Connect laminate behavior to
structural performance.

Structural models → Laminate mechanics · CLT / FSDT

Choose a formulation and study. Buckling and modal can be requested together; static bending requires FSDT. These are reference-elastic studies, separate from coupled process or progressive failure.

Structural models → Cylinder models

Choose one cylinder formulation per case record. Geometry and plies remain shared; thick-wall radial results exclude torsion and process strains.

Structural models → Laminate mechanics → Membrane, bending & beam

Geometry and the case determine the membrane or beam-test interpretation. Euler buckling requires a compatible beam section and a separate reference-elastic study; it is not a strength or local-buckling pass.

Structural models → Layerwise sections & joints

Coupled delamination is available only for the layerwise Plate section and needs calibrated interface and ply properties. Lap-shear uses its separate joint geometry and perfectly bonded elastic formulation.

Structural models → Sandwich bending

Dedicated sandwich screening. Check core, faces and nominal bond shear separately; peel, mixed-mode debonding and crack growth are not assessed.

Structural models → Laminate mechanics → Failure criteria

One primary failure criterion per load. In Response → Failure, compare all eligible theories or a custom selection in the envelope controls. Each theory runs independently; criteria are not blended.

Structural models → Laminate mechanics → Fatigue

Select calibrated S–N curves for each material, direction and stress sign in Fatigue. Different sources can use different models. S–N life does not define residual stiffness or strength.

Models → Structural models → ASTM · Virtual Test Lab

Uniform small-strain compression using linked laminate Ex and thickness. Measured compressive strength supplies a screening ratio; fixture, tabs, buckling and failure evolution are not simulated.

Models → Structural models → ASTM · Virtual Test Lab

Uniform nominal shear between notches using linked laminate Gxy and thickness. Not a notch/fixture stress field or nonlinear shear solution. Gauge length is the effective shear deformation length, not crosshead travel.

Models → Structural models → ASTM · Virtual Test Lab

Ideal Euler–Bernoulli DCB with equal homogeneous 0° arms, each half the linked laminate thickness. No root rotation, shear, large displacement or cohesive growth. Critical load is an initiation estimate from supplied GIc.

Models → Structural models → ASTM · Virtual Test Lab

Ideal equal-arm, homogeneous 0° ENF beam; support span is twice the half-span. Crack must be shorter than the half-span. No shear/root correction or unstable crack growth. GIIc is supplied, not fitted automatically.

Models → Structural models → ASTM · Virtual Test Lab

Benzeggagh–Kenane envelope from calibrated GIc, GIIc and exponent. Supplied GI/GII are energy-release rates from a separate test reduction or analysis. This does not resolve the MMB lever fixture or propagate a crack.

Models → Structural models → ASTM · Virtual Test Lab

Homogeneous slab, initially dry, both faces held at equilibrium moisture. Fits diffusivity from two early uptake measurements (both ≤50% saturation) using the square-root-time approximation. Edge ingress and temperature dependence are excluded. Does not overwrite material properties.

Models → Structural models → ASTM · Virtual Test Lab

Single-pin nominal bearing, net-section and shear-out checks with independent measured allowables. Bypass tension is added to net-section load only. No contact, bolt preload, load redistribution or validated bearing–bypass interaction envelope.

Models → Structural models → ASTM · Virtual Test Lab

Nominal gross/net stress and demand relative to measured open-hole compressive strength for this geometry and layup. This is test-data screening, not an uncalibrated notch-strength prediction. No local buckling or kink-band simulation.

Models → Structural models → ASTM · Virtual Test Lab

Compares user-measured open- and filled-hole compressive strengths using gross-section stress. Use matched layup, hole, environment and fastener condition. Filling a hole does not automatically recover strength; no fastener contact/preload model is applied.

Models → Structural models → ASTM · Virtual Test Lab

Incident energy from measured impact velocity; residual compressive strength from measured peak CAI force. Rebound energy estimates energy not returned to the striker, NOT damage energy. No impact/contact solver, damage-area prediction or energy-to-strength extrapolation.

Structural models → Laminate mechanics → Failure criteria → Open-hole strength

Infinite-width, specially orthotropic tension screening. Point and average stress distances must be calibrated independently for this laminate. Not compression, bearing or a joint allowable.

Structural models → Laminate mechanics → Creep & stress relaxation

Linear uniaxial response at the calibration temperature. Reference Ex is the instantaneous modulus. Three Maxwell branches; creep is solved from stress equilibrium, not the reciprocal relaxation modulus. No thermal shifting or nonlinear creep.

Structural models → Layerwise sections & joints → Analytical bonded joint

Identical equivalent-elastic adherends, long free arms and a thin elastic adhesive. Compare shear-only Volkersen with eccentric single-lap shear and peel. Not a debonding, plasticity or strength calculation.

Structural models → Laminate mechanics → Failure criteria → LaRC04

NASA LaRC04 linear-shear specialization, evaluated at both faces of every ply under membrane and bending loads. Supplied ply strengths are effective/in-situ values; no automatic thin-ply enhancement. Initiation only, not degradation or nonlinear-shear instability.

Structural models → Tool-release shape

Free CLT release from prescribed ply-local shrinkage/thermal eigenstrains. Corner spring-in is a separate uniform-strain estimate. Stress-free temperature and effective post-gel shrinkage need calibration. No tool friction, cure kinetics or viscoelastic restraint history.

Structural models → Laminate mechanics → Fatigue → Residual properties

Prescribed power-law retention fitted to constant-amplitude tests at a fixed stress ratio, amplitude and temperature. Stiffness and strength have independent coefficients. S–N life alone cannot calibrate either. Does not modify the saved laminate.

Structural models → Cylinder models → Cylinder buckling

Simply supported, thin, specially orthotropic cylinder under uniform axial compression. Discrete Donnell modes; prescribed knockdown factor explores imperfection sensitivity, not a prediction from measured imperfection amplitude. No pressure, torsion, postbuckling or strength pass.

Structural models → Uncertainty & sensitivity

Seeded independent uniform sampling of shared modulus, ply-thickness and angle offsets. Recomputes laminate ABD for each sample. Bounds are assumptions, not measured distributions. Percentiles and sensitivity are exploratory, not reliability certification.

Models → Electromagnetics · RF → Normal-incidence laminate TMM

Coherent isotropic nonmagnetic layers between air half-spaces.

Models → Electromagnetics · RF → Oblique polarized laminate TMM

TE or TM waves; scalar isotropic layers, no polarization conversion.

Models → Electromagnetics · RF → 1D transmission line matrix

Normal-incidence lossless delay-line mesh with pulse decay, energy and mesh-refinement safeguards. Explicit Run required; not a 3D solver.

Models → Electromagnetics · RF → 1D Floquet–Bloch periodic layers

Lossless isotropic A/B unit-cell eigenvalues, folded Bloch phase and stop-band attenuation at normal incidence. Not arbitrary-cell homogenization.