Carga crítica de flambagem de painel de carbono/epóxi para laminados QUAD e Double-Double: influência de parâmetros geométricos, de material e de plataformas comerciais de elementos finitos

Abstract

The use of composite materials in the aerospace industry began in the 1960s. As relatively recent materials, there is still significant potential for research into manufacturing processes and calculation methodologies. The general objective of this study is to evaluate the buckling load of a reinforced panel constructed from carbon fiber reinforced polymer (CFRP) using the finite element method (FEM). The secondary objectives of this study are to develop and validate models using commercial software such as Nastran®, OptStruct®, and Abaqus®, as well as experimental data available in the literature. Additionally, the study aims to identify the main geometric and material parameters influencing the buckling load and to optimize a lay-up proposal for the panel's laminate using the Double-Double laminate theory. It was found that the most influential parameters in the calculation of the critical buckling load were the longitudinal modulus of elasticity (E1) and the ply thickness (t). Moreover, the Double-Double model supported a 66% higher load compared to the QUAD model when laminates with the same number of layers were compared. The study successfully related the influence of the critical buckling load across three solvers, the mechanical and geometric properties of the panel with two laminate lay-up configurations. It was also observed that lighter structures could be designed using the Double-Double configuration.