Structural Analysis of a Carbon Fiber Composite Propeller
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DOI:
https://doi.org/10.5281/zenodo.14897891Keywords:
Carbon Fiber Materials, FEA Analysis, Aerospace Components, Structural Analysis, Mechanical PropertiesAbstract
This study explores the topology optimization of a propeller component using the finite
element method in ANSYS, with the objective of minimizing material usage while maintaining structural
integrity. Carbon fiber, modeled as an orthotropic material, was selected due to its superior mechanical
properties, including a Young’s modulus of 230 GPa in the primary loading direction. A structured
optimization approach was employed. The optimization process, constrained to 500 iterations, resulted in
a mass reduction of 11.86%, decreasing from 0.016404 kg to 0.014459 kg, and a volume reduction from
9113.2 mm³ to 8032.6 mm³, retaining 88.143% of the original volume. Structural analysis revealed that
most regions experienced von Mises stress values below 20 GPa, with maximum stress levels exceeding
43 GPa, particularly near fixation points, contrary to expected stress distributions. These findings align
with literature data emphasizing the critical role of material selection and microstructural characteristics
in determining composite performance. The results validate the effectiveness of topology optimization in
reducing component weight while preserving mechanical performance. This study highlights the potential
application of carbon fiber reinforced composites in weight sensitive engineering fields, such as
aerospace and automotive industries, where the balance between weight reduction and load bearing
capacity is critical. Future work may focus on refining stress distribution patterns and further enhancing
the optimization algorithm to achieve even greater material efficiency.
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