Abstract

This study introduces an analytical solution method which is called the differential transform method (DTM) to analyze the free vibration response of a beam which features material coupling between flapwise bending and torsional vibrations. The governing differential equations of motion are solved by applying DTM. The mode shapes and the natural frequencies are obtained and plotted for bending and torsional behavior, separately. Application of the model solved by DTM is investigated for a typical cantilever aircraft wing when flexural and torsional motions are coupled and the bending-torsion coupling effect is ignored, separately, using a numeric computing environment, MATLAB.

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