Stress of an aircraft wing (localization analysis)
- Want to see detailed results of the microstructure of the composite materials
- Currently having trouble because material properties of the composite material is unknown
- Want to analyze the model of composite material easily and with a high degree of accuracy.
The analysis is conducted by replacing the honeycomb sandwich panels that make up the wing section with the homogeneous body.
Macro stress distribution obtained here is one that has averagely evaluated results of the fine structure, so to speak. Furthermore, this analysis evaluates the stress distribution of the inner fine structure by performing the localization analysis for particular elements of the macro model. Localized analysis can also be performed for a macro model that takes into account the large deformation in the non-linear version CMAS.
Use the following licenses:
※This example requires one of the following licenses in addition to the above.