Analysis of Composite Laminate for Maximum Stiffness
Sharad D. Pawar1, Abhay Utpat2

1Sharad D. Pawar, Department of Mechanical Engineering, SVERI’s College of Engineering, Pandharpur, (Maharashtra), India.
2Abhay Utpat, Department of Mechanical Engineering, FTC’s College of Engineering and Research, Sangola, (Maharashtra), India.

Manuscript received on 20 May 2014 | Revised Manuscript received on 25 May 2014 | Manuscript published on 30 May 2014 | PP: 60-66 | Volume-3 Issue-2, May 2014 | Retrieval Number: B1105053214/2014©BEIESP
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Abstract: The purpose of this study is to develop optimization procedure to maximize the stiffness and minimize the weight of composite laminate subjected to in-plane loading .The design variables for optimization problem are fiber orientation angles, thickness of lamina and number of laminas. Maximum stress failure criteria are used to determine whether load bearing capacity is exceeded for a configuration generated during optimization process. In a recent year, the application of Fiber reinforced composite material has increased with increasing need of low weight, high strength, high stiffness etc. in aerospace industry, automobile industry, sporting equipment, civil industry etc. In the case of Fiber Reinforcement Plastic composite structural design, the requirements of certain application can be achieved not only by sizing the cross sectional areas and thickness of components but by changing the material system design i.e. optimizing the material system itself such as fiber orientation angle, ply thickness, stacking sequence etc. The optimization techniques are being used to assist the designer in finding an optimized solution. Carefully designed individual composite parts at present, are about