EPE Association: EPE 2013 - DS3m: Electrical Systems in Aerospace, Space, and EMC related phenomena

EPE 2013 - DS3m: Electrical Systems in Aerospace, Space, and EMC related phenomena
You are here: EPE Documents > 01 - EPE & EPE ECCE Conference Proceedings > EPE 2013 ECCE Europe - Conference > EPE 2013 - Topic 19: Electrical systems in aerospace, space, surface and marine transport (not road) > EPE 2013 - DS3m: Electrical Systems in Aerospace, Space, and EMC related phenomena

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   Analysis on Power Supply and Distribution System for Spacecraft Based on Reliability
By Lingjie KONG, Li WANG, Ligang RUAN, Shanshui YANG [View]
[Download]

Abstract: Reliable operation of the power supply and distribution system is of vital importance for the safety of a spacecraft. In this paper, a topology suitable for power supply and distribution system and its grid-connecting operation is introduced, then conceptions of basic reliability and mission reliability are explained. Based on system life obeying exponential distribution, reliability of the system is assessed and evaluated. Improvements are proposed for the deficiencies.

   Common mode current calculation in a driver stage for power semiconductor modules
By Rodolphe DE MAGLIE, Markus NUBER, Juergen ENGSTLER, Alfred ENGLER [View]
[Download]

Abstract: This paper deals with the calculation of the common mode current at the input power supply of adriver board for power semiconductor modules. Applying a proven method for main power circuit tothe driver stage, calculations are successfully compared with measurements and lead to an aerospacecompliant filter design.

   Comparison of converter topologies for battery-powered high-speed drives considering different cooling conditions and semiconductor materials for ultra light-we
By Roman HORFF, Mark-Matthias BAKRAN [View]
[Download]

Abstract: This paper presents a comparison of two-level and three-level converters for high frequency drives. Themaximum output power per chip area is calculated and compared by the Total Harmonic Distortion(THD).A variable DC-link voltage is assumed and it is derived, that the three-level topologies suffer more froman increasing DC-link voltage than the two-level inverter. The influence of the cooling system on thechoice of topology is discussed. It is shown that three-level converters do not profit as much as two-levelinverter of the benefit from liquid cooling system in comparison to forced-air cooling.Regarding fast switching silicon carbide devices, a calculation shows, that the converter weight can bereduced significantly.

   Design of an Electrical Distribution Test Rig for Validation of Equipment for More Electrical Aircraft
By Jean Ernst BESTER, Augustin MPANDA, Niels POLFLIET, Jeroen VAN DEN KEYBUS, Guillaume MARTIAL [View]
[Download]

Abstract: In order to mitigate economical, ecological and technological challenges aircraft manufacturers haveshifted towards more electrical aircraft, bringing with it many new technologies to be implementedand a redesign of the existing electrical network. This paper details the development of an electricaldistribution centre as taking place under the European Framework 7 Clean Sky Program. Thedeveloped distribution centre is to be integrated into an existing electrical test bench which recreatesthe entire electrical system of an aircraft and allows both aircraft and aerospace equipmentmanufactures to conduct verification activities over different aircraft electrical architectures. The taskthen of the distribution centre is to bring an element of flexibility to the existing electrical test bench inorder for it to be easily reconfigured into any aircraft architecture, including both airplane androtorcraft. In order to achieve this, the distribution centre contains both low voltage and high voltageDC bus bars. The connection of sources and loads to the bus bars, and the interconnection between busbars themselves, are achieved by using Racks, each of which contains a controllable and sequenceableswitching element together with high fidelity proprietary measurement instrumentation and embeddedprotection. The entire system has undergone in-house testing and successfully passed factoryacceptance tests before its delivery and subsequent commissioning, with the results being noted anddiscussed here.

