PSI - Issue 21

ScienceDirect Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2019) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2019) 000 – 000 Available online at www.sciencedirect.com Procedia Structural Integrity 21 (2019) 112–119

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© 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Peer-review under responsibility of the 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials organizers Abstract Among the principal load-carrying parts of an aircraft, the center wing box yields the main mechanical load-carrying area and is composed of many structural components and elements such as upper and lower skin panels, internal rods, ribs, stringers, front and rear spars. For the structural analysis of such real complex systems, simplified representations of the same sections would be used alternatively to determine whether components could withstand loadings without experiencing failure, thus stay in the margin of safety. Nevertheless, these components should contribute to weight efficiency while carrying in-plane loads and distribute out-of plane loads to in-plane members safely. Materials selection plays a crucial role for the determination of such candidate materials along with their material properties in specific structural applications. It is usually performed by considering proper objectives, constraints and free variables with respect to functions of the components of a system. Since Composite Material Handbook (CMH 17), Metallic Materials Properties Development and Standardization (MMPDS), and Preliminary Material Properties Handbook (PMP-HDBK) databases are embedded in the materials selection software (CES Edupack), best candidate materials would be easily identified by using coupling constant(s) such as in multiple-constraints designs. In this study, Ashby’s methodology was applied to determine best candidate materials for constructing skin panels by considering them as bending plates. According to materials selection approach, continuous fiber reinforced epoxy composites was stipulated as one of the best candidate materials. Computational failure analysis was then carried out by referring the proper material properties from the materials selection software. Abstract Among the principal load-carrying parts of an aircraft, the center wing box yields the main mechanical load-carrying area and is composed of many structural components and elements such as upper and lower skin panels, internal rods, ribs, stringers, front and rear spars. For the structural analysis of such real complex systems, simplified representations of the same sections would be used alternatively to determine whether components could withsta d loadings without experiencing failure, thus stay in the m rgin of safety. Nevertheless, these compone ts should contribute to weight efficiency while c rrying in-pl ne loads and distribute out-of pl ne loads to in-plane members safely. Materi ls selection plays a crucial role for the determination of such ca didate materials long with their material properties in specific str ctural applications. It is usually rformed by considering proper objectives, constraints and free variables with respect to functions of the components of a system. Since Composite Material Handbook (CMH 17), Metallic Materials Properties Development and Standardization (MMPDS), and Pr liminary Material Properties Handbook (PMP-HDBK) databases are embedded in the materials selection software (CES Edupack), best candidate materials would b easily identified by using coupling constant(s) such as in multipl -c nstraints designs. In this study, Ashby’s methodology was applied to determine best candidate mat rials for constructing skin panels by considering them as bending pl t s. Acc rding to materials selection approach, continuous fib r reinforced epoxy omposites was stipulated as one of the best candidate mat rials. Computational failure analysis w s then arried out by referring the proper material properties fro t e materials election software. Keywords: Materials selection; structural components; finite element analysis 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials Materials Selection for Aircraft Skin Panels by Integrating Multiple Constraints Design with Computational Evaluations 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials Materials Selecti n f r Aircraft Skin P els by Integrating ultiple Constraints Design with Computational Evaluations Hande Yavuz * Department of Mechanical Engineering, University of Turkish Aeronautical Association, Ankara 06790, Turkey Hande Yavuz * Department of Mechanical Engineering, University of Turkish Aeronautical Association, Ankara 06790, Turkey

Keywords: Materials selection; structural components; finite element analysis

* Corresponding author. Tel.: +90-312-589-6104; fax: +90-312-324-8460. E-mail address: hande.yavuz@centraliens.net

2452-3216 © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Peer-review under responsibility of the 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials organizers 10.1016/j.prostr.2019.12.092 2452-3216 © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/ Peer-review under responsibility of the 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials organizers 2452-3216 © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/ Peer-review under responsibility of the 1st International Workshop on Plasticity, Damage and Fracture of Engineering Materials organizers * Corresponding author. Tel.: +90-312-589-6104; fax: +90-312-324-8460. E-mail address: hande.yavuz@centraliens.net