EPE Association: EPE 2022 - DS3p: Electric Drive Trains for Aerospace and Space Applications

EPE 2022 - DS3p: Electric Drive Trains for Aerospace and Space Applications
You are here: EPE Documents > 01 - EPE & EPE ECCE Conference Proceedings > EPE 2022 ECCE Europe - Conference > EPE 2022 - Topic 08: Electric Vehicle Propulsion Systems and their Energy Storage > EPE 2022 - DS3p: Electric Drive Trains for Aerospace and Space Applications

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   Cascaded H-Bridge Converter Designs for Future Short-Range All-Electric Aircraft Propulsion
By Maximilian HAGEDORN [View]
[Download]

Abstract: The cascaded H-bridge converter topology makes a high voltage power supply structure with distributedenergy storage for all-electric aircraft possible. In this paper, different cascaded H-bridge convertertopologies are compared regarding mass and efficiency, with a focus on the requirements for the energystorage in a battery-powered short-range aircraft.

   Design and Performance Analysis of Single-phase Axial Flux Permanent Magnet Motor for Coaxial Cascade
By Chu WANG [View]
[Download]

Abstract: This paper is about the modeling, design and verification of single-phase axial-flux permanent magnet (AFPM) motor for coaxial cascade. The topology principle with yokeless and segmented armature (YASA) is proposed and discussed. The single-phase AFPM motor is designed and coaxially cascaded for forming a multiphase AFPM motor to compare with three-phase AFPM motor. The comparative results show that the three-phase AFPM motors formed with coaxial has higher power density and fault-tolerant ability.

   Hardware in the Loop Test of an Electric Aircraft Powertrain
By Sebastian MÖNNINGHOFF [View]
[Download]

Abstract: Electric machines are attracting attention as potential alternatives to conventional aircraft powertrains. During the development process of an electric aircraft it is often necessary to test and analyze the entire powertrain or components before all interacting systems are physically available. The function and behavior of subsystems, which interact with the powertrain, have to be emulated at a test bench. The powertrain is subject to varying external conditions during flight, which effect the function of the subsystems. Environmental conditions and the characteristic behavior of the aircraft have to be considered. This paper studies the development of a hardware in the loop test (HIL test), which allows to emulate flight conditions on a test bed during powertrain testing. The HIL test is subsequently implemented and developed for the example of the touring motor glider FVA 30. A duty cycle is derived from an aircraft flight test case and used to simulate the aircraft behavior. The results of the HIL test indicate, that the aircraft will meet the specified flight performance goals, but also hint at high temperatures inside the v-shaped tail section, which requires further study and possibly additional cooling effort.

   Innovative driving scheme for electrical generators in More Electric Aircrafts employing Series Active Filtering
By Nena APOSTOLIDOU [View]
[Download]

Abstract: As more electrification of the future aircrafts becomes a trend, more electric functions, such as theStarter/Generator (S/G) that are incorporated in the More Electric Aircrafts (MEA) concept, increasethe need for electrical power systems with high power supply capabilities, facilitating both motor(starter) and generator operation. Under this light, an innovative driving scheme for electrical generators in MEA that employs series active filtering (SAF) is proposed in this paper, to impose the desired output current in the dc microgrid (DCMG) of the MEA, thus facilitating the multi-operating-point range capability of the machine drive. The proposed SAF-based system that facilitates the incorporation of multiple energy storage units (ESUs) constitutes a robust S/G solution that serves this double-mode operation requirement (set by the specific application), along with the wide set point range necessity of the power generation mode. Moreover, an appropriately developed Design Tool allows for the selection of the optimal SAF parameters, according to the DCMG and the machine drive specifications, facilitating high performance and reliability of the proposed drive unit. The developed S/G driving scheme is verified through MATLAB/Simulink simulations and, additionally, the performance of the power generation control of the system under study is evaluated via real-time control hardware in-the loop (CHIL) tests, with the use of a dedicated microcontroller (dsPIC30f4011) and dSPACE 1202 (MicroLabBox) platform.

