Application of a numerical procedure for the dynamic analysis of plane aeronautical structures

The main purpose of this paper concerns the applicability of a particular numerical procedure that is an alternative to the finite element method (F.E.M.) for a simplified dynamic analysis of plane aeronautical structures. Cantilever rectangular or trapezoidal plates with constant or variable thickness have been considered in the modelling. These elements are representative of typical aeronautical structural components such as wing or tail surface structures, which might also be formed by two or more parts having the above-mentioned geometry. Since there is the possibility of the occurrence of shear strain, according to Mindlin plate theory, transverse deformability has been taken into account. A study of the coupling phenomenon between the flexural-torsional and shear vibration modes has also been included. (C) 1996 Academic Press Limited