Composite Layup Analysis & Failure Prediction
Analyze composite laminates and predict failure modes using Classical Lamination Theory
What You Can Do
You input ply orientations, material properties, and loading conditions, and Claude applies Classical Lamination Theory to calculate effective stiffness matrices, stress/strain distributions across each ply, and evaluate multiple failure criteria simultaneously. This enables you to screen composite layup candidates, optimize stacking sequences, and identify critical failure modes in minutes—without manual hand calculations or expensive FEA preprocessing. You get actionable design feedback, sensitivity analysis, and documentation-ready output for design reports.
Features
Example Output
Example 1: Carbon/Epoxy Tube Layup Analysis
Input: [0/±45/90]s quasi-isotropic laminate, 8 plies, 0.125 mm each, 500 N axial + 100 N·m torque
Output:
Effective Laminate Properties:
- Ex = 58.2 GPa | Ey = 58.1 GPa | νxy = 0.32
- Gxy = 4.1 GPa | Bending stiffness preserved (B matrix ≈ 0)
Critical Ply: 90° plies
- Transverse stress σyy = 42.3 MPa (exceeds matrix strength)
- Max strain criterion: FPF load = 480 N (governs)
- Tsai-Wu failure index: 1.08 (critical)
- Margin of Safety: -7.8% (design change recommended)
Optimization Path: Increase ±45° content to 50% → FPF improves to 612 N
Example 2: Sandwich Panel Face Sheet Screening
Input: Glass/Polyester [0/90/0]s facing (3 plies per side), 75 kPa pressure loading
Output:
Failure Mode: Matrix-dominated transverse cracking at 91 kPa
- Tsai-Wu index at 75 kPa = 0.82 (safe)
- Margin = 21.3%
- Recommendation: Current design acceptable; ply angle sensitivity minimal
What's Included
- SKILL.md instruction file with CLT formulations and failure criterion reference:
- Laminate Input Template (CSV format: ply angle, thickness, material grade):
- Material Property Database (common aerospace composites: AS4/3506, IM7/8552, E-glass/epoxy):
- Failure Criteria Checklists (Maximum Stress, Maximum Strain, Tsai-Wu, Hoffman—when to apply each):
- Design Optimization Workflow (sensitivity analysis template, trade-study matrix for stacking sequences):
Who It's For
- Aerospace structural engineers designing composite wings, fuselages, and control surfaces
- Materials engineers evaluating composite layup performance against airworthiness requirements
- Design engineers screening preliminary concepts before FEA investment
- Stress analysts supporting trade studies and design-for-manufacturability assessments
- Certification engineers documenting laminate properties for type approval packages
Best For
- Preliminary composite layup design and feasibility screening during concept phase
- Multi-candidate stacking sequence ranking before detailed FEA analysis
- Ply-level failure mode prediction and critical load identification
- Laminate property sensitivity analysis (fiber angle, thickness, material variations)
- Troubleshooting unexpected test failures and validating design margins
- Training engineers on laminate mechanics fundamentals and CLT applications
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