Analysis of Aircraft Fittings
Fittings for aircraft panels are described.
![](../../../images/solvers/aerospace_analysis_aircraft_dfem_model.png)
Figure 1. DFEM Model
The above fitting is analyzed for tensile and compressive loads, in two different load steps.
![](../../../images/solvers/aerospace_airframe_loads_and_bc.png)
Figure 2. Details of Loads and Boundary Conditions
The analysis is performed with different analysis types.
Linear Static Analysis
![](../../../images/solvers/aerospace_analysis_aircraft_dfem_model_results.png)
Figure 3. DFEM Model Results from Linear Static Analysis
Nonlinear Analysis with Pre-loaded Fasteners
![](../../../images/solvers/aerospace_analysis_aircraft_results_before_after_external_load.png)
Figure 4. DFEM Model Results from Nonlinear Static Analysis. (a) before applying an external load; (b) after the application of external load
Large Displacement Nonlinear Analysis with Pre-loaded Fasteners
![](../../../images/solvers/aerospace_analysis_aircraft_results_nonlinear_disp_static.png)
Figure 5. DFEM Model Results from Nonlinear Large Displacement Static Analysis
Model Files
Refer to Access the Model Files to download the required model file(s).
- Linear_static_fittings.fem
- LGDISP_preloaded.fem