Dear All, there are two channels for you to follow our research.

1. We started a newsletter called Thoughts on Composites Modeling on LinkedIn. Please subscribe to it to get informed about our research and ideas we want to share with the community.

2. We moved our discussion forum to github at wenbinyugroup · Discussions · GitHub as it has more features which can serve you better.

Wenbin

Close

# Prof. Yu's Research Group in the Cloud

Search pages

## Problem Description

The failure index and strength ratio of a honeycomb sandwich plate under the biaxial loading condition are predicted using the MSG plate model. For a plate structural analysis, the loads are usually expressed in terms of plate stress resultants {N11, N22, N12, M11, M22, M12}. In this example, N11=N22=10 N is assumed.

## Solution Procedure

Below describes the step-by-step procedure you followed to solve the problem.

### 1. step 1

• Open Gmsh4SC and create a new model (Change the default name). Click Material->Thermoelastic and input the matrix and fiber properties as shown in Fig. 1 and Fig. 2.

Fig. 1

Fig. 2

* Click Geometry->Common SG-> 3D SG->Honeycomb. Select the materials for core and skim as shown in Fig. 3.

Fig. 3

* Click Mesh->Generate 3D mesh->Generate (Fig. 4.).

Fig. 4

* Click SwiftComp->Homogenization->Plate model. Keep the default parameters and click save and run. The homogenization results will automatically pop up (Fig. 5.).
Fig. 5

### 2. step 2

* Click SwiftComp->Static failure->Input failure constants. Assign failure criterion (max-stress) to the core first (Fig. 6.) and input the failure constants (Fig. 7.). Repeat this step to define the fiber failure constants as shown in Fig. 8 and 9. Note that the lam is non-isotropic material and we will use Tsai-Wu failure criterion in this example.

Fig. 6

Fig. 7

Fig. 8

Fig. 9

* Click Failure index and strength ratio and select stress-based failure criterion. Click add. Select plate model and input and loads as shown in Fig. 10.
Fig. 10

* Click Run. The contour plots of the failure index and strength ratio under this loading condition is given as shown in Fig. 11 and 12.

Fig. 11

Fig. 12