EPE Association: EPE 2011 - DS1a: Topic 19: Electrical Systems in Aerospace, Space

EPE 2011 - DS1a: Topic 19: Electrical Systems in Aerospace, Space
You are here: EPE Documents > 01 - EPE & EPE ECCE Conference Proceedings > EPE 2011 ECCE Europe - Conference > EPE 2011 - Topic 19: Electrical systems in aerospace, space, surface and marine transport (not road) > EPE 2011 - DS1a: Topic 19: Electrical Systems in Aerospace, Space

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   50KW- DC/DC CONVERTERS FOR APPLICATIONS IN HIGHVOLTAGE-DC-NETWORKS FOR MORE ELECTRICAL AIRCRAFTS
By Maik HOHMANN [View]
[Download]

Abstract: No abstract provided.

   A 2.5kV to 22V, 1kW Radar Decoy Power Supply Using Silicon Carbide Semiconductor Devices
By Amit JAIN, David MCINTOSH, Matt JONES, Brian RATLIFF [View]
[Download]

Abstract: A 2.5kVdc to 22Vdc 1kW power supply utilizing 3.2kV silicon carbide (SiC) MOSFETs and Schottky diodes is presented. The power supply provides power to solid-state microwave power amplifiers in an aircraft towed radar decoy. High voltage silicon carbide semiconductors are utilized to switch the high voltage at high frequency without requiring input series connection of devices or converters. A half bridge ZVS topology is utilized in order to eliminate switching loss and minimize noise. Device characteristics, circuit design challenges, packaging, and bench top experimental results are included. Implantation solutions to isolated gate drive and startup from 2.5kV are presented. High voltage SiC MOSFETs and schottky diodes prove to be the enabling technology for high frequency and high power density conversion required in this application.

   A Simple Adaptive Control for a Novel Voltage Bus Conditioner with Reduced Capacitive Storage
By Stefan MOLLOV [View]
[Download]

Abstract: Aircraft nowadays carry various loads imposing a very dynamic load profile on the electricaldistribution bus. The proposed bidirectional converter topology and its controller successfullystabilise the power bus in any combination of distribution impedance and constant –power / pulsedloads. The power topology permits the use of a storage capacitor with lower rating, as all of the storedenergy can be used. A simple adaptive controller was developed, requiring only voltagemeasurements, thus dispensing with expensive sensors. Extensive SABER simulation results arepresented which verify the control principles and demonstrate the practicality of the approach.

   BUCK AC/DC CONVERTER FOR AIRCRAFT APPLICATIONS
By Mohamad TAHA [View]
[Download]

Abstract: There is a general move in the aerospace industry to increase the amount of electrically powered equipments on future aircraft. This trend is referred to as the “More Electric Aircraft”. It assumes using electrical energy instead of hydraulic, pneumatic and mechanical means to power virtually all aircraft subsystem including flight control actuation, environmental control system and utility function. The concept offers advantages of reduced overall aircraft weight, reduced need for ground support equipment and maintenance and increased reliability [1, 2]. Many aircraft power systems are now operating with a variable frequency over a typical range of 360 Hz to 800 Hz. Distribution voltages for an aircraft system can be classified as:Nominal 14, 28 and 42 V dc.Nominal 115/200 V rms and 230/400 V rms ac, both one phase and three phase, over variable frequency range.This paper presents simulation results for a buck 3 phase converter at variable input frequency, which provide a 42 DC power supply for aircraft system. The design of this system poses significant challenges due to the supply frequency variation and requires many features such as:1. The supply current to the converter must have a low harmonic content to minimize its impact on the aircraft variable frequency electrical system.2. A high input power factor must be achieved to minimize reactive power requirements.3. Power density must be maximized for minimum size and weight.

   Design and evaluation of state of the art rectifiers dedicated for a 46 kW E-ECS aerospaceapplication with respect to power density and reliability
By Sebastian LIEBIG, Josef LUTZ [View]
[Download]

Abstract: A major intention of the “More Electric Aircraft” concept (MEA), is the use of power electronics instead of mechanical, hydraulical or pneumatical systems, which promises reduced weight, higher efficiency and less maintenance costs. This paper presents the design of rectifier topologies Active Power Factor Correction (APFC) and Autotransformer Rectifier Unit (ATRU) dedicated for a 46 kW electrical environmental control system (E-ECS) for aerospace application. The derived power-densities reveal, that the active solution offers less weight. However, due to the use of power semiconductors, the lifetime is reduced compared to the passive transformer. To optimize the lifetime, four different switches are evaluated, taking into account losses, junction temperatures, power cycles to failure and cosmic ray susceptibility.

