Computer-aided simulation of unmanned aerial vehicle composite structure dynamics
The dynamic response of an aerial vehicle structure is a key parameter that must be determined before further aeroelastic phenomena can be analysed in the aerospace sector. Natural frequencies, mode shapes, and damping can be measured or predicted through experimental, operational, or computational...
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| Format: | Article |
| Language: | English |
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Vilnius Gediminas Technical University
2024-12-01
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| Series: | Transport |
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| Online Access: | https://jbem.vgtu.lt/index.php/Transport/article/view/23159 |
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| author | Artur Kierzkowski Tomasz Kisiel Maciej Milewski Ádám Török Michał Stosiak Jakub Wróbel |
| author_facet | Artur Kierzkowski Tomasz Kisiel Maciej Milewski Ádám Török Michał Stosiak Jakub Wróbel |
| author_sort | Artur Kierzkowski |
| collection | DOAJ |
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The dynamic response of an aerial vehicle structure is a key parameter that must be determined before further aeroelastic phenomena can be analysed in the aerospace sector. Natural frequencies, mode shapes, and damping can be measured or predicted through experimental, operational, or computational studies. To reduce the costs and complexity of experimental investigations, there is a demand for numerical models that accurately represent the structure′s dynamic behaviour. This article focuses on modelling composite structures, which are increasingly utilised in the aerospace industry and whose dynamic properties are heavily influenced by fibre directionality. ANSYS software and the ACP module were employed to develop a numerical model of a wet Epoxy Carbon UD (230 GPa) composite commonly used in Unmanned Aerial Vehicle (UAV) components. Ten layers of 0.1 mm thick carbon fibre were incorporated into the model to create a 1 mm thick composite plate, with fibres oriented at 0°, 30°, 45°, and 90° relative to the horizontal direction of the plate. The simulations demonstrated that careful consideration and modelling of the material significantly impact the values of natural frequencies and, more importantly, the mode shapes.
First published online 28 January 2025
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| format | Article |
| id | doaj-art-5ed4cf0200304cbea8805dee0c4f658b |
| institution | Kabale University |
| issn | 1648-4142 1648-3480 |
| language | English |
| publishDate | 2024-12-01 |
| publisher | Vilnius Gediminas Technical University |
| record_format | Article |
| series | Transport |
| spelling | doaj-art-5ed4cf0200304cbea8805dee0c4f658b2025-01-28T16:30:20ZengVilnius Gediminas Technical UniversityTransport1648-41421648-34802024-12-0139410.3846/transport.2024.23159Computer-aided simulation of unmanned aerial vehicle composite structure dynamicsArtur Kierzkowski0Tomasz Kisiel1Maciej Milewski2Ádám Török3Michał Stosiak4Jakub Wróbel5Dept of Technical Systems Operation and Maintenance, Faculty of Mechanical Engineering, Wroclaw University of Science and Technology, Poland Dept of Technical Systems Operation and Maintenance, Faculty of Mechanical Engineering, Wroclaw University of Science and Technology, PolandDept of Technical Systems Operation and Maintenance, Faculty of Mechanical Engineering, Wroclaw University of Science and Technology, PolandDept of Transport Technology and Economics, Faculty of Transportation Engineering and Vehicle Engineering, Budapest University of Technology and Economics, HungaryDept of Technical Systems Operation and Maintenance, Faculty of Mechanical Engineering, Wroclaw University of Science and Technology, PolandDept of Technical Systems Operation and Maintenance, Faculty of Mechanical Engineering, Wroclaw University of Science and Technology, Poland The dynamic response of an aerial vehicle structure is a key parameter that must be determined before further aeroelastic phenomena can be analysed in the aerospace sector. Natural frequencies, mode shapes, and damping can be measured or predicted through experimental, operational, or computational studies. To reduce the costs and complexity of experimental investigations, there is a demand for numerical models that accurately represent the structure′s dynamic behaviour. This article focuses on modelling composite structures, which are increasingly utilised in the aerospace industry and whose dynamic properties are heavily influenced by fibre directionality. ANSYS software and the ACP module were employed to develop a numerical model of a wet Epoxy Carbon UD (230 GPa) composite commonly used in Unmanned Aerial Vehicle (UAV) components. Ten layers of 0.1 mm thick carbon fibre were incorporated into the model to create a 1 mm thick composite plate, with fibres oriented at 0°, 30°, 45°, and 90° relative to the horizontal direction of the plate. The simulations demonstrated that careful consideration and modelling of the material significantly impact the values of natural frequencies and, more importantly, the mode shapes. First published online 28 January 2025 https://jbem.vgtu.lt/index.php/Transport/article/view/23159unmanned aerial vehiclemodal analysiscompositefinite element methodvibration |
| spellingShingle | Artur Kierzkowski Tomasz Kisiel Maciej Milewski Ádám Török Michał Stosiak Jakub Wróbel Computer-aided simulation of unmanned aerial vehicle composite structure dynamics Transport unmanned aerial vehicle modal analysis composite finite element method vibration |
| title | Computer-aided simulation of unmanned aerial vehicle composite structure dynamics |
| title_full | Computer-aided simulation of unmanned aerial vehicle composite structure dynamics |
| title_fullStr | Computer-aided simulation of unmanned aerial vehicle composite structure dynamics |
| title_full_unstemmed | Computer-aided simulation of unmanned aerial vehicle composite structure dynamics |
| title_short | Computer-aided simulation of unmanned aerial vehicle composite structure dynamics |
| title_sort | computer aided simulation of unmanned aerial vehicle composite structure dynamics |
| topic | unmanned aerial vehicle modal analysis composite finite element method vibration |
| url | https://jbem.vgtu.lt/index.php/Transport/article/view/23159 |
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