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ANSYS Model Configuration Tool (AMCT)

ANSYS APDL user configurable Finite Element Model (FEM) log file for analyses of Indentation (IND) / Compression after impact (CAI) simulation. Finite element model considers the substitution of the actual honeycomb structure with the solid volume. Hill plasticity was considered for core material properties. MaxStress failure criteria was considered for composite face sheets with progressive damage propagation mechanism. Cohezive zone model with contact separation was considered for adhesive layer material.

Finite element model consists of two load step non-linear analyses. Load step 1 for indentation analysis and Load step 2 for CAI analysis. Interaction between indenter and indentation frame realized by the use of surface-to-surface contact. Interaction between face sheets and core was realized as surface-to-surface contact with opening option (Cohezive zone model).

Based on standard 150 x 100 mm specimen size, standard CAI indentation frame (125 x 75 mm opening) in combination of quasi-static indentation. Model can be accustomed for the user dimensions within reasonable range, where applicable. CAI based on free side CAI setup, with 20 mm resin casting of both loading edges.

All basic input dimensions and quantities are in: mm, N, MPa.
All basic ANSYS output dimensions and quantities are in: m, N, Pa.

Panel dimmensions:
Basic dimensions of panel, indentation / impact frame support width, CAI edge casting depth.

Panel length X (CAI loading direction), mm (100-250 mm):

Panel width Y, mm (50-250 mm):

Panel edge support width for impact, mm (10-25 mm):

Loading edge casting heigth / clamping heigth, mm (10-25 mm):

Panel face sheet composition / properties:
Both composite face sheets with different lay-up can be entered, but with the same material, lamina properties, failure criteria as well as damage degradation degree can be configured.

Panel face sheet composition: Top face sheet lay-up (bottom first, top last, comma separated):

Bottom face sheet lay-up (bottom first, top last, comma separated):

Top face sheet thickness, mm:

Bottom face sheet thickness, mm:

Face sheet material properties: E11 modulus, GPa (70-200 GPa):

E22=E33 modulus, GPa (7-20 GPa):

G12 modulus, GPa (3-15 GPa):

Laminate Failure criteria (Corresponding strength and shear stress), MPa: Tension strength stress 1 direction, MPa:

Compression strength stress 1 direction, MPa:

Tension strength stress 2 direction, MPa:

Compression strength stress 2 direction, MPa:

Tension strength stress 3 direction, MPa:

Compression strength stress 3 direction, MPa:

Shear strength stress 1 direction, MPa:

Shear strength stress 2 direction, MPa:

Shear strength stress 3 direction, MPa:

FC Material Degradation value, % (1-99):

Honeycomb material properties/ dimmensions:
Honeycomb (smeared) properties obtained from flatwise compression test was implemented as bilinear isotropic hardening model with Hill plasticity (with major stiffness multiplication 1.0 along honeycomb height and 0.05 multiplication along in-plane axis).

HC flatwise compression modulus, GPa:

HC crushing stress / buckling strength, MPa:

HC tangential modulus, GPa:

HC thickness / height, mm (10-30 with step 5):

Honeycomb adhesive layer properties/ dimmensions:
Adhesive layer thickness can be input for individual interfaces (Top and Bottom). Adhesive layer material properties obtained from resin coupon tests as well as peel drum test can be input. Adhesive layer material model was implemented as bilinear isotropic hardening model with Cohezive zone model (Critical fracture energy) for contact separation.

Adhesive tension / comp modulus, GPa:

Adhesive yield stress, MPa:

Adhesive tangential modulus, GPa:

Max separation stress (Peeldrum test), Mpa:

G1 VCCM I mode energy, J/m2:

Adhesive layer thickness, TOP (impact face), mm:

Adhesive layer thickness, BOT, mm:

Honeycomb material properties/ dimmensions:
Indentation / Impactor diameter, indentation force, as well as Compression after impact (CAI) end shortening can be input. Residual indentation depth can be analyzed at the end of Load step 1 (Time=1.0), CAI buckling at Load step 2. Results can be extracted by additionally available POST26 script used for load-shortening curve and Failure criteria script for composite damage analyses.

Indentation Sphere diameter, mm (10-150 with step 5):

Indentation force, N:

CAI shortening / displacement loading, mm (0.5-2.0):

Contacts