Plate and beam response
Use the released CLT/FSDT finite-plate or membrane/beam path with compatible dimensions, loads and supports. Buckling, modal and static bending are distinct study choices.
Workflow / 03.5 Design
Evaluate the complete
composite structure.
Choose a compatible released plate, cylinder, beam, section, joint or analytical study. Shared laminate inputs do not make every model combination valid.
Select cases and inspect your model
Inspect the selected model in Live Sim
SIMULATE opens with Live Sim, an input-driven view of the selected cases. The four selectors remain available above the scene. Switch to Blocks to manage candidate records and trace their connections.
- Select Geometry, Laminate, a constituent or a case to inspect the inputs that are actually used. Clicking a used block heading also opens its Live Sim inspection.
- Select a ply in the stack or geometry view to inspect its source. Micro-derived and stored-property plies are identified separately. Woven sources show the fabric unit-cell preview when applicable.
- Select the Thermal or Moisture case to inspect its surface boundary schedule. Move the step slider to compare prescribed conditions. This is not a solved internal temperature or moisture field.
- Use Edit input to open the source record. The scene follows the changed inputs; rerun the simulation before trusting previous results.
Geometry, ply bands and arrows are input illustrations, not a finite-element mesh or solved deformation. Display-only thickness enlargement and any model-specific visualization assumptions are identified in the preview.
Choose the run in the SIMULATION block
SIMULATION is the control point for the run. Select a Thermal case, Moisture case, Mechanical case and EM case, or None in any slot. Each selected case shows its analysis model, laminate and applicable geometry.
- Keep candidate records in the surrounding blocks. Adding a candidate does not select it for execution.
- Select the required cases in SIMULATION and review their inputs before Run. At least one case is required.
- Use the same laminate for a supported combined run. Run standalone studies separately with the other selectors set to None.
- Run executes the selected combination. A connection or Used marker is not evidence of a successful solve.
Selecting several cases does not add unsupported physics coupling. EM screening studies do not automatically heat the thermal case.
Review every downstream geometry dependency
A geometry record can be shared by several cases and simulations. Editing its dimensions or type affects all linked consumers, including studies that are not currently open. Unrelated records are unchanged.
- After editing geometry, open Solver messages and expand Review affected cases and simulations. Select a linked name to inspect that record.
- Check the selected model, load basis, dimensions and boundary conditions. Loads are not automatically replaced when the geometry changes.
- Resolve incompatible geometry and model combinations before running. An I-section does not turn a plate theory into a beam theory.
- Rerun affected simulations before relying on previous results. Inputs changed warnings indicate that stored results no longer match their connected inputs.
Geometry affects only dimensions consumed by the selected model. One-dimensional transport retains its through-thickness assumptions; standalone studies may own their dimensions. Under fixed total edge loads, changing plate width changes force per unit width. Under prescribed resultants, it does not.
Stored ply properties bypass Micro. Mixed stacks keep both paths. Gray blocks are not selected. Geometry, process schedules and other model records are omitted here for clarity; a real run must include all required references.
Fatigue uses intact CLT endpoint stresses and measured S–N calibration. It is evaluated separately from Run and progressive failure. The dashed handoff is not active: optimization still uses current properties until a degradation law is supplied.
Materials → Micro → Laminate.
03.5 / Workflow focus
Connected engineering recordCylinder formulations
Thin-wall membrane and layerwise thick-wall elasticity have different load and process limits. Donnell axial buckling is a separate thin-shell study with an explicit knockdown factor.
Sections and joints
Layerwise sections, lap joints and sandwich bending have their own geometry and interfaces. The analytical Volkersen / Goland–Reissner study is a separate identical-adherend elastic approximation.
Failure and notches
The five existing criteria support eligible CLT first-ply / progressive calculations. LaRC04 linear-shear initiation and calibrated open-hole strength are separate studies, not additional progressive choices.
Fatigue
S–N models predict life from calibrated data. Residual stiffness / strength requires independently fitted retention laws in its separate study; neither automatically changes optimization properties.
Creep, shape and uncertainty
Reference-state studies explore time response, prescribed-eigenstrain free release and bounded ABD sampling. Their scope, inputs and output handoffs are listed below.
Keep evidence connected
Run the selected Simulation after relevant edits. Review model assumptions, stale-result warnings, convergence and calibration before interpreting the result.
Workbench availability: released models, inputs and compatible study paths. The wider theory library includes reference formulations not available in every Workbench solve.
Use this workflow in Workbench: interactive Blocks, record selections and connection controls →
Connected model layer
Design · released model connections
Expand a family for inputs, outputs, supported formulations, theory and an exercise. All model families ↗
∑ Plate · CLT & FSDT
Structural models → Laminate mechanics · CLT / FSDT
InputsLaminate stiffness, finite plate dimensions, supported edges and study choiceResults / handoffFSDT static bending or selected buckling / modal results; not progressive damage
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.
