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User Manual / Examples

Published cases.
Solver-visible results.

Choose an example library to explore published material systems, original research, NASA technical reports, and running CDS solver routes without working through one long page.

Traceable by design. Published values are transcribed from the linked primary source. CDS plots are calculated or reconstructed from the stated inputs and are clearly labeled; they are not presented as digitized experimental curves.

M05 Fiber-volume stiffness sweepIllustrated example · not a live run
  1. Materials
  2. Micro
  3. Properties

1 Inputs

01
Ef1 230 GPa
02
Em 3.5 GPa
03
Vf 0.35–0.65
04
longitudinal ROM route

Keep these conditions unchanged when comparing with the answer.

2 Output visualization

E1 · GPa82.835%105.445%128.155%150.765%fiber volume fraction
3 What the result shows

The solver increases E1 from 82.8 to 150.7 GPa across the selected fiber-volume range.

Result basisCDS r15 micromechanics sweep. Values and trends reproduce this page’s example; this is not a fresh solver result or an additional validation claim.
Explore micromechanics inputs and answer →
L01 Quasi-isotropic laminate familyIllustrated example · not a live run
  1. Ply properties
  2. Laminates
  3. Response

1 Inputs

01
QI-8
02
cross-ply
03
±45 angle-ply
04
0/±60 tri-axial
05
0.125 mm plies

Keep these conditions unchanged when comparing with the answer.

2 Output visualization

GPaEx 69.68 GPaGxy 26.88 GPaQI-8Ex 95.99 GPaGxy 7.17 GPacross-plyEx 25.05 GPaGxy 46.59 GPaangle-plyEx 69.68 GPaGxy 26.88 GPatri-axialExGxy
3 What the result shows

QI-8 and 0/±60 return the same Ex = Ey = 69.68 GPa and Gxy = 26.88 GPa.

Result basisPublished layup families · CDS CLT. Values and trends reproduce this page’s example; this is not a fresh solver result or an additional validation claim.
Explore laminates inputs and answer →
A03 First-ply failure screenIllustrated example · not a live run
  1. Laminate
  2. Geometry / cycle
  3. CASES
  4. Response

1 Inputs

01
[0/45/−45/90]s
02
Nx 300 N/mm
03
1.0 mm total thickness

Keep these conditions unchanged when comparing with the answer.

2 Output visualization

FI = 10°0°: failure index 0.2590.259+45°+45°: failure index 0.8040.804−45°−45°: failure index 0.8040.80490°90°: failure index 1.1061.106Tsai–Wu failure index · Nx = 300 N/mm
3 Failure threshold exceeded

The 90° plies reach FI 1.106 first; the example load is above predicted first-ply failure.

Result basisPublished allowables · CDS CLT/Tsai–Wu. Values and trends reproduce this page’s example; this is not a fresh solver result or an additional validation claim.
Explore analyses inputs and answer →

Example subpages

Choose one focused library
0110 cases

Micromechanics

Translate constituent, fiber-form, and published lamina data into solver-ready engineering properties.

Open library 028 cases

Laminates

Turn ply data and stacking sequences into extensional stiffness, equivalent laminate families, and design-level comparisons.

Open library 039 cases

Analyses

Exercise environmental, processing, and failure blocks with traceable material systems and explicit solver assumptions.

Open library 046 files

Starter files

Download runnable solver cases and compact CSV inputs for direct inspection and adaptation.

Open downloads