Finite Element Analysis for Composite Laminates

About the project

ANSYS Composite Laminate FEA – Limited-Budget Research Assistance I am looking for an ANSYS specialist or postgraduate researcher experienced in composite materials to perform a comparative finite element analysis of two carbon/epoxy composite laminates. Laminate specifications Plate dimensions: 200 mm × 100 mm Material: Carbon/Epoxy Number of plies: 8 Individual ply thickness: 0.2 mm Total thickness: 1.6 mm Density: 1600 kg/m³ Laminate A: [0/30/60/90]s Laminate B: [0/45/−45/90]s Material properties Longitudinal Young's modulus, E1 = 230 GPa Transverse Young's modulus, E2 = 23 GPa In-plane shear modulus, G12 = 9 GPa Through-thickness shear modulus, G23 = 8 GPa Major Poisson's ratio, ν12 = 0.2 Please identify any additional material properties needed for the selected analysis. Boundary conditions and loading Simply supported boundary conditions along all four edges. Uniform transverse pressure of 1 MPa applied over the plate. Identical loading and support conditions for both laminates. Required outputs Total deformation contour plot, in mm. Equivalent elastic strain contour plot, in mm/mm. Tsai–Wu failure index for each ply, subject to availability of the required strength properties. Ply-level stresses, including σ1, σ2, and τ12 in the local material coordinate system. Comparative discussion of the structural response of both laminates. Basic mesh convergence and verification of the model. Deliverables Editable ANSYS Workbench project files. Composite layup and material definition. Contour plots and numerical result summaries. Concise technical report describing methodology, assumptions, and results. This is a limited-budget research assistance project. Please provide a fixed-price quotation for both laminates together and identify any additional costs before starting. Applicants should have practical experience with ANSYS composite layups and orthotropic material modeling.

Skills required