Étude statique et vibratoire d’une pale d’hélicoptère par le logiciel ANSYS

Abstract

The study of helicopter blade vibrations is essential to ensure flight safety and performance. This thesis aims to analyze the static and vibrational behavior of a helicopter blade with a NACA 0012 airfoil, using the ANSYS APDL software, version 17.2.The static analysis evaluates the mechanical resistance of the blade under aerodynamic lift and drag forces. The modal analysis identifies the natural frequencies and mode shapes of the blade, modeled using two different materials: aluminum 7075-T6 and carbon-epoxy composite. Finally, the harmonic analysis investigates the dynamic response of the blade to a periodic harmonic excitation, both with and without the inclusion of a damping system. The results demonstrate the effectiveness of the damper in reducing the vibrational amplitudes of the helicopter blade.