Aeroelastic model of rotor was developed using dynamics of flexible multibody systems.The modeling of components of rotor was independent

so different rotor configurations can be modeled and the model was appropriate for new configuration rotor aeroelastic analysis.A large deflection beam model

suitable for aeroelastic analysis of rotor

was incorporated.To simplify the form of constraint equations

dynamic equations of component including a joint were deduced.To avoid singularities for large rotations

the angular constraint equations

expressed by Rodriguez parameters

were modified by introduced a nominal motion.To verify the correctness of the developed method

the aeroelastic analysis of helicopter rotor and influence study of blade structure parameters were implemented.It demonstrates that the method is very useful for improving computation precision of aeroelastic stability.