Abstract
A ree ned coupled rotor/e exible fuselage aeroelastic response model is developed for vibration reduction studies based on active control of structural response (ACSR). The structural model is capable of representing e exible, hingeless rotors combined with a e exible fuselage, and a rigid platform combined with the actuators required for modeling the ACSR system and is combined with a free wake model. The ine uence of rotor/fuselage coupling and improved aerodynamics on the vibratory hub loads is investigated.
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