A refined coupled rotor/flexible fuselage aeroelastic response analysis is developed for vibration reduction studies using active control of structural response(ACSR). The model is capable of representing flexible hingeless rotors combined with a flexible fuselage, and a platform for installing the ACSR system. The model is validated by conducting comparisons with previously obtained results for trim, vibratory hub loads and aeroelastic response, for fixed hub conditions. The results indicate that the fixed hub condition is not a reliable model for the estimation of vibratory hub loads; however, the fixed hub model produces reasonable results for the trim vector which is insensitive to both fuselage dynamics and flexibility. The role of non-structural mass for obtaining correct estiamtes for the lower fuselage frequencies is also addressed. The influence of the number of the blades on the vibratory loads is also shown. This paper is a precursor to vibration reduction studies which will be conducted in a sequel.
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