Composite Horizontal Tail - Simplified FEA Model

Create a 3D CAD model of a composite aircraft horizontal tail for aerospace structural analysis in ANSYS. Use millimeters. Dimensions: half-span 1494 mm, root chord 480 mm, tip chord 470 mm, root thickness 60 mm, tip thickness 30 mm. Create a tapered trapezoidal tail with a smooth airfoil-like cross-section, not a rectangular block. Include separate upper and lower CFRP skins (2 mm each), front and rear spars (2 mm thick), internal ribs (2 mm thick), and a lightweight foam core. Prepare the skins and spars for an 8-ply symmetric laminate: [0°/+45°/−45°/90°]s, with 0.25 mm per ply. Make the geometry clean, editable, and suitable for finite element analysis. Export as STEP (.stp) if supported. Do not invent material properties or simulation results.

Parameters

Every value above is a live dimension. Open a model like this in the editor and each one becomes a slider you can drag before exporting.