Abstract:
A framework for the fully integrated simulation of aeroelastic rotors and fuselages has been developed to capture the entire range of interactional vibratory loads that arise in a rotorcraft. The framework adds fixed-frame fuselage fluid-structure interaction and rotor/fuselage structural coupling capabilities to well-established rotor CFD/CSD methods. The solution methods utilized for the fuselage structural dynamics response are detailed. The effects of compliance on the rotor/fuselage interface are examined for the structural coupling. It is observed that startup transients excite the fuselage structural response and are slow to decay, so an approach to accelerate the convergence of structural dynamics in periodic flight conditions is examined. Identification of the coupled effects on fuselage vibrations are investigated by partially decoupling the framework. Further development of the framework is warranted to extend the coupling options and support alternative solvers.