Details
| Originalsprache | Englisch |
|---|---|
| Titel des Sammelwerks | 2023 25th European Conference on Power Electronics and Applications, EPE 2023 ECCE Europe |
| Herausgeber (Verlag) | Institute of Electrical and Electronics Engineers Inc. |
| ISBN (elektronisch) | 9789075815412 |
| Publikationsstatus | Veröffentlicht - 2023 |
| Veranstaltung | 25th European Conference on Power Electronics and Applications, EPE 2023 ECCE Europe - Aalborg, Dänemark Dauer: 4 Sept. 2023 → 8 Sept. 2023 |
Publikationsreihe
| Name | 2023 25th European Conference on Power Electronics and Applications, EPE 2023 ECCE Europe |
|---|
Abstract
To reduce the wear-out effect and minimize the Single Event Burnout effect of the power semiconductor, several hardware design rules for inverters in electric aircraft propulsion systems are posed and implemented in this work. These strategies include scalable chip area and derated DC-link voltage. It is observed in a short-range reference aircraft case study that these rules could result in a conflict of objectives: reducing the risk of wear-out failure while simultaneously minimizing the risk of random failure. Therefore, it is recommended to consider random failures, wear-out failures, and their mutual impacts in a comprehensive analysis of system reliability. A reliability-oriented design rule is proposed in this work.
ASJC Scopus Sachgebiete
- Energie (insg.)
- Energieanlagenbau und Kraftwerkstechnik
- Ingenieurwesen (insg.)
- Elektrotechnik und Elektronik
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2023 25th European Conference on Power Electronics and Applications, EPE 2023 ECCE Europe. Institute of Electrical and Electronics Engineers Inc., 2023. (2023 25th European Conference on Power Electronics and Applications, EPE 2023 ECCE Europe).
Publikation: Beitrag in Buch/Bericht/Sammelwerk/Konferenzband › Aufsatz in Konferenzband › Forschung › Peer-Review
}
TY - GEN
T1 - Inverter design for future electrified aircraft propulsion systems under consideration of wear-out failure and random failure
AU - Cao, Yongtao
AU - Fauth, Leon
AU - Keuter, Ralf Johannes
AU - Sangwongwanich, Ariya
AU - Novak, Mateja
AU - Blaabjerg, Frede
AU - Ponick, Bernd
AU - Mertens, Axel
N1 - Funding Information: We would like to acknowledge the funding by the Deutsche Forschungsgemeinschaft (DFG, German Research Foundation) under Germany’s Excellence Strategy – EXC 2163/1 - Sustainable and Energy-Efficient Aviation – Project-ID 390881007. This work is also supported by the German Federal Ministry of Economic Affairs and Climate Action under the joint research programme LuFo VI-1. The authors are responsible for the content of this publication.
PY - 2023
Y1 - 2023
N2 - To reduce the wear-out effect and minimize the Single Event Burnout effect of the power semiconductor, several hardware design rules for inverters in electric aircraft propulsion systems are posed and implemented in this work. These strategies include scalable chip area and derated DC-link voltage. It is observed in a short-range reference aircraft case study that these rules could result in a conflict of objectives: reducing the risk of wear-out failure while simultaneously minimizing the risk of random failure. Therefore, it is recommended to consider random failures, wear-out failures, and their mutual impacts in a comprehensive analysis of system reliability. A reliability-oriented design rule is proposed in this work.
AB - To reduce the wear-out effect and minimize the Single Event Burnout effect of the power semiconductor, several hardware design rules for inverters in electric aircraft propulsion systems are posed and implemented in this work. These strategies include scalable chip area and derated DC-link voltage. It is observed in a short-range reference aircraft case study that these rules could result in a conflict of objectives: reducing the risk of wear-out failure while simultaneously minimizing the risk of random failure. Therefore, it is recommended to consider random failures, wear-out failures, and their mutual impacts in a comprehensive analysis of system reliability. A reliability-oriented design rule is proposed in this work.
KW - Electrified Aircraft
KW - Inverter design
KW - Lifetime
KW - Reliability
UR - http://www.scopus.com/inward/record.url?scp=85175196786&partnerID=8YFLogxK
U2 - 10.23919/EPE23ECCEEurope58414.2023.10264306
DO - 10.23919/EPE23ECCEEurope58414.2023.10264306
M3 - Conference contribution
AN - SCOPUS:85175196786
T3 - 2023 25th European Conference on Power Electronics and Applications, EPE 2023 ECCE Europe
BT - 2023 25th European Conference on Power Electronics and Applications, EPE 2023 ECCE Europe
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 25th European Conference on Power Electronics and Applications, EPE 2023 ECCE Europe
Y2 - 4 September 2023 through 8 September 2023
ER -