CLT Documentation

Complete reference for the Classical Lamination Theory analysis tool — laminate setup, applied loads, stiffness matrices, failure criteria, and theoretical background.

Results & Outputs

After defining the laminate and loads, all results are computed in real time. The results display shows ply-level detail at three through-thickness locations per ply.

Mid-Plane Strains & Curvatures

The mid-plane strains (ε⁰x, ε⁰y, γ⁰xy) and curvatures (κx, κy, κxy) are the primary unknowns in CLT. They are obtained by inverting the ABD system.

Note: For symmetric laminates ([B] = 0), in-plane loads produce only mid-plane strains and bending moments produce only curvatures. For non-symmetric laminates, the coupling matrix [B] produces coupled behavior.
Ply-Level Strains & Stresses

For each ply, strains and stresses are reported at three through-thickness locations:

  • Top (Outer) — Upper/outer surface of the ply (z = zk-1)
  • Mid — Center of the ply (z = (zk-1 + zk)/2)
  • Bot (Inner) — Lower/inner surface of the ply (z = zk)

Results are presented in two coordinate systems:

  • Laminate (x-y) — Global coordinate strains (εx, εy, γxy) and stresses (σx, σy, τxy)
  • Material (1-2) — Fiber-aligned strains (ε₁, ε₂, γ₁₂) and stresses (σ₁, σ₂, τ₁₂), obtained by rotating through the ply angle θ

Laminate Strain at Depth z

εx(z)εy(z)γxy(z)
=
ε⁰xε⁰yγ⁰xy
+ z ·
κxκyκxy

Laminate Stress (x-y)

σxσyτxy
=
Q̄₁₁Q̄₁₂Q̄₁₆Q̄₁₂Q̄₂₂Q̄₂₆Q̄₁₆Q̄₂₆Q̄₆₆
·
εx(z)εy(z)γxy(z)

Material Stress (1-2)

σ₁σ₂τ₁₂
=
Q₁₁Q₁₂0Q₁₂Q₂₂000Q₆₆
·
ε₁ε₂γ₁₂

Stress Transformation (x-y → 1-2)

σ₁σ₂τ₁₂
=
2mn−2mn−mnmnm²−n²
·
σxσyτxy

Strain Transformation (x-y → 1-2)

ε₁ε₂γ₁₂
=
mn−mn−2mn2mnm²−n²
·
εxεyγxy

where m = cos(θ), n = sin(θ), and θ is the ply angle

Material coordinate values are used for failure evaluation, since composite failure is governed by fiber-direction and transverse-direction mechanisms.

Workbook Export & CSV

The results can be exported in two formats:

  • Workbook View — An interactive tabular display that mirrors the layout of the Composite_Laminates.xlsm spreadsheet for direct comparison.
  • CSV Export — Downloads the full ply-by-ply results as a CSV file for use in external tools or reports.

Shared Laminate Builder

Laminate Properties

Input Allowables Format

Toggle between Strain (με) and Stress (ksi). Values in the stack and limits will convert on-the-fly.

NameET1 (Msi)EC1 (Msi)ET2 (Msi)EC2 (Msi)G12 (Msi)ν12t (in)σ₁t (ksi)σ₁c (ksi)σ₂t (ksi)σ₂c (ksi)σ₁₂s (ksi)r_c Tens (in)r_c Comp (in)K_br TensK_br Comp
Save as Custom Preset

Save the current material properties under a name so you can reuse them without re-entering values.

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