Coupling Technique of Rotor-Fuselage Dynamic Analysis

Abstract

In this paper is introduced a method of dynamic analysis of the helicopter rotor coupled with fuselage in the rotating plane. The method has been used to determine the inplane rotor-fuselage dynamic properties of a light helicopter with fiberglass-reinforced plastics rotor blades. This paper makes particular reference to the effect of anisotropic dynamic stiffness of the rotor shaft end of fuselage on the natural dynamic characteristics.