- A stiffened panel is to be analysed regarding its structural strength and stability by means of an existing FE model. The panel is a skin segment of an aircraft wing between two spars and two ribs, which is stiffened by T-shaped stringers, as illustrated in Figure 1.
- All detailed dimensions, properties and boundary conditions can be obtained from within the FE model.
- Three representative load cases are considered. The internal section loads applied on the model boundaries are modelled as a combination of a longitudinal, transverse and shear load fraction, as seen in Figure 2. These fractions are scaled in each load case.
In this repo, there exist two python files, namely Task1 and Task2. Each script is used for differnet task although they're nearly the same.
- Hypermesh Model
- Getting info about 2D Stress Element in mid plane for each load case in:
- XX Stresses in X direction
- YY Stresses in Y direction
- XY Shear Stresses
- Von-Misses Stresses
- All data are in .txt format and they're then put in their respective directory
- The output will be a text file called LC{x}_Final, where x is the load case you're working on