Non-Linear Analysis in Post-Buckling Regime of a Tilt Rotor Composite Wing Structure Using Detailed Model and Robust Loading Approach
The design and development of a wing for a completely brand-new aircraft represents, in aeronautics, one of the highest challenges from an engineering point of view. The present work describes a novel methodology devoted to execute numeric simulation in a non-linear post-buckling regime to verify th...
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| Format: | Article |
| Language: | English |
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MDPI AG
2023-12-01
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| Series: | Journal of Composites Science |
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| Online Access: | https://www.mdpi.com/2504-477X/8/1/4 |
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| author | Antonio Chiariello Pasquale Vitale Marika Belardo Francesco Di Caprio Mauro Linari Claudio Pezzella Jacopo Beretta Luigi Di Palma |
| author_facet | Antonio Chiariello Pasquale Vitale Marika Belardo Francesco Di Caprio Mauro Linari Claudio Pezzella Jacopo Beretta Luigi Di Palma |
| author_sort | Antonio Chiariello |
| collection | DOAJ |
| description | The design and development of a wing for a completely brand-new aircraft represents, in aeronautics, one of the highest challenges from an engineering point of view. The present work describes a novel methodology devoted to execute numeric simulation in a non-linear post-buckling regime to verify the composite wing compliance under the design load conditions. The procedure was developed as part of a wing design and research activity and was motivated by the need to have more realistic results, without standard conservatisms like the no-buckling up to ultimate load, to be of use for achieving further weight savings. To carry this out, it was obviously necessary to ensure that the structural integrity was also guaranteed in the post-buckling regime, above the limit load, and therefore in a highly non-linear regime. The present work illustrates a numerical approach based on non-linear finite element analysis which uses the inertia relief option in order to have a more realistic representation of the structural response of the wing in its real context. All that represents a novelty since, at present, the commercial FE codes allow us to use the inertia relief option exclusively for linear analysis. Obviously, the approach can be applied to any other structural component with similar needs. The obtained results show that the differences between linear and non-linear regime are not negligible and, above all, that it is possible to design a wing (or other structural components) considering, at the same time, the large deformation due to the post-buckling regime, the material non-linearities due to the failures and any other non-linearities in order to achieve the challenging weight requirement of the new aircraft generation. |
| first_indexed | 2024-03-08T10:46:41Z |
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| id | doaj.art-dd1feb74500b45d6a6f5f1e684a11045 |
| institution | Directory Open Access Journal |
| issn | 2504-477X |
| language | English |
| last_indexed | 2024-03-08T10:46:41Z |
| publishDate | 2023-12-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Journal of Composites Science |
| spelling | doaj.art-dd1feb74500b45d6a6f5f1e684a110452024-01-26T17:10:39ZengMDPI AGJournal of Composites Science2504-477X2023-12-0181410.3390/jcs8010004Non-Linear Analysis in Post-Buckling Regime of a Tilt Rotor Composite Wing Structure Using Detailed Model and Robust Loading ApproachAntonio Chiariello0Pasquale Vitale1Marika Belardo2Francesco Di Caprio3Mauro Linari4Claudio Pezzella5Jacopo Beretta6Luigi Di Palma7Italian Aerospace Research Centre (CIRA), Via Maiorise, 81043 Capua, CE, ItalyMagnaghi Aeronautica (a MA Group Company), Aeronautical Industry, Via Galileo Ferraris 76, 80146 Napoli, NA, ItalyItalian Aerospace Research Centre (CIRA), Via Maiorise, 81043 Capua, CE, ItalyItalian Aerospace Research Centre (CIRA), Via Maiorise, 81043 Capua, CE, ItalyMSC Software, Hexagon’s Manufacturing Intelligence Division, Corso Italia 44, 00198 Rome, RM, ItalyMare Group, Via ex Aeroporto, s.n.c. c/o Consorzio “Il Sole”, 80038 Pomigliano d’Arco, NA, ItalyIBK-Innovation GmbH, 21129 Hamburg, GermanyMare Group, Via ex Aeroporto, s.n.c. c/o Consorzio “Il Sole”, 80038 Pomigliano d’Arco, NA, ItalyThe design and development of a wing for a completely brand-new aircraft represents, in aeronautics, one of the highest challenges from an engineering point of view. The present work describes a novel methodology devoted to execute numeric simulation in a non-linear post-buckling regime to verify the composite wing compliance under the design load conditions. The procedure was developed as part of a wing design and research activity and was motivated by the need to have more realistic results, without standard conservatisms like the no-buckling up to ultimate load, to be of use for achieving further weight savings. To carry this out, it was obviously necessary to ensure that the structural integrity was also guaranteed in the post-buckling regime, above the limit load, and therefore in a highly non-linear regime. The present work illustrates a numerical approach based on non-linear finite element analysis which uses the inertia relief option in order to have a more realistic representation of the structural response of the wing in its real context. All that represents a novelty since, at present, the commercial FE codes allow us to use the inertia relief option exclusively for linear analysis. Obviously, the approach can be applied to any other structural component with similar needs. The obtained results show that the differences between linear and non-linear regime are not negligible and, above all, that it is possible to design a wing (or other structural components) considering, at the same time, the large deformation due to the post-buckling regime, the material non-linearities due to the failures and any other non-linearities in order to achieve the challenging weight requirement of the new aircraft generation.https://www.mdpi.com/2504-477X/8/1/4post-bucklingcompositetilt-rotorwinginertia reliefDFEM |
| spellingShingle | Antonio Chiariello Pasquale Vitale Marika Belardo Francesco Di Caprio Mauro Linari Claudio Pezzella Jacopo Beretta Luigi Di Palma Non-Linear Analysis in Post-Buckling Regime of a Tilt Rotor Composite Wing Structure Using Detailed Model and Robust Loading Approach Journal of Composites Science post-buckling composite tilt-rotor wing inertia relief DFEM |
| title | Non-Linear Analysis in Post-Buckling Regime of a Tilt Rotor Composite Wing Structure Using Detailed Model and Robust Loading Approach |
| title_full | Non-Linear Analysis in Post-Buckling Regime of a Tilt Rotor Composite Wing Structure Using Detailed Model and Robust Loading Approach |
| title_fullStr | Non-Linear Analysis in Post-Buckling Regime of a Tilt Rotor Composite Wing Structure Using Detailed Model and Robust Loading Approach |
| title_full_unstemmed | Non-Linear Analysis in Post-Buckling Regime of a Tilt Rotor Composite Wing Structure Using Detailed Model and Robust Loading Approach |
| title_short | Non-Linear Analysis in Post-Buckling Regime of a Tilt Rotor Composite Wing Structure Using Detailed Model and Robust Loading Approach |
| title_sort | non linear analysis in post buckling regime of a tilt rotor composite wing structure using detailed model and robust loading approach |
| topic | post-buckling composite tilt-rotor wing inertia relief DFEM |
| url | https://www.mdpi.com/2504-477X/8/1/4 |
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