The role of conformation and the effect of position of the substituent on the activity of copper(II) derivative of meso-5,10,15-tris(4- or 5- bromothien-2-yl)-20-(4-((thiophen-2-ylimino)methyl)benzoic acid)porphyrin (CuXB5TP, X = 4 or 5) as photosensitisers have been investigated. The predicted result using intelligent techniques shows good agreement with experimental data. These techniques give an accurate prediction of thickness strain which is helpful for prediction of failures in the punch-corner region and wall region at any unknown punch diameter and temperature. In this paper, thickness distribution at various temperature and blank diameter is evaluated from experiments and is modelled using intelligent techniques such as Artificial Neural Networks (ANN) and least squares Support Vector Machines (SVM).

Moreover, one of the important qualitative aspects in formability is to study the effect of temperature on thickness distribution of properly formed cups. It is found that below 150☌, formability of the material is very poor and above 150☌ till 400☌, Limiting Draw Ratio (LDR) is found to be 1.86 which is considerably lesser than other structural alloys. The stress results obtained analytically have been found to be in excellent agreement with the results obtained from the finite element analysis.ĭeep drawing experiments have been performed in order to study formability of Ti-6Al-4V alloy sheet at temperature ranging from room temperature to 400☌. Further, a finite element model has been created using ANSYS 15.0. These properties of section are then used to calculate the stresses of each ply of I-beam at any given level. Analytical expressions for calculating the properties of laminated beam section such as centroid, axial and bending stiffness have been derived. The objective of this study focuses on the development of an analytical method for inter-laminar stress analysis of laminated composite I-beam by extending the applicability of lamination theory usually used at laminate level to composite structure level.

Unlike isotropic materials, the parametric study and optimization analysis of composite structures is complicated due to high number of parameters involved in designing like material properties, fiber orientation and stacking sequence, besides geometric dimensions.

The advantage of material properties and flexibility of choosing material have made composite materials a primary preference for structural and aircraft applications.

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