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The aerospace industry deals from the beginning with structures with special requirements as extreme lightweight and withstanding to a big number of load cases. Aerodynamics constraints lead to supplementary restrictions, the results being the complex shape to sustain the fuselage, the rotor blades or the wings skin. This paper presents a static structural analysis of the main rotor blade for the light helicopter. To simulate the mechanical behavior of the blade, a finite elements method was used. A case of hovering flight mode was considered.

STRUCTURAL ANALYSIS OF THE MAIN ROTOR BLADE FOR A LIGHT HELICOPTER - CASE OF HOVERING FLIGHT MODE