Flutter Analysis of a 3D Box-Wing Aircraft Configuration

The aim of this paper is to present a flutter analysis 3D Box-Wing Aircraft (BWA) configuration. box wing structure considered as consisting two wings (front and rear wings) connected with winglet. Plunge pitch motions are for each the winglet modeled by longitudinal spring. In order exert effect wing-joint interactions (bending torsion coupling), ends spring located on gravity centers tip sections. Wagner unsteady model used simulate aerodynamic force moment wing. governing equations extracted via Hamilton’s variational principle. To transform resulting partial integro-differential into set ordinary differential equations, assumed modes method utilized. confirm model, results clean compared validated previously published results. Also, validation, aircraft configuration MSC NASTRAN software good agreement observed. effects design parameters such tension stiffness, sweep dihedral angles, altitude velocity frequency investigated. reveal that physical geometrical properties front also have significant influence BWA aeroelastic stability boundary.