Aeroelastic stability analysis of composite rotor blade

This work presents a coupled motion of a helicopter rotor blade and stability analysis response in the hovering flight condition reinforced by GFRP fiber. The search for increasingly high performances in the field of the helicopters brings to the development of materials having higher rigidities and specific resistances. The use of the composite material blades which are not sensitive to corrosion, offers a good aeroelastic Stability. On the basis of aerodynamic model, the use of the finite element method makes it possible to develop a three dimensional model of the blade and to establish dynamic equations of the movement. Numerical calculations of the model developed with a three dimensional beam type, taking into account the aeroelastic interaction, prove that the composites offer better results compared to ordinary materials.