Impact of Current Density and Cooling on the Weight Balance of Electrical Propulsion Drives for Aviation
Through applying an exemplary design study, the dependencies between current density, temperatures, and weight in an electrical drive system for a small range aircraft with conventional electrical fan or propeller drives are evaluated. This study applies a combined numerical (Finite Element Method F...
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| Format: | Article |
| Language: | English |
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MDPI AG
2020-11-01
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| Series: | Energies |
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| Online Access: | https://www.mdpi.com/1996-1073/13/22/6149 |
| _version_ | 1797547100422012928 |
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| author | Jan Hoffmann Wolf-Rüdiger Canders Markus Henke |
| author_facet | Jan Hoffmann Wolf-Rüdiger Canders Markus Henke |
| author_sort | Jan Hoffmann |
| collection | DOAJ |
| description | Through applying an exemplary design study, the dependencies between current density, temperatures, and weight in an electrical drive system for a small range aircraft with conventional electrical fan or propeller drives are evaluated. This study applies a combined numerical (Finite Element Method FEM) and analytical approach to the machine design, calculation of temperatures, and cooling system design (cooler, pumps, piping). A design scenario was defined using start and climb flight in a warm tropical surrounding as the worst load case. The design has to move between two fixed temperature limits: The maximum allowable temperature in the machine insulation and the ambient temperature. The implemented method facilitates a comparatively fast-medium depth design of the drive system. The derived results show, in fact, a minimum of weight at a certain current density, which is one of the key interests for the designers of the electrical machine. The main influences on this minimum are the temperature drops in the machine, the heat transfer to the cooling fluid, the heat transfer to the cooler wall, and the remaining heat rejection to the ambient. Method and results are transferable to other types of airplanes with different ratings. |
| first_indexed | 2024-03-10T14:38:25Z |
| format | Article |
| id | doaj.art-e99cdc97f0e945d79c3893627b585d79 |
| institution | Directory Open Access Journal |
| issn | 1996-1073 |
| language | English |
| last_indexed | 2024-03-10T14:38:25Z |
| publishDate | 2020-11-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Energies |
| spelling | doaj.art-e99cdc97f0e945d79c3893627b585d792023-11-20T22:01:18ZengMDPI AGEnergies1996-10732020-11-011322614910.3390/en13226149Impact of Current Density and Cooling on the Weight Balance of Electrical Propulsion Drives for AviationJan Hoffmann0Wolf-Rüdiger Canders1Markus Henke2Cluster of Excellence SE²A—Sustainable and Energy-Efficient Aviation, Technische Universität Braunschweig, 38108 Braunschweig, GermanyInstitut für Elektrische Maschinen, Antriebe und Bahnen, Technische Universität Braunschweig, 38106 Braunschweig, GermanyCluster of Excellence SE²A—Sustainable and Energy-Efficient Aviation, Technische Universität Braunschweig, 38108 Braunschweig, GermanyThrough applying an exemplary design study, the dependencies between current density, temperatures, and weight in an electrical drive system for a small range aircraft with conventional electrical fan or propeller drives are evaluated. This study applies a combined numerical (Finite Element Method FEM) and analytical approach to the machine design, calculation of temperatures, and cooling system design (cooler, pumps, piping). A design scenario was defined using start and climb flight in a warm tropical surrounding as the worst load case. The design has to move between two fixed temperature limits: The maximum allowable temperature in the machine insulation and the ambient temperature. The implemented method facilitates a comparatively fast-medium depth design of the drive system. The derived results show, in fact, a minimum of weight at a certain current density, which is one of the key interests for the designers of the electrical machine. The main influences on this minimum are the temperature drops in the machine, the heat transfer to the cooling fluid, the heat transfer to the cooler wall, and the remaining heat rejection to the ambient. Method and results are transferable to other types of airplanes with different ratings.https://www.mdpi.com/1996-1073/13/22/6149electrical aviation driveslightweight machine designhigh current density designdirect slot coolingminimum weightpolysiloxan cooling fluids |
| spellingShingle | Jan Hoffmann Wolf-Rüdiger Canders Markus Henke Impact of Current Density and Cooling on the Weight Balance of Electrical Propulsion Drives for Aviation Energies electrical aviation drives lightweight machine design high current density design direct slot cooling minimum weight polysiloxan cooling fluids |
| title | Impact of Current Density and Cooling on the Weight Balance of Electrical Propulsion Drives for Aviation |
| title_full | Impact of Current Density and Cooling on the Weight Balance of Electrical Propulsion Drives for Aviation |
| title_fullStr | Impact of Current Density and Cooling on the Weight Balance of Electrical Propulsion Drives for Aviation |
| title_full_unstemmed | Impact of Current Density and Cooling on the Weight Balance of Electrical Propulsion Drives for Aviation |
| title_short | Impact of Current Density and Cooling on the Weight Balance of Electrical Propulsion Drives for Aviation |
| title_sort | impact of current density and cooling on the weight balance of electrical propulsion drives for aviation |
| topic | electrical aviation drives lightweight machine design high current density design direct slot cooling minimum weight polysiloxan cooling fluids |
| url | https://www.mdpi.com/1996-1073/13/22/6149 |
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