Demonstration project

Carbon panel FEA & layup study

How we validate a laminate: load cases, stress results and a ply schedule tuned for stiffness and weight.

Industry: [e.g. Drones / UAV]
Services: FEA & layup
Material: Carbon fiber [resin system]
Process: [Prepreg / infusion / wet layup]
Timeline: [e.g. 1 week]

The challenge

Show how a carbon part can be checked for strength and stiffness, and how changing the ply orientation changes the result, before any tooling is made.

[Describe the part, its load cases and the targets it had to meet.]

What we did

Image: model, mesh and boundary conditions

Stage 1

Load cases & model

We defined how the part is supported and loaded, then built the finite element model.

[Load cases and assumptions used.]

Image: stress and deflection results

Stage 2

Stress & deflection results

We identified where stress concentrates and how much the part deflects under each load case.

[Key results.]

Image: ply schedule table

Stage 3

Layup iterations & ply schedule

We compared layups and settled on a ply count and orientation that meets the targets at the lowest weight.

[Final layup, e.g. [0/±45/90]s, and why.]

The result

[Outcome with numbers if you have them, e.g. stiffness gained or weight saved versus the starting layup.]

Image: before / after comparison

Image: report page

Photo: finished part

Your part next?

Have a similar part? Get a free feasibility check.

Send your CAD and get a risk report within 48 hours. No cost, no obligation.

Free Feasibility Check More projects