Multidisciplinary Optimization for Weight Saving in a Variable Tapered Span-Morphing Wing Using Composite Materials—Application to the UAS-S4
This paper is a follow-up to earlier work on applying multidisciplinary numerical optimization to develop a morphing variable span of a tapered wing (MVSTW) to reduce its weight by using composite materials. This study creates a numerical environment of multidisciplinary optimization by integrating...
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| Format: | Article |
| Language: | English |
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MDPI AG
2022-04-01
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| Series: | Actuators |
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| Online Access: | https://www.mdpi.com/2076-0825/11/5/121 |
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| author | Mohamed Elelwi Felipe Schiavoni Pinto Ruxandra Mihaela Botez Thien-My Dao |
| author_facet | Mohamed Elelwi Felipe Schiavoni Pinto Ruxandra Mihaela Botez Thien-My Dao |
| author_sort | Mohamed Elelwi |
| collection | DOAJ |
| description | This paper is a follow-up to earlier work on applying multidisciplinary numerical optimization to develop a morphing variable span of a tapered wing (MVSTW) to reduce its weight by using composite materials. This study creates a numerical environment of multidisciplinary optimization by integrating material selection, structural sizing, and topological optimization following aerodynamic optimization results with the aim to assess whether morphing wing optimization is feasible. This sophisticated technology is suggested for developing MVSTWs. As a first step, a problem-specific optimization approach is described for specifying the weight-saving structure of wing components using composite materials. The optimization was performed using several approaches; for example, aerodynamic optimization was performed with CFD and XFLR5 codes, the material selection was conducted using MATLAB code, and sizing and topology optimization was carried out using Altair’s OptiStruct and SolidThinking Inspire solvers. The goal of this research is to achieve the MVSTW’s structural rigidity standards by minimizing wing components’ weight while maximizing stiffness. According to the results of this optimization, the weight of the MVSTW was reduced significantly to 5.5 kg in comparison to the original UAS-S4 wing weight of 6.5kg. The optimization and Finite Element Method results also indicate that the developedmorphing variable span of a tapered wing can complete specified flight missions perfectly and without any mechanical breakdown. |
| first_indexed | 2024-03-10T03:32:44Z |
| format | Article |
| id | doaj.art-de5e710219974bf2a5c043f525c36d21 |
| institution | Directory Open Access Journal |
| issn | 2076-0825 |
| language | English |
| last_indexed | 2024-03-10T03:32:44Z |
| publishDate | 2022-04-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Actuators |
| spelling | doaj.art-de5e710219974bf2a5c043f525c36d212023-11-23T09:37:08ZengMDPI AGActuators2076-08252022-04-0111512110.3390/act11050121Multidisciplinary Optimization for Weight Saving in a Variable Tapered Span-Morphing Wing Using Composite Materials—Application to the UAS-S4Mohamed Elelwi0Felipe Schiavoni Pinto1Ruxandra Mihaela Botez2Thien-My Dao3Laboratory of Active Controls, Avionics and AeroServoElasticity LARCASE, ÉTS—École de Technologie Supérieure, 1100 Rue Notre-Dame Ouest, Montréal, QC H3C 1K3, CanadaLaboratory of Active Controls, Avionics and AeroServoElasticity LARCASE, ÉTS—École de Technologie Supérieure, 1100 Rue Notre-Dame Ouest, Montréal, QC H3C 1K3, CanadaLaboratory of Active Controls, Avionics and AeroServoElasticity LARCASE, ÉTS—École de Technologie Supérieure, 1100 Rue Notre-Dame Ouest, Montréal, QC H3C 1K3, CanadaResearch Team in Machines, Dynamics, Structures and Processes, ÉTS—École de Technologie Supérieure, 1100 Rue Notre-Dame Ouest, Montréal, QC H3C 1K3, CanadaThis paper is a follow-up to earlier work on applying multidisciplinary numerical optimization to develop a morphing variable span of a tapered wing (MVSTW) to reduce its weight by using composite materials. This study creates a numerical environment of multidisciplinary optimization by integrating material selection, structural sizing, and topological optimization following aerodynamic optimization results with the aim to assess whether morphing wing optimization is feasible. This sophisticated technology is suggested for developing MVSTWs. As a first step, a problem-specific optimization approach is described for specifying the weight-saving structure of wing components using composite materials. The optimization was performed using several approaches; for example, aerodynamic optimization was performed with CFD and XFLR5 codes, the material selection was conducted using MATLAB code, and sizing and topology optimization was carried out using Altair’s OptiStruct and SolidThinking Inspire solvers. The goal of this research is to achieve the MVSTW’s structural rigidity standards by minimizing wing components’ weight while maximizing stiffness. According to the results of this optimization, the weight of the MVSTW was reduced significantly to 5.5 kg in comparison to the original UAS-S4 wing weight of 6.5kg. The optimization and Finite Element Method results also indicate that the developedmorphing variable span of a tapered wing can complete specified flight missions perfectly and without any mechanical breakdown.https://www.mdpi.com/2076-0825/11/5/121morphing variable span of a tapered wing (MVSTW)UAS-S4 multidisciplinary numerical optimizationcomposite materialsCFD and XFLR5MATLABaerodynamic optimization |
| spellingShingle | Mohamed Elelwi Felipe Schiavoni Pinto Ruxandra Mihaela Botez Thien-My Dao Multidisciplinary Optimization for Weight Saving in a Variable Tapered Span-Morphing Wing Using Composite Materials—Application to the UAS-S4 Actuators morphing variable span of a tapered wing (MVSTW) UAS-S4 multidisciplinary numerical optimization composite materials CFD and XFLR5 MATLAB aerodynamic optimization |
| title | Multidisciplinary Optimization for Weight Saving in a Variable Tapered Span-Morphing Wing Using Composite Materials—Application to the UAS-S4 |
| title_full | Multidisciplinary Optimization for Weight Saving in a Variable Tapered Span-Morphing Wing Using Composite Materials—Application to the UAS-S4 |
| title_fullStr | Multidisciplinary Optimization for Weight Saving in a Variable Tapered Span-Morphing Wing Using Composite Materials—Application to the UAS-S4 |
| title_full_unstemmed | Multidisciplinary Optimization for Weight Saving in a Variable Tapered Span-Morphing Wing Using Composite Materials—Application to the UAS-S4 |
| title_short | Multidisciplinary Optimization for Weight Saving in a Variable Tapered Span-Morphing Wing Using Composite Materials—Application to the UAS-S4 |
| title_sort | multidisciplinary optimization for weight saving in a variable tapered span morphing wing using composite materials application to the uas s4 |
| topic | morphing variable span of a tapered wing (MVSTW) UAS-S4 multidisciplinary numerical optimization composite materials CFD and XFLR5 MATLAB aerodynamic optimization |
| url | https://www.mdpi.com/2076-0825/11/5/121 |
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