Determination of the flutter instability boundary of a composite wing using Support Vector Machine

The main goal of this article is to train a support vector machine in order to determin the boundary of the composite wing aeroelastic instability. Aircraft wing is modeled as a cantilever beam with two degrees of freedom with thrust as a follower force and mass of the engine. For structural modeling of composite wing the layer theory has been used and in the aerodynamic model, the flow has been assumed to be unsteady, subsonic and incompressible. Using the assumed mode method, the wing dynamic equations of the motion have been derived by Lagrange equations. Linear flutter speed according to the eigenvalues of the motion equations has been calculated. The process of flutter speed calculation has been converted to a computer code in which the number of layers, angle of fibers in each layer, the mass of the engine, and the thrust are input variables and the flutter speed is its output. Determination of the instability boundary using this conventional method is time consuming. In this article, a support vector machine has been adopted to reduce the calculation cost. The results indicate that support vector machine can be used in determining the boundary of the wings flutter instability as an accurate and fast tool.