Formulations and study choices
- CLT
- FSDT
- Static bending
- Modal
- Buckling
- Buckling and modal
∑ Cylinder
Structural models → Cylinder models
InputsLaminate, cylinder dimensions and formulation-compatible pressure / axial loadingResults / handoffThin-wall membrane response or layerwise radial fields, with distinct assumptions
Choose one cylinder formulation per case record. Geometry and plies remain shared; thick-wall radial results exclude torsion and process strains.
Formulations and study choices
- Linear thin-wall membrane
- Layerwise thick-wall elasticity
∑ Membrane, bending & beam buckling
Structural models → Laminate mechanics → Membrane, bending & beam
InputsLaminate, compatible section and static or Euler load caseResults / handoffMembrane / bending response or separate Euler buckling result
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.
Formulations and study choices
- Linear static
- Linear static with failure indices
- Beam Euler buckling
∑ Layerwise sections, joints & delamination
Structural models → Layerwise sections & joints
InputsSection or lap geometry, laminate, loads and calibrated interface propertiesResults / handoffx–z fields; coupled ply damage and delamination only for the supported layerwise plate path
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.
Formulations and study choices
- Layerwise x-z plane strain
- Single-lap x-z plane strain
- Coupled delamination growth
∑ Sandwich bending
Structural models → Sandwich bending
InputsFaces, core, dimensions and three-point-bend loadResults / handoffDeflection and separate face, core and nominal bond-shear screening
Dedicated sandwich screening. Check core, faces and nominal bond shear separately; peel, mixed-mode debonding and crack growth are not assessed.
Formulations and study choices
- Sandwich three-point bend
∑ Failure & envelope comparison
Structural models → Laminate mechanics → Failure criteria
InputsEligible CLT load case, strengths / strain limits and selected criterionResults / handoffFirst-ply envelopes or supported progressive ply-damage histories; criteria are not blended
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.
Formulations and study choices
- Maximum stress
- Maximum strain
- Tsai–Hill
- Tsai–Wu
- Hashin
∑ Fatigue S–N
Structural models → Laminate mechanics → Fatigue
InputsIntact ply stresses, cyclic loads and measured S–N calibrationResults / handoffSeparate life assessment; no automatic laminate degradation
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.
Formulations and study choices
- Kim–Zhang
- Sendeckyj
- Weibull S–N
- Kohout–Vechet
- Basquin
∑ D6641 · Compression coupon
Models → Structural models → ASTM · Virtual Test Lab
InputsLinked laminate and explicit specimen, load or measured calibration inputsResults / handoffUniform 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.
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.
Formulations and study choices
- Virtual test · compression coupon
∑ D5379 / D7078 · Shear coupon
Models → Structural models → ASTM · Virtual Test Lab
InputsLinked laminate and explicit specimen, load or measured calibration inputsResults / handoffUniform 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.
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.
Formulations and study choices
- Virtual test · nominal shear coupon
∑ D5528 · DCB opening
Models → Structural models → ASTM · Virtual Test Lab
InputsLinked laminate and explicit specimen, load or measured calibration inputsResults / handoffIdeal 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.
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.
Formulations and study choices
- Virtual test · DCB beam compliance
∑ D7905 · ENF sliding
Models → Structural models → ASTM · Virtual Test Lab
InputsLinked laminate and explicit specimen, load or measured calibration inputsResults / handoffIdeal 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.
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.
Formulations and study choices
- Virtual test · ENF beam compliance
∑ D6671 · Mixed-mode fracture envelope
Models → Structural models → ASTM · Virtual Test Lab
InputsLinked laminate and explicit specimen, load or measured calibration inputsResults / handoffBenzeggagh–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.
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.
Formulations and study choices
- Virtual test · BK mixed-mode envelope
∑ D5229 · Moisture uptake calibration
Models → Structural models → ASTM · Virtual Test Lab
InputsLinked laminate and explicit specimen, load or measured calibration inputsResults / handoffHomogeneous 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.
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.
Formulations and study choices
- Virtual test · Fickian uptake calibration
∑ D5961 · Bearing / bypass screening
Models → Structural models → ASTM · Virtual Test Lab
InputsLinked laminate and explicit specimen, load or measured calibration inputsResults / handoffSingle-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.
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.
Formulations and study choices
- Virtual test · bearing bypass screening
∑ D6484 · Open-hole compression
Models → Structural models → ASTM · Virtual Test Lab
InputsLinked laminate and explicit specimen, load or measured calibration inputsResults / handoffNominal 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.
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.
Formulations and study choices
- Virtual test · measured open-hole compression
∑ D6742 · Filled-hole comparison
Models → Structural models → ASTM · Virtual Test Lab
InputsLinked laminate and explicit specimen, load or measured calibration inputsResults / handoffCompares 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.
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.
