Abstract

Helicopter rotor blade design is one of the most complex tasks in the aviation industry. During the design, the designer needs to concentrate on the vibration because excessive vibration may lead to affect the performance, design and stability of the helicopter. In this research, carry out the vibration analysis of the helicopter rotor blades in order to determine the vibration-natural frequency with respect to using the different lengths of the blades, based on the number of blades, speeds and different materials. so, this research helps identify the suitable rotor blade for the BELL 403 helicopter. In addition, designers can improve the strength and stability of the rotor blades and it could be helpful for further improvement with dynamic analysis. The rotor blade model is designed by the CATIA V5 design software and ANSYS – Finite Element Analysis (Vibration Analysis) is used to analyse the designed rotor blades.

Keywords: Rotor blades, Vibration- Natural Frequency, ANSYS – Finite Element Analysis.