A COUPLED ROTOR/AIRFRAME VIBRATION MODEL WITH HIGHER HARMONIC CONTROL EFFECTS

A technique to identify the transfer matrix in the higher harmonic control model using a known a priori matrix is presented. The identified matrix is such that it differs the least from the a priori transfer matrix and satisfies the constraints imposed by the measured vibration levels. Application of the technique is demonstrated by using an analytical helicopter model consisting of an assumed mode rotor model and a finite element beam fuselage model. Results of the numerical simulations indicate that the technique could lead to significant reduction in vibrations.