This project deals with the numerical analysis of a composite cantilever beam that represents a section of a helicopter propeller blade. The analysis is carried out using ANSYS software, with the beam modeled using Fiber-Reinforced Polymer materials such as Carbon Fiber-Reinforced Polymer (CFRP) and Glass Fiber-Reinforced Polymer (GFRP). Since helicopter blades are usually pre-twisted to improve their aerodynamic performance, this study considers both the pre-twisted geometry and the anisotropic nature of composite materials. Modal analysis is performed to understand the natural frequencies and vibration modes of the beam.

Torsional vibrations are especially important in rotating blade structures, as they can lead to problems such as flutter, stall-induced vibrations, and structural instability. The interaction between axial forces and torsional motion, known as tension–torsion coupling, is examined to understand effects like blade untwisting and torsional stiffening. These phenomena are important in modern rotor blade design, where passive twist control is achieved through proper material tailoring.

The finite element model includes bending, torsion, shear deformation, and material directionality to accurately capture the dynamic behavior. The results show that pre-twist and material anisotropy significantly influence the vibration response. Overall, this study highlights how composite materials and structural tailoring can be effectively used to improve vibration control and performance in helicopter rotor blades.