Composite Material Layup Simulator — Ply Orientation & Laminate Stiffness Interactive

Interactive 3D composite laboratory: stack four plies, apply tension and read laminate modulus, stress and transverse strain.

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About the Composite Material Layup Simulator

Inspect four separated plies, consolidate them into a symmetric balanced laminate, then apply in-plane tension. Fiber orientation changes laminate extensional stiffness and the transverse strain response.

What the simulator shows

• 3D scene parts: four resin-bound plies; oriented fiber bundles; in-plane tensile grips; material and loading directions; extensional stiffness readout. • Controls: four-ply sequence ([0 / 0 / 0 / 0], [0 / 90 / 90 / 0], [θ / −θ / −θ / θ]), angle-ply θ (0–90 °), fiber volume fraction (0.2–0.7), applied axial strain (0.001–0.005), separate plies for inspection. • Live readouts: lamina longitudinal modulus; lamina transverse estimate; laminate axial modulus; axial laminate stress; transverse strain; load · 20 mm wide × 1 mm thick. • Guided experiments: Unidirectional axial layup; Cross-ply balance; Angle-ply shear compliance. • Four tabs (visual laboratory, curves and measurements, experiments, learn and assess), a model-verification run, a timestamped event log and a trial report.

The model equations

Ef=230 GPa, Em=3 GPa; νf=0.2, νm=0.35 E1=Vf Ef+(1−Vf)Em; 1/E2=Vf/Ef+(1−Vf)/Em G12 uses inverse mixture of constituent shear moduli Transform each plane-stress Q to Q̄, then average equal-thickness plies Ex=Q̄11−Q̄12²/Q̄22; εy=−Q̄12 εx/Q̄22 σx=Ex εx; F=σx×20/1000 kN.

Model limits and how to explore

Linear elastic classical extensional lamination calculation for the listed symmetric balanced sequences, with approximate constituent mixing rules. No strength, damage, delamination, curing, thermal stress or buckling prediction. The 3D strain is magnified; separated plies are an inspection view. Try the preset experiments, then compare the live readouts with the equations.

Frequently asked questions

Is longitudinal rule of mixtures valid at every fiber angle?

No. Off-axis response requires transformed stiffness or compliance.

Does a high modulus guarantee high laminate strength?

No. Failure and damage are not calculated by this elastic model.

What does this simulator not model?

Linear elastic classical extensional lamination calculation for the listed symmetric balanced sequences, with approximate constituent mixing rules. No strength, damage, delamination, curing, thermal stress or buckling prediction. The 3D strain is magnified; separated plies are an inspection view.

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