Coupled helicopter rotor/flexible fuselage aeroelastic model for control of structural response

A refined coupled rotor/flexible fuselage aeroelastic response model is dev eloped for vibration reduction studies based on arrive control of structura l response (ACSR). The structural model is capable of representing flexible , hingeless rotors combined with a flexible fuselage, and a rigid platform combined with the actuators required for modeling the ACSR system and is co mbined with a free wake model. The influence of rotor/fuselage coupling and improved aerodynamics on the vibratory hub loads is investigated.