Parametric Study on Cohesive Element for Composite Fuselage Model

Finite element analysis (FEA) modeling on adhesive joint for composite fuselage model

In this paper, a finite element modeling via ABAQUS/Explicit simulation on a novel fabrication miniature composite fuselage structure is presented. The fuselage structure is modeled as a continuum composite layup that consisted of a woven C-glass fiber/epoxy 200 g/m 2 composite laminated [908] with the orthotropic elastic material properties and adhesively bonded butt joint. The adhesively bond...

Topology and Parametric Optimization of a Lattice Composite Fuselage Structure

Conventional commercial aircraft fuselages use all-aluminium semi-monocoque structures where the skin carries the external loads, the internal fuselage pressurization and is strengthen using frames and stringers. Environmental and economic issues force aircraft designers to minimize weight and costs to keep air transport competitive and safe. But as metal designs have reached a high degree of p...

Surrogate Model Based Control Considering Uncertainties for Composite Fuselage Assembly

Numerical Analysis of Delamination Buckling in Composite Cylindrical Shell under Uniform External Pressure: Cohesive Element Method

Nowadays, due to high ratio of strength to weight, composite cylindrical shells are extensively used in a great variety of different industrial applications and under different cases of loads. In this study, the buckling of composite cylindrical shells was examined under uniform external pressure. The buckling analysis of composite cylindrical shells was first done by using theoretical relation...

High Fidelity Failure Analysis for A Composite Fuselage Section

A high fidelity delamination failure analysis was developed by combining a local failure analysis with a global fullscale finite element structural analysis to address strength and delamination failure in a single package. The methodology was demonstrated through a local threedimensional pull-off failure analysis and a geometrically nonlinear structural analysis of a five-foot composite helicop...