   Experimental Validation of Two-Generator-Concepts for Electric Power Generation in More Electric Aircraft Engine
By Klaus MUEHLBAUER, Dieter GERLING [View]
[Download]

Abstract: No abstract provided.

   Radiation Prediction of Power Electronics Drive System for Electromagnetic Compatibility in Aerospace Applications
By Rodolphe DE MAGLIE, Juergen ENGSTLER, Alfred ENGLER [View]
[Download]

Abstract: This paper deals with the prediction of radiated emission of power electronics drive systems in theenvironmental conditions of aerospace applications. The aerospace norm and constraints define limitsof radiated emissions for such systems. Thus, it is of importance to predict them in the design phase ofthe product development to ensure the electromagnetic compliance of the system. This paper presentsa method to achieve the radiated emissions prediction. First, theoretical considerations highlight thedifferent phenomena responsible of the radiations in typical power electronic system. The modellingprinciple is explained and results are successfully compared with experiments on two test benches.

   Reliability Analysis of DC Power Distribution Network Based on Minimal Cut Sets
By Ling ZHANG, Shanshui YANG, Ling CAI, Li WANG [View]
[Download]

Abstract: This paper introduces a reliability assessment algorithm based on minimal cut sets which is suited to evaluate the reliability of the aircraft and spacecraft power distribution network. According to the raw reliability data of the components of two different DC power distribution networks, the reliability of two distribution networks can be evaluated.

   Stability analysis of motor drive interactions in aircraft electrical systems
By Catherine JONES, Mike BARNES, Andrew FORSYTH [View]
[Download]

Abstract: More Electric Aircraft are currently being developed so that in the future all non-propulsive power on an aircraft can be provided by the electrical system. In this electrical system, it is expected that several motor loads will run in parallel from a single DC bus. The paper will investigate the interactions between five motor loads connected to a common DC bus, paying particular attention to the effects of the line impedance on the stability of the system, and how this interacts with any capacitance in the input filters to the motor drive loads. Based on the results of the tests carried out, guidelines to ensure the stability of a multiple load system are presented.To achieve this, a generic model for a motor load is proposed. Five of these motor loads are then connected to a DC bus and the stability of this system has been tested. The motor parameters have been scaled to represent models of different sizes, and they have different input filters. The impedance of the line has been included.

EPE 2011 - DS1a: Topic 19: Electrical Systems in Aerospace, Space
You are here: EPE Documents > 01 - EPE & EPE ECCE Conference Proceedings > EPE 2011 ECCE Europe - Conference > EPE 2011 - Topic 19: Electrical systems in aerospace, space, surface and marine transport (not road) > EPE 2011 - DS1a: Topic 19: Electrical Systems in Aerospace, Space
	[return to parent folder]

	50KW- DC/DC CONVERTERS FOR APPLICATIONS IN HIGHVOLTAGE-DC-NETWORKS FOR MORE ELECTRICAL AIRCRAFTS By Maik HOHMANN	[View] [Download]
Abstract: No abstract provided.

	A 2.5kV to 22V, 1kW Radar Decoy Power Supply Using Silicon Carbide Semiconductor Devices By Amit JAIN, David MCINTOSH, Matt JONES, Brian RATLIFF	[View] [Download]
Abstract: A 2.5kVdc to 22Vdc 1kW power supply utilizing 3.2kV silicon carbide (SiC) MOSFETs and Schottky diodes is presented. The power supply provides power to solid-state microwave power amplifiers in an aircraft towed radar decoy. High voltage silicon carbide semiconductors are utilized to switch the high voltage at high frequency without requiring input series connection of devices or converters. A half bridge ZVS topology is utilized in order to eliminate switching loss and minimize noise. Device characteristics, circuit design challenges, packaging, and bench top experimental results are included. Implantation solutions to isolated gate drive and startup from 2.5kV are presented. High voltage SiC MOSFETs and schottky diodes prove to be the enabling technology for high frequency and high power density conversion required in this application.

	A Simple Adaptive Control for a Novel Voltage Bus Conditioner with Reduced Capacitive Storage By Stefan MOLLOV	[View] [Download]
Abstract: Aircraft nowadays carry various loads imposing a very dynamic load profile on the electricaldistribution bus. The proposed bidirectional converter topology and its controller successfullystabilise the power bus in any combination of distribution impedance and constant –power / pulsedloads. The power topology permits the use of a storage capacitor with lower rating, as all of the storedenergy can be used. A simple adaptive controller was developed, requiring only voltagemeasurements, thus dispensing with expensive sensors. Extensive SABER simulation results arepresented which verify the control principles and demonstrate the practicality of the approach.

