Computational analysis of helicopter blade vibrations

In this study, computational dynamic analysis of the blade structure, one of the helicopter rotors components, is performed. The vibrations on the blades cause vibration and adversely affect the structure's material life, flight crew, and helicopter operation. It is vital to reveal the vibration characteristic for vibration-induced tremors to be at the most appropriate level and not cause destruction. Since the structure's material affects the vibration characteristics, the choice of material used in the blade is essential. Within the scope of the study, it aims to understand the aspects of the vibrations that may occur in helicopter blades. The blade structure under consideration is based on the Euler-Bernoulli beam theory. The blade design is done using the Solidworks package program. The finite element model is constructed using the Ansys program. Modal and harmonic vibration analyses are performed for three materials: Titanium alloy, honeycomb, and carbon fiber. The results are discussed comparatively. The suitability of the materials in terms of use is evaluated according to the analysis results. The analyses are assessed, and the appropriate material is selected.