Equivalent Continuum Beam-Rod Models of Aircraft Wing Structures for Aeroelastic Analysis

초록

The equivalent continuum beam-rod models of aircraft wing structures with composite laminated skins have been developed based on the concept of energy equivalence. The equivalent structural properties of a continuum beam-rod model are obtained f개m the direct comparison of the reduced stiffness and mass matrices for a typical segment of aircraft wing with those for a finite-element of continuum beam-rod model. The finite element stiffness and mass matrices from well-known finite-element formulation are used in calculating the reduced matrices for the aircraft wing structure. The finite-element matrices are condensed to obtain the reduced stiffness and mass matrices in terms of continuum degrees of freedom introduced in this paper. The present method of continuum modeling yields every equivalent structural properties including all possible coupling between bending, torsional, and transverse shear deformations. To evaluate the equivalent continuum beam-rod model developed herein, free vibration and aeroelastic analyses are conducted. The numerical results from a continuum beam-rod model are compared with results from different models of a box-beam typed aircraft wing structure.