VIBRATION SUPPRESSION IN HELICOPTER ROTOR/FLEXIBLE FUSELAGE SYSTEM USING THE ACSR APPROACH WITH DISTURBANCE REJECTION

This paper describes two control approaches for vibration reduction in a coupled rotor/flexible fuselage system using the disturbance rejection approach. A concise description of the coupled rotor/flexible fuselage aeroelastic response model is followed by a description of the control algorithms. Numerical results demonstrating effective vibration suppression in the fuselage are presented for both soft-in-plane and stiff-in-plane configurations. The numerical results are all based on the first, or simple control scheme; the second scheme, based on the internal model principle is currently being implemented. Results indicate that substantial vibration reduction is achievable; however, fairly large control forces are needed for vibration reduction.