comparative analysis of simulation of composites material with ANSYS.

mechanical engg

A laminated composite material consists of several layers of a composite mixture consisting of matrix and fibers. Each layer may have similar or dissimilar material properties with different fiber orientations under varying stacking sequence. There are many open issues relating to design of these laminated composites. Design engineer must consider several alternatives such as best stacking sequence, optimum fiber angles in each layer as well as number of layers itself based on criteria such as achieving highest natural frequency or largest buckling loads of such structure. Analysis of such composite materials starts with estimation of resultant material properties. In this study, a three layered composite shell consisting of middle layer of High Strength Steel-4340 and outside layers of Aluminium Alloy 7075-76 is designed and analysed for complex aerodynamic loading. The analysis results are found for both elemental & nodal solution. The minimum & maximum elastic strain intensities are 0.172e-04 and 0.00855 respectively for elemental solution while the minimum & maximum values of stress Intensity are 0.140e+07 & 0.594e+09 respectively in case of Nodal Solution, which indicates the variation in the stress intensities in different materials corresponding to their moduli of elasticity. The analysis results directly relate to the stress-strain characteristics of each material and need to be carefully considered keeping in view the variation in stress-strain characteristics of different grades of steel and numerous alloys of Aluminium. The behaviour of each material subject to axial & biaxial tensile as well as compressive loading up to elastic limit is taken into account in the analysis of composites for point loads.

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