   Electric Drive System for a Sailplane
By Martin RANGE, Friedrich WERNER, Marcus ZIEGLER [View]
[Download]

Abstract: The paper deals with the fundamental research for the design of an electric drive system for a sailplane in cooperation with the oldest and one of the largest sailplane manufactures \textit{Alexander Schleicher}\footnote{The sailplane manufacturer \textit{Alexander Schleicher} (founded in 1927) has its corporate headquarters in 36163 Poppenhausen, Wasserkuppe; Germany}. The realizability of this purpose is checked by a system perspective of the electric drive system. Different approaches are considered, e.g. a system with a gear, a downsized motor or an air drag optimized sustainer system to reduce the sinking due to the sustainer system.

   EMI Terminal Modelling of DC-Fed Motor Drives
By Hemant BISHNOI, Rolando BURGOS, Paolo MATTAVELLI, Dushan BOROYEVICH [View]
[Download]

Abstract: A three-terminal noise-model has been shown earlier to predict the common-mode noise currents at the input and output side of a dc fed motor-drive system. Accuracy of this model was found to be good up to 30 MHz. The DO-160 standards for aerospace applications however are based on total noise and hence simulations based on common-mode model alone are inadequate for EMC compliance. This paper proposes simple terminal models to predict the differential mode noise currents in a motor-drive system. In the end, predictions from the common and differential mode models will be combined to estimate the total noise at the input and output side of the motor-drive system. The proposed method is validated with experiments.

   Experimental validation of a hybrid emergency network with low and medium voltage Li-Ion batteries for more electrical aircraft
By Fabien LACRESSONNIERE, Eric BRU, Guillaume FONTES, Xavier ROBOAM [View]
[Download]

Abstract: This paper deals with a hybrid electrical network for an aircraft in emergency operation. The principle of this network is to hybridize, through a bidirectional DC/DC converter, a high speed Ram Air Turbine (RAT) with an electrochemical Lithium Ion accumulator. A design study of DC/DC power converters, according to the voltage of the accumulator, is presented. The results of this study have shown that utilization of a medium-voltage battery can be a good mass / efficiency trade off of the overall system. Some experiments on a lab test bench have allowed validating the principle of the hybridization and several energy management strategies have been tested with low and medium voltage lithium ion batteries.

   MODELING AND ANALYSIS OF AN INNOVATIVE WASTE HEAT RECOVERY SYSTEM FOR HELICOPTERS
By Georgios CHRISTIDIS, Ioannis KARATZAFERIS, Matthieu SAUTREUIL, Emmanuel TATAKIS, Nikolaos PAPANIKOLAOU [View]
[Download]

Abstract: The efficiency of helicopters is limited due to the high power losses of combustion engines, a fraction of which can be recovered and provided to the electrical bus by exploiting the heat found in the exhaust gases and through power electronics converters. The first system recovers energy through a thermoelectric generator, whereas the second through a permanent magnet generator rotated by a steam turbine. A third power converter, connected to a supercapacitor bank, compensates the peak currents demanded by the loads. Since extensive simulations have to be run in order to validate the feasibility of those systems, average models of the power converters are derived, and their accuracy is examined. Finally, based on those average models, the developed control strategy is examined

   Multiobjective Optimization of a Power Supply for Space Application Using a Flexible CAD Tool
By Olivier DEBLECKER, Christophe VERSÈLE, Zacharie DE GREVE, Jacques LOBRY [View]
[Download]

Abstract: This paper presents the adaptation of a previously published CAD tool that was initially conceived for high power isolated dc-dc converters, to the multiobjective optimal design of a switch-mode power supply for space application. The main changes to the existing tool concern the magnetic elements (transformer and inductor), the reduction of voltage and current ratings of the semiconductor devices, the cooling aspects, and the input filter design. The database of the tool is also enriched with silicon carbide devices in order to highlight, for the considered application, the benefits of using this new technology. The Pareto fronts in terms of power loss and mass are shown for two sets of electrical specifications of the power supply. Several solutions are analyzed in detail through the values of the optimization variables.