   On the Cosmic Ray Influence on the Electronics Design of a High Altitude Electric Aircraft
By Philippe MOREY [View]
[Download]

Abstract: Space in Earth's orbit is growing more and more scares. High altitude solar electric drones, known as High Altitude Pseudo-Satellites (HAPS), are becoming a viable solution to replace satellite functions. One of the issues that must be faced in their design are cosmic rays (CR). CR can cause failures in power electronics and their flux is significantly higher with altitude. Additionally, with lower pressures, arcing and thermal management become issues as well. This study aims to determine the effects of cosmic radiation at stratospheric altitudes and fix guidelines to be able to answer how to design a high-altitude electric aircraft power plant.

   Potentials to Improve the Post-Fault Performance of a Fault-Tolerant Inverter System in Electrified Aircraft Propulsion System
By Yongtao CAO [View]
[Download]

Abstract: Due to the increased exposure to cosmic radiation at higher flight altitude, a significant voltage derating of power semiconductors is required to reduce the failure rate of the inverters designed for electrified aircraft propulsion systems. By utilizing the necessary oversized block-voltage capability of the power semiconductors while employing the concept of variable DC-link voltage, post-fault performance of the inverter system can be improved.

   Short Circuit Behavior of Dual Three-phase Permanent Magnet Synchronous Motors with Different Mutual Inductance in Electric Propulsion Application
By Yinghui YANG [View]
[Download]

Abstract: The dual three-phase permanent magnet synchronous motors (DTP-PMSMs) are suitable in aircraftelectric propulsion unit (EPU) application because of their good reliability and fault-tolerant capability.However, this fault-tolerant capability can get weakened or even eliminated in short circuit fault due tothe influence of flux coupling between the two isolated three-phase sub-systems. In this paper, amathematical model of DTP-PMSMs with different mutual inductance between the two sub-systems aredeveloped and analyzed. Based on the model, different short circuit protection methods are discussedand compared. Finally, a simulation of an EPU consisting of a DTP-PMSM, and a simplified constantspeed propeller (CSP), is implemented to verify the short circuit behaviors.

EPE 2022 - DS3p: Electric Drive Trains for Aerospace and Space Applications
You are here: EPE Documents > 01 - EPE & EPE ECCE Conference Proceedings > EPE 2022 ECCE Europe - Conference > EPE 2022 - Topic 08: Electric Vehicle Propulsion Systems and their Energy Storage > EPE 2022 - DS3p: Electric Drive Trains for Aerospace and Space Applications
	[return to parent folder]

	Cascaded H-Bridge Converter Designs for Future Short-Range All-Electric Aircraft Propulsion By Maximilian HAGEDORN	[View] [Download]
Abstract: The cascaded H-bridge converter topology makes a high voltage power supply structure with distributedenergy storage for all-electric aircraft possible. In this paper, different cascaded H-bridge convertertopologies are compared regarding mass and efficiency, with a focus on the requirements for the energystorage in a battery-powered short-range aircraft.

	Design and Performance Analysis of Single-phase Axial Flux Permanent Magnet Motor for Coaxial Cascade By Chu WANG	[View] [Download]
Abstract: This paper is about the modeling, design and verification of single-phase axial-flux permanent magnet (AFPM) motor for coaxial cascade. The topology principle with yokeless and segmented armature (YASA) is proposed and discussed. The single-phase AFPM motor is designed and coaxially cascaded for forming a multiphase AFPM motor to compare with three-phase AFPM motor. The comparative results show that the three-phase AFPM motors formed with coaxial has higher power density and fault-tolerant ability.

