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Project Summary and Motivation
Project Summary and Motivation
The aerospace industry extensively employs tapered configurations as they provide ‘weight-saving’ design by trimming the structure from its rectangular domain. This design is standard in aircraft wing structures (ribs and spars) and helicopter blades.
In the third optimization project, I designed a 3D tapered composite beam using composite sandwich materials in ANSYS DesignModeler. Similar to the wing bracket and drone airframe, I aimed to use the ANSYS optimization module to achieve the minimum beam mass for maximum deformation and equivalent stress.
Project Details and Achievements
Project Details and Achievements
3D Modeling of the Tapered Cantilever Beam- Static Structural Analysis
I performed a static analysis by fixing one end of the beam and applying a vertical load at the free end, obtaining the maximum deformation and equivalent stress as the constraints.
Total Deformation (mm)
Equivalent Stress (MPa)
Conclusion - What Did I Achieve?
Conclusion - What Did I Achieve?
Before Optimization
After Optimization
By conducting a similar mass optimization analysis in ANSYS DOE, I obtained the minimum geometric mass and the corresponding optimum thickness (17% mass reduction) to save manufacturing costs.
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