Formulations and study choices
- Virtual test · measured filled-hole comparison
∑ D7136 / D7137 · Impact & CAI assessment
Models → Structural models → ASTM · Virtual Test Lab
InputsLinked laminate and explicit specimen, load or measured calibration inputsResults / handoffIncident 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.
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.
Formulations and study choices
- Virtual test · measured impact and CAI
∑ Open-hole strength
Structural models → Laminate mechanics → Failure criteria → Open-hole strength
InputsSpecially orthotropic laminate, hole radius, unnotched strength and calibrated distancesResults / handoffPoint / average stress strength screening and radial stress profile
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.
Formulations and study choices
- Whitney–Nuismer open-hole tension
∑ Creep & stress relaxation
Structural models → Laminate mechanics → Creep & stress relaxation
InputsLaminate Ex, Prony fractions / times and held stress or strain at calibration temperatureResults / handoffSeparate axial creep and relaxation curves with time-refinement safeguards
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.
Formulations and study choices
- Generalized Maxwell · axial Prony
∑ Analytical bonded joint
Structural models → Layerwise sections & joints → Analytical bonded joint
InputsIdentical equivalent-elastic adherends, adhesive, overlap, width and tensile forceResults / handoffVolkersen shear and Goland–Reissner shear / peel; no debond growth
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.
Formulations and study choices
- Volkersen & Goland–Reissner joint
∑ LaRC04 failure initiation
Structural models → Laminate mechanics → Failure criteria → LaRC04
InputsLaminate, membrane / bending resultants and calibrated effective ply strengthsResults / handoffLinear-shear LaRC04 initiation indices at ply faces; no progressive degradation
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.
Formulations and study choices
- LaRC04 · linear shear
∑ Tool-release shape
Structural models → Tool-release shape
InputsLaminate and prescribed temperatures, CTE and effective post-gel shrinkageResults / handoffFree-release CLT curvature and separate corner spring-in estimate; not an automatic process-history handoff
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.
Formulations and study choices
- Free-release eigenstrain & spring-in
∑ Fatigue residual properties
Structural models → Laminate mechanics → Fatigue → Residual properties
InputsModulus, independently fitted stiffness / strength retention laws, life and elapsed cyclesResults / handoffResidual-property curves for the specified constant-amplitude calibration; saved laminate is unchanged
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.
Formulations and study choices
- Calibrated residual-property fatigue
∑ Cylinder buckling
Structural models → Cylinder models → Cylinder buckling
InputsThin specially orthotropic shell, radius, length, axial compression and prescribed knockdownResults / handoffIdeal / knocked-down Donnell axial buckling and governing mode; no pressure or postbuckling
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.
Formulations and study choices
- Donnell cylinder · axial buckling
∑ Uncertainty & sensitivity
Structural models → Uncertainty & sensitivity
InputsLaminate, bounded modulus / thickness / angle variations, seed and axial loadResults / handoffABD axial-strain percentiles and signed correlations; not certified reliability
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.
Formulations and study choices
- Seeded laminate uncertainty
∑ Normal-incidence laminate TMM
Models → Electromagnetics · RF → Normal-incidence laminate TMM
InputsExplicit dielectric A/B layers, thicknesses, repetition, frequency and supported polarizationResults / handoffReflection, transmission, absorption and shielding spectra; no mechanical coupling
Coherent isotropic nonmagnetic layers between air half-spaces.
Formulations and study choices
- EM · Normal-incidence laminate TMM
∑ Oblique polarized laminate TMM
Models → Electromagnetics · RF → Oblique polarized laminate TMM
InputsExplicit dielectric A/B layers, thicknesses, repetition, frequency and supported polarizationResults / handoffReflection, transmission, absorption and shielding spectra; no mechanical coupling
TE or TM waves; scalar isotropic layers, no polarization conversion.
Formulations and study choices
- EM · Oblique polarized laminate TMM
∑ 1D transmission line matrix
Models → Electromagnetics · RF → 1D transmission line matrix
InputsExplicit dielectric A/B layers, thicknesses, repetition, frequency and supported polarizationResults / handoffReflected and transmitted pulse histories and spectra; mesh and energy checks
Normal-incidence lossless delay-line mesh with pulse decay, energy and mesh-refinement safeguards. Explicit Run required; not a 3D solver.
Formulations and study choices
- EM · 1D transmission line matrix
∑ 1D Floquet–Bloch periodic layers
Models → Electromagnetics · RF → 1D Floquet–Bloch periodic layers
InputsExplicit dielectric A/B layers, thicknesses, repetition, frequency and supported polarizationResults / handoffPeriodic-cell eigenvalues, folded Bloch phase and stop-band decay
Lossless isotropic A/B unit-cell eigenvalues, folded Bloch phase and stop-band attenuation at normal incidence. Not arbitrary-cell homogenization.
Formulations and study choices
- EM · 1D Floquet–Bloch periodic layers