| Título: | A tool for local buckling optimization of composite panels using Nastran® SOL 200 |
| Autor: | Guilherme Pedroso Pires Abreu |
| Programa: | Engenharia Aeronáutica e Mecânica |
| Área de Concentração: | Engenharia Aeronáutica |
| Orientador : | José Antônio Hernandes |
| Coorientador : | Saullo Giovani Pereira Castro |
| Ano de Publicação : | 2016 |
| Curso : | Mestrado Profissional |
| Assuntos : | Análise estrutural |
| t | Materiais compósitos |
| t | Flambagem |
| t | Otimização |
| t | Estruturas de aeronaves |
| t | Método de elementos finitos |
| t | Engenharia aeronáutica |
| Resumo : | Current trend of composite materials utilization leads the scientific development to new analysis criteria and methodologies. Also associated to this trend, structural optimization is becoming more "popular" with composite material structures. This work performs a local buckling optimization of wing composite panels with advanced constraints via multidisciplinary optimization solution of NASTRAN® (SOL 200) proposing a new panel buckling calculation criterion for composite materials, a semi-analytical approach alternatively to the buckling eigenvalue solution at finite element solvers. An external FORTRAN® subroutine is called at optimization runs to calculate the buckling eigenvalue for each wing panel. A Python-built model and structure management tool was extended to organize, control and create, automatically, the optimization cards. The buckling optimization was performed under two types of loading, one load case simulating an up-bending condition and another one simulating a down-bending condition. Results present that this methodology has a significant potential of weight reduction in aeronautical structures. |
| Data de Defesa : | 21/03/2016 |
| Texto na íntegra : | [Visualizar] |