Sloshing reduced-order models for aeroelastic analyses of innovative aircraft configurations

The present paper introduces the sloshing effects on aeroelastic stability and response of flying wing configurations. Using reduced order model based data provided by computational fluid dynamics data, description slosh is introduced into an integrated modelling that accounts for both rigid elastic behaviour flexible aircraft. fully unsteady aerodynamics, modelled in frequency domain via doublet lattice method, recast time-domain state-space form through rational function approximation. reference aircraft Body Freedom Flutter equipped with a single tank cylindrical geometry, partially filled water, located underneath center mass. results analyses are compared frozen case final aim showing how movement affects complete behaviour.