   Optimal LCL Filter Design for 3-phase Space Vector PWM Rectifiers on Variable Frequency Aircraft Power System
By Lei SHEN, Greg ASHER, Pat WHEELER, Serhiy BOZHKO [View]
[Download]

Abstract: Regulations restrict the harmonics permitted on civil aircraft electrical power supplies. However, the More Electric Aircraft (MEA) will see a significant increase in high switching frequency power electronic conversion which may include 3-phase active PWM rectifiers. This paper describes an optimal LCL filter design method for 3-phase 2-level active rectifiers affixed to a variable frequency grid. The current harmonics for both synchronous and asynchronous Space Vector PWM are analytically calculated. A search method is used to find the optimal filter solution to meet the RTCA DO-160E harmonic specifications for variable grid frequency from 360Hz to 800Hz.

   Prognostic Capability Evaluation of Power Electronic Modules in Transportation Electrification and Vehicle Systems
By Alireza ALGHASSI [View]
[Download]

Abstract: Health management and reliability are fundamental part of the design and development cycle of thepower electronic products. This paper presents the study and investigation about the prognostic andhealth management of power electronic IGBT module. To achieve this aim, a fusion approach hasbeen introduced. In addition, for the physic based part of approach, a thermal model is used to predicttemperatures of inaccessible locations within the power module. Then by employing the rainflowalgorithm, the remaining life of the power electronic IGBT module has been determined.

   Real-time Simulation of More-Electric Aircraft Power Systems
By Leonardo MONTEALEGRE LOBO, Christian DUFOUR, Jean MAHSEREDJIAN [View]
[Download]

Abstract: The More-Electric Aircraft (MEA) requires thorough testing procedures to meet extreme securityrequirements. Real-time simulation technologies have been traditionally part of this validation andtesting process for conventional aircraft designs. The MEA concept is now pushing HIL technologiestoward aircraft electric system real-time simulation. This paper discusses the real-time simulationrequirements for MEA, analyses an aircraft electrical power system, identifies real-time modelingbottlenecks and validation needs. The case of Bombardier Global Express aircraft is used for thispurpose.

   Research on Methods of Distortion Spectrum Analysis For Aircraft VFAC Power System
By Shanshui YANG, Mengdi CAI, Jian ZHAO, Li WANG, Yan LIU [View]
[Download]

Abstract: A lot of power electronic conversion devices are used in the variable frequency AC power system. Harmonic pollution and voltage distortion have serious impact on power quality, and voltage distortion spectrum is an important indicator to measure the electric power quality of aircraft. The distortion spectrum is analyzed for aircraft VFAC power system. The frequency ranged 360 ~ 800Hz brings a wider frequency range distortion spectrum according to MIL-STD-704F. Based on digital filtering technology, the paper proposes a distortion spectrum testing method. The test system can collect synchronous voltage signal by PXI high-speed data acquisition card. The characteristics of digital notch filter are analyzed by simulation, and Butterworth notch filter with four orders is designed for filtering out fundamental component of the distortion voltage. Experimental results show that this test method can extract the fundamental frequency, calculate distortion factor, obtain distortion spectrum. The feasibility and reliability of the test system are verified.

   Suppressing Overvoltage of Carbodies for a Highspeed EMU
By Satoru HATSUKADE, Kenji FUJINO, Satoru KANNO [View]
[Download]

Abstract: Overvoltage is created on carbodies of a highspeed electric multiple unit (EMU) when the train raises its pantograph or when its main circuit breaker is switched. This paper outlines the mechanism behind the phenomenon of overvoltage generation on carbodies of the highspeed train, proposing suppressing method, and the results of verification of the method. The results indicate the efficiency of the method, where the overvoltage is reduced by 50\% from the maximum.

   The Characteristics of Aerospace DC arc Fault Current
By Zhen MENG, Li WANG, Qiangang SUN [View]
[Download]

Abstract: Arc fault is of great destructiveness and can threaten the safety of electrical system. It is necessary to understand the behaviors and special characteristics of arc fault to develop devices that can detect arc faults. In this paper, the DC arc fault data are obtained via arcing tests according to SAE AS5692 and AS6019. The average value, standard deviation in time domain, spectrum in frequency domain of normal or fault current are analyzed by statistics. The results show the difference between normal and arc fault current. The relationship between the characters of fault current with resistive load in time domain and the supply voltage is also discussed. The study of DC arc fault characteristics lays theoretical foundation for the aircraft DC arc faults detection and protection.

EPE 2013 - DS3m: Electrical Systems in Aerospace, Space, and EMC related phenomena
You are here: EPE Documents > 01 - EPE & EPE ECCE Conference Proceedings > EPE 2013 ECCE Europe - Conference > EPE 2013 - Topic 19: Electrical systems in aerospace, space, surface and marine transport (not road) > EPE 2013 - DS3m: Electrical Systems in Aerospace, Space, and EMC related phenomena
	[return to parent folder]

	Analysis on Power Supply and Distribution System for Spacecraft Based on Reliability By Lingjie KONG, Li WANG, Ligang RUAN, Shanshui YANG	[View] [Download]
Abstract: Reliable operation of the power supply and distribution system is of vital importance for the safety of a spacecraft. In this paper, a topology suitable for power supply and distribution system and its grid-connecting operation is introduced, then conceptions of basic reliability and mission reliability are explained. Based on system life obeying exponential distribution, reliability of the system is assessed and evaluated. Improvements are proposed for the deficiencies.

	Common mode current calculation in a driver stage for power semiconductor modules By Rodolphe DE MAGLIE, Markus NUBER, Juergen ENGSTLER, Alfred ENGLER	[View] [Download]
Abstract: This paper deals with the calculation of the common mode current at the input power supply of adriver board for power semiconductor modules. Applying a proven method for main power circuit tothe driver stage, calculations are successfully compared with measurements and lead to an aerospacecompliant filter design.

	Comparison of converter topologies for battery-powered high-speed drives considering different cooling conditions and semiconductor materials for ultra light-we By Roman HORFF, Mark-Matthias BAKRAN	[View] [Download]
Abstract: This paper presents a comparison of two-level and three-level converters for high frequency drives. Themaximum output power per chip area is calculated and compared by the Total Harmonic Distortion(THD).A variable DC-link voltage is assumed and it is derived, that the three-level topologies suffer more froman increasing DC-link voltage than the two-level inverter. The influence of the cooling system on thechoice of topology is discussed. It is shown that three-level converters do not profit as much as two-levelinverter of the benefit from liquid cooling system in comparison to forced-air cooling.Regarding fast switching silicon carbide devices, a calculation shows, that the converter weight can bereduced significantly.

	Design of an Electrical Distribution Test Rig for Validation of Equipment for More Electrical Aircraft By Jean Ernst BESTER, Augustin MPANDA, Niels POLFLIET, Jeroen VAN DEN KEYBUS, Guillaume MARTIAL	[View] [Download]
Abstract: In order to mitigate economical, ecological and technological challenges aircraft manufacturers haveshifted towards more electrical aircraft, bringing with it many new technologies to be implementedand a redesign of the existing electrical network. This paper details the development of an electricaldistribution centre as taking place under the European Framework 7 Clean Sky Program. Thedeveloped distribution centre is to be integrated into an existing electrical test bench which recreatesthe entire electrical system of an aircraft and allows both aircraft and aerospace equipmentmanufactures to conduct verification activities over different aircraft electrical architectures. The taskthen of the distribution centre is to bring an element of flexibility to the existing electrical test bench inorder for it to be easily reconfigured into any aircraft architecture, including both airplane androtorcraft. In order to achieve this, the distribution centre contains both low voltage and high voltageDC bus bars. The connection of sources and loads to the bus bars, and the interconnection between busbars themselves, are achieved by using Racks, each of which contains a controllable and sequenceableswitching element together with high fidelity proprietary measurement instrumentation and embeddedprotection. The entire system has undergone in-house testing and successfully passed factoryacceptance tests before its delivery and subsequent commissioning, with the results being noted anddiscussed here.

	Electric Drive System for a Sailplane By Martin RANGE, Friedrich WERNER, Marcus ZIEGLER	[View] [Download]
Abstract: The paper deals with the fundamental research for the design of an electric drive system for a sailplane in cooperation with the oldest and one of the largest sailplane manufactures \textit{Alexander Schleicher}\footnote{The sailplane manufacturer \textit{Alexander Schleicher} (founded in 1927) has its corporate headquarters in 36163 Poppenhausen, Wasserkuppe; Germany}. The realizability of this purpose is checked by a system perspective of the electric drive system. Different approaches are considered, e.g. a system with a gear, a downsized motor or an air drag optimized sustainer system to reduce the sinking due to the sustainer system.

	EMI Terminal Modelling of DC-Fed Motor Drives By Hemant BISHNOI, Rolando BURGOS, Paolo MATTAVELLI, Dushan BOROYEVICH	[View] [Download]
Abstract: A three-terminal noise-model has been shown earlier to predict the common-mode noise currents at the input and output side of a dc fed motor-drive system. Accuracy of this model was found to be good up to 30 MHz. The DO-160 standards for aerospace applications however are based on total noise and hence simulations based on common-mode model alone are inadequate for EMC compliance. This paper proposes simple terminal models to predict the differential mode noise currents in a motor-drive system. In the end, predictions from the common and differential mode models will be combined to estimate the total noise at the input and output side of the motor-drive system. The proposed method is validated with experiments.

	Experimental validation of a hybrid emergency network with low and medium voltage Li-Ion batteries for more electrical aircraft By Fabien LACRESSONNIERE, Eric BRU, Guillaume FONTES, Xavier ROBOAM	[View] [Download]
Abstract: This paper deals with a hybrid electrical network for an aircraft in emergency operation. The principle of this network is to hybridize, through a bidirectional DC/DC converter, a high speed Ram Air Turbine (RAT) with an electrochemical Lithium Ion accumulator. A design study of DC/DC power converters, according to the voltage of the accumulator, is presented. The results of this study have shown that utilization of a medium-voltage battery can be a good mass / efficiency trade off of the overall system. Some experiments on a lab test bench have allowed validating the principle of the hybridization and several energy management strategies have been tested with low and medium voltage lithium ion batteries.

	MODELING AND ANALYSIS OF AN INNOVATIVE WASTE HEAT RECOVERY SYSTEM FOR HELICOPTERS By Georgios CHRISTIDIS, Ioannis KARATZAFERIS, Matthieu SAUTREUIL, Emmanuel TATAKIS, Nikolaos PAPANIKOLAOU	[View] [Download]
Abstract: The efficiency of helicopters is limited due to the high power losses of combustion engines, a fraction of which can be recovered and provided to the electrical bus by exploiting the heat found in the exhaust gases and through power electronics converters. The first system recovers energy through a thermoelectric generator, whereas the second through a permanent magnet generator rotated by a steam turbine. A third power converter, connected to a supercapacitor bank, compensates the peak currents demanded by the loads. Since extensive simulations have to be run in order to validate the feasibility of those systems, average models of the power converters are derived, and their accuracy is examined. Finally, based on those average models, the developed control strategy is examined

	Multiobjective Optimization of a Power Supply for Space Application Using a Flexible CAD Tool By Olivier DEBLECKER, Christophe VERSÈLE, Zacharie DE GREVE, Jacques LOBRY	[View] [Download]
Abstract: This paper presents the adaptation of a previously published CAD tool that was initially conceived for high power isolated dc-dc converters, to the multiobjective optimal design of a switch-mode power supply for space application. The main changes to the existing tool concern the magnetic elements (transformer and inductor), the reduction of voltage and current ratings of the semiconductor devices, the cooling aspects, and the input filter design. The database of the tool is also enriched with silicon carbide devices in order to highlight, for the considered application, the benefits of using this new technology. The Pareto fronts in terms of power loss and mass are shown for two sets of electrical specifications of the power supply. Several solutions are analyzed in detail through the values of the optimization variables.

	Optimal LCL Filter Design for 3-phase Space Vector PWM Rectifiers on Variable Frequency Aircraft Power System By Lei SHEN, Greg ASHER, Pat WHEELER, Serhiy BOZHKO	[View] [Download]
Abstract: Regulations restrict the harmonics permitted on civil aircraft electrical power supplies. However, the More Electric Aircraft (MEA) will see a significant increase in high switching frequency power electronic conversion which may include 3-phase active PWM rectifiers. This paper describes an optimal LCL filter design method for 3-phase 2-level active rectifiers affixed to a variable frequency grid. The current harmonics for both synchronous and asynchronous Space Vector PWM are analytically calculated. A search method is used to find the optimal filter solution to meet the RTCA DO-160E harmonic specifications for variable grid frequency from 360Hz to 800Hz.

	Prognostic Capability Evaluation of Power Electronic Modules in Transportation Electrification and Vehicle Systems By Alireza ALGHASSI	[View] [Download]
Abstract: Health management and reliability are fundamental part of the design and development cycle of thepower electronic products. This paper presents the study and investigation about the prognostic andhealth management of power electronic IGBT module. To achieve this aim, a fusion approach hasbeen introduced. In addition, for the physic based part of approach, a thermal model is used to predicttemperatures of inaccessible locations within the power module. Then by employing the rainflowalgorithm, the remaining life of the power electronic IGBT module has been determined.

	Real-time Simulation of More-Electric Aircraft Power Systems By Leonardo MONTEALEGRE LOBO, Christian DUFOUR, Jean MAHSEREDJIAN	[View] [Download]
Abstract: The More-Electric Aircraft (MEA) requires thorough testing procedures to meet extreme securityrequirements. Real-time simulation technologies have been traditionally part of this validation andtesting process for conventional aircraft designs. The MEA concept is now pushing HIL technologiestoward aircraft electric system real-time simulation. This paper discusses the real-time simulationrequirements for MEA, analyses an aircraft electrical power system, identifies real-time modelingbottlenecks and validation needs. The case of Bombardier Global Express aircraft is used for thispurpose.

	Research on Methods of Distortion Spectrum Analysis For Aircraft VFAC Power System By Shanshui YANG, Mengdi CAI, Jian ZHAO, Li WANG, Yan LIU	[View] [Download]
Abstract: A lot of power electronic conversion devices are used in the variable frequency AC power system. Harmonic pollution and voltage distortion have serious impact on power quality, and voltage distortion spectrum is an important indicator to measure the electric power quality of aircraft. The distortion spectrum is analyzed for aircraft VFAC power system. The frequency ranged 360 ~ 800Hz brings a wider frequency range distortion spectrum according to MIL-STD-704F. Based on digital filtering technology, the paper proposes a distortion spectrum testing method. The test system can collect synchronous voltage signal by PXI high-speed data acquisition card. The characteristics of digital notch filter are analyzed by simulation, and Butterworth notch filter with four orders is designed for filtering out fundamental component of the distortion voltage. Experimental results show that this test method can extract the fundamental frequency, calculate distortion factor, obtain distortion spectrum. The feasibility and reliability of the test system are verified.

	Suppressing Overvoltage of Carbodies for a Highspeed EMU By Satoru HATSUKADE, Kenji FUJINO, Satoru KANNO	[View] [Download]
Abstract: Overvoltage is created on carbodies of a highspeed electric multiple unit (EMU) when the train raises its pantograph or when its main circuit breaker is switched. This paper outlines the mechanism behind the phenomenon of overvoltage generation on carbodies of the highspeed train, proposing suppressing method, and the results of verification of the method. The results indicate the efficiency of the method, where the overvoltage is reduced by 50\% from the maximum.

	The Characteristics of Aerospace DC arc Fault Current By Zhen MENG, Li WANG, Qiangang SUN	[View] [Download]
Abstract: Arc fault is of great destructiveness and can threaten the safety of electrical system. It is necessary to understand the behaviors and special characteristics of arc fault to develop devices that can detect arc faults. In this paper, the DC arc fault data are obtained via arcing tests according to SAE AS5692 and AS6019. The average value, standard deviation in time domain, spectrum in frequency domain of normal or fault current are analyzed by statistics. The results show the difference between normal and arc fault current. The relationship between the characters of fault current with resistive load in time domain and the supply voltage is also discussed. The study of DC arc fault characteristics lays theoretical foundation for the aircraft DC arc faults detection and protection.