	Hardware in the Loop Test of an Electric Aircraft Powertrain By Sebastian MÖNNINGHOFF	[View] [Download]
Abstract: Electric machines are attracting attention as potential alternatives to conventional aircraft powertrains. During the development process of an electric aircraft it is often necessary to test and analyze the entire powertrain or components before all interacting systems are physically available. The function and behavior of subsystems, which interact with the powertrain, have to be emulated at a test bench. The powertrain is subject to varying external conditions during flight, which effect the function of the subsystems. Environmental conditions and the characteristic behavior of the aircraft have to be considered. This paper studies the development of a hardware in the loop test (HIL test), which allows to emulate flight conditions on a test bed during powertrain testing. The HIL test is subsequently implemented and developed for the example of the touring motor glider FVA 30. A duty cycle is derived from an aircraft flight test case and used to simulate the aircraft behavior. The results of the HIL test indicate, that the aircraft will meet the specified flight performance goals, but also hint at high temperatures inside the v-shaped tail section, which requires further study and possibly additional cooling effort.

	Innovative driving scheme for electrical generators in More Electric Aircrafts employing Series Active Filtering By Nena APOSTOLIDOU	[View] [Download]
Abstract: As more electrification of the future aircrafts becomes a trend, more electric functions, such as theStarter/Generator (S/G) that are incorporated in the More Electric Aircrafts (MEA) concept, increasethe need for electrical power systems with high power supply capabilities, facilitating both motor(starter) and generator operation. Under this light, an innovative driving scheme for electrical generators in MEA that employs series active filtering (SAF) is proposed in this paper, to impose the desired output current in the dc microgrid (DCMG) of the MEA, thus facilitating the multi-operating-point range capability of the machine drive. The proposed SAF-based system that facilitates the incorporation of multiple energy storage units (ESUs) constitutes a robust S/G solution that serves this double-mode operation requirement (set by the specific application), along with the wide set point range necessity of the power generation mode. Moreover, an appropriately developed Design Tool allows for the selection of the optimal SAF parameters, according to the DCMG and the machine drive specifications, facilitating high performance and reliability of the proposed drive unit. The developed S/G driving scheme is verified through MATLAB/Simulink simulations and, additionally, the performance of the power generation control of the system under study is evaluated via real-time control hardware in-the loop (CHIL) tests, with the use of a dedicated microcontroller (dsPIC30f4011) and dSPACE 1202 (MicroLabBox) platform.

	On the Cosmic Ray Influence on the Electronics Design of a High Altitude Electric Aircraft By Philippe MOREY	[View] [Download]
Abstract: Space in Earth's orbit is growing more and more scares. High altitude solar electric drones, known as High Altitude Pseudo-Satellites (HAPS), are becoming a viable solution to replace satellite functions. One of the issues that must be faced in their design are cosmic rays (CR). CR can cause failures in power electronics and their flux is significantly higher with altitude. Additionally, with lower pressures, arcing and thermal management become issues as well. This study aims to determine the effects of cosmic radiation at stratospheric altitudes and fix guidelines to be able to answer how to design a high-altitude electric aircraft power plant.

	Potentials to Improve the Post-Fault Performance of a Fault-Tolerant Inverter System in Electrified Aircraft Propulsion System By Yongtao CAO	[View] [Download]
Abstract: Due to the increased exposure to cosmic radiation at higher flight altitude, a significant voltage derating of power semiconductors is required to reduce the failure rate of the inverters designed for electrified aircraft propulsion systems. By utilizing the necessary oversized block-voltage capability of the power semiconductors while employing the concept of variable DC-link voltage, post-fault performance of the inverter system can be improved.

	Short Circuit Behavior of Dual Three-phase Permanent Magnet Synchronous Motors with Different Mutual Inductance in Electric Propulsion Application By Yinghui YANG	[View] [Download]
Abstract: The dual three-phase permanent magnet synchronous motors (DTP-PMSMs) are suitable in aircraftelectric propulsion unit (EPU) application because of their good reliability and fault-tolerant capability.However, this fault-tolerant capability can get weakened or even eliminated in short circuit fault due tothe influence of flux coupling between the two isolated three-phase sub-systems. In this paper, amathematical model of DTP-PMSMs with different mutual inductance between the two sub-systems aredeveloped and analyzed. Based on the model, different short circuit protection methods are discussedand compared. Finally, a simulation of an EPU consisting of a DTP-PMSM, and a simplified constantspeed propeller (CSP), is implemented to verify the short circuit behaviors.