	BUCK AC/DC CONVERTER FOR AIRCRAFT APPLICATIONS By Mohamad TAHA	[View] [Download]
Abstract: There is a general move in the aerospace industry to increase the amount of electrically powered equipments on future aircraft. This trend is referred to as the “More Electric Aircraft”. It assumes using electrical energy instead of hydraulic, pneumatic and mechanical means to power virtually all aircraft subsystem including flight control actuation, environmental control system and utility function. The concept offers advantages of reduced overall aircraft weight, reduced need for ground support equipment and maintenance and increased reliability [1, 2]. Many aircraft power systems are now operating with a variable frequency over a typical range of 360 Hz to 800 Hz. Distribution voltages for an aircraft system can be classified as:Nominal 14, 28 and 42 V dc.Nominal 115/200 V rms and 230/400 V rms ac, both one phase and three phase, over variable frequency range.This paper presents simulation results for a buck 3 phase converter at variable input frequency, which provide a 42 DC power supply for aircraft system. The design of this system poses significant challenges due to the supply frequency variation and requires many features such as:1. The supply current to the converter must have a low harmonic content to minimize its impact on the aircraft variable frequency electrical system.2. A high input power factor must be achieved to minimize reactive power requirements.3. Power density must be maximized for minimum size and weight.

	Design and evaluation of state of the art rectifiers dedicated for a 46 kW E-ECS aerospaceapplication with respect to power density and reliability By Sebastian LIEBIG, Josef LUTZ	[View] [Download]
Abstract: A major intention of the “More Electric Aircraft” concept (MEA), is the use of power electronics instead of mechanical, hydraulical or pneumatical systems, which promises reduced weight, higher efficiency and less maintenance costs. This paper presents the design of rectifier topologies Active Power Factor Correction (APFC) and Autotransformer Rectifier Unit (ATRU) dedicated for a 46 kW electrical environmental control system (E-ECS) for aerospace application. The derived power-densities reveal, that the active solution offers less weight. However, due to the use of power semiconductors, the lifetime is reduced compared to the passive transformer. To optimize the lifetime, four different switches are evaluated, taking into account losses, junction temperatures, power cycles to failure and cosmic ray susceptibility.

	Experimental Validation of Two-Generator-Concepts for Electric Power Generation in More Electric Aircraft Engine By Klaus MUEHLBAUER, Dieter GERLING	[View] [Download]
Abstract: No abstract provided.

	Radiation Prediction of Power Electronics Drive System for Electromagnetic Compatibility in Aerospace Applications By Rodolphe DE MAGLIE, Juergen ENGSTLER, Alfred ENGLER	[View] [Download]
Abstract: This paper deals with the prediction of radiated emission of power electronics drive systems in theenvironmental conditions of aerospace applications. The aerospace norm and constraints define limitsof radiated emissions for such systems. Thus, it is of importance to predict them in the design phase ofthe product development to ensure the electromagnetic compliance of the system. This paper presentsa method to achieve the radiated emissions prediction. First, theoretical considerations highlight thedifferent phenomena responsible of the radiations in typical power electronic system. The modellingprinciple is explained and results are successfully compared with experiments on two test benches.

	Reliability Analysis of DC Power Distribution Network Based on Minimal Cut Sets By Ling ZHANG, Shanshui YANG, Ling CAI, Li WANG	[View] [Download]
Abstract: This paper introduces a reliability assessment algorithm based on minimal cut sets which is suited to evaluate the reliability of the aircraft and spacecraft power distribution network. According to the raw reliability data of the components of two different DC power distribution networks, the reliability of two distribution networks can be evaluated.

	Stability analysis of motor drive interactions in aircraft electrical systems By Catherine JONES, Mike BARNES, Andrew FORSYTH	[View] [Download]
Abstract: More Electric Aircraft are currently being developed so that in the future all non-propulsive power on an aircraft can be provided by the electrical system. In this electrical system, it is expected that several motor loads will run in parallel from a single DC bus. The paper will investigate the interactions between five motor loads connected to a common DC bus, paying particular attention to the effects of the line impedance on the stability of the system, and how this interacts with any capacitance in the input filters to the motor drive loads. Based on the results of the tests carried out, guidelines to ensure the stability of a multiple load system are presented.To achieve this, a generic model for a motor load is proposed. Five of these motor loads are then connected to a DC bus and the stability of this system has been tested. The motor parameters have been scaled to represent models of different sizes, and they have different input filters. The impedance of the line has been included.