper No.86-0547, Reno, Nevada,1986.
[34]R.Ross. Application of Electro-Impulse De-Icing to the NASA Lewis Altitude Wind Tunnel (AWT) turning vanes, AIAA Paper No.86-0548, Reno, Nevada,1986.
[35]W.D.Bernhart, P.H.Gien. A structural dynamics investigation related to EIDI applications, AIAA Paper No.86-0550, Reno, Nevada,1986.
[36]Peter B. Zieve. Low voltage Electro-Impulse De-Icer, AIAA Paper No.88-0021, Reno, Nevada,1988.
[37]Peter B.Zieve. Low voltage Electromagnetic Riveter, Paper AD86-680,Society of Manufacturing Engineers,October,1986.
[38]Bernhart.W.D., Schrag, R.L. Electro-Impulse De-Icing:Electrodymnamic Solution by Discrete Elements, AIAA Paper No.88-0018, Reno, Nevada,1988.
[39]G.W.Zumwalt. Electro-Impulse De-Icing, AIAA Paper No.88-0019, Reno, Nevada,1988.
[40]Nelepovitz D. Test and Analysis of Electro-Impulse De-Icing Systems in Turbine Engine Inlets,AIAA Paper No.88-0020, Reno, Nevada,1988.
[41]Samuel O.Smith. Modeling and Strain Gauging of Eddy Current Repulsion Deicing System,AIAA Paper No.93-0296, Reno, Nevada,1993.
[42]Kamel Al-Khalil. Thermo-Mechanical Expulsion Deicing System—TMEDS, AIAA Paper No.2007-692, Reno, Nevada,2007.
[43]李红梅,邱景辉,林澍.脉冲电流测量线圈的理论分析与试验研究[J],电子测量与仪器学报,2004年增刊,703~707.
[44]申烛,钱政,罗承沐,等.Rogowski线圈的测量误差分析和估计[J],高电压技术,2003年7月,Vol.29 No.1,5~7.
[45]龚兴根.脉冲大电流的测量[J],爆轰波与冲击波,1999年12月,第4期,158~169.
[46]谢祖荣,周晓正,曾建唐,等。强电流脉冲充磁技术研究与设计问题[C],中国电工技术学会电力电子学会第八届学术年会论文集,901~904.