A computationally efficient methodology to simulate hybrid bolted joints including thermal effects
Carbon-aluminum bolted assemblies are difficult to simulate because of the complex phenomenology involved (contact, friction, preload and thermal expansion). Therefore, accurate but computationally feasible methodologies are necessary. We propose two simplified methodologies, one based on continuum...
| Autores: | , , , |
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| Formato: | artículo |
| Estado: | Versión aceptada para publicación |
| Fecha de publicación: | 2022 |
| País: | España |
| Recursos: | Varias* (Consorci de Biblioteques Universitáries de Catalunya, Centre de Serveis Científics i Acadèmics de Catalunya) |
| Repositorio: | Recercat. Dipósit de la Recerca de Catalunya |
| OAI Identifier: | oai:recercat.cat:10256/26210 |
| Acesso em linha: | http://hdl.handle.net/10256/26210 |
| Access Level: | acceso abierto |
| Palavra-chave: | Materials laminats Mètode dels elements finits Laminated materials Finite element method Cèl·lules (Aeronàutica) Airframes |
| Resumo: | Carbon-aluminum bolted assemblies are difficult to simulate because of the complex phenomenology involved (contact, friction, preload and thermal expansion). Therefore, accurate but computationally feasible methodologies are necessary. We propose two simplified methodologies, one based on continuum shell elements and the other on conventional shells, and compare them with a full 3D solids model. The two cases explored are a single-lap shear coupon with one bolt, and a hybrid wingbox subcomponent with 46 bolts. The effect of temperature jumps on the bolt preloads are explored. Results show that the continuum shell model presents the best tradeoff between accuracy and computational cost |
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