COMPOSITE WING OPTIMALIZATION USING FEM ANALYSES SYSTEMS

Abstract

This article describes the creation of a model wing unnamed air vehicle for the optimal design through the design wings that combine 2D orthotropic composite (Skins) and Isotropic Al materials (and all other structures) and compare them with the same wing perform a reorientation of composite layers of orientation in the skin . Optimal design for each wing with a different orientation layers can be obtained by comparing the stresses and displacements . Modeling structure is completed using 3D CAD system. Finite element modeling is completed MSc in Patran using IGS file as geometry , the element type is used to image the 2D shell elements with QUAD4 element topology and the different parts are connected RBE2 (rigid body element) connection . Static analysis performed using NASTRAN engineering . Obtained by the finite element model is analyzed using the aerodynamic (lift) force is used to simulate the load on the wing surface . The optimal design is found tabular stresses and displacements for each layer combinations.