Bird-Strike Simulation on Composite Blade with metal leading edge cap

I have already completed geometry design in SolidWorks and hex meshing in HyperMesh.
The mesh is available as a valid ANSYS .cdb file (1.8 GB).

OBJECTIVE:-

Perform explicit dynamic bird-strike simulation on a composite blade with metal leading-edge cap and adhesive layer and evaluate structural response.

Tasks to be Performed in ANSYS:-

1) IMPORT MESH

Import HyperMesh .cdb file into ANSYS Workbench using External Model

Link it to Explicit Dynamics analysis system

Verify mesh integrity (hex elements, separate bodies)

2) Material Assignment

Assign materials to individual parts:

Composite blade (CFRP – orthotropic)

Metal leading edge cap (Titanium)

Adhesive layer (EA 9394 Hysol)

Use realistic material properties suitable for impact analysis

3) Bird Modeling (SPH)

Create bird as a cylindrical SPH body

Bird properties:

Mass ≈ 2 kg

Density ≈ 1000 kg/m³

Velocity: 100–200 m/s

Position bird in front of blade leading edge with small gap

4) Contact Definition

Define contact between bird (SPH) and blade

Define bonded / contact interactions between:

Composite–adhesive

Adhesive–metal cap

5) Boundary Conditions

Fix blade root (cantilever condition)

Apply initial velocity to bird only

6) Analysis Settings

Explicit dynamics solver

Suitable time step and total simulation time

Enable large deformation and nonlinear effects

7) Results Extraction

Stress distribution in:

Composite blade

Metal leading edge cap

Adhesive layer

Strain contours

Deformation plots

Contact force / energy absorption (if possible)

*) Deliverables Required

ANSYS Workbench project file

Result plots (stress, strain, deformation)

Short explanation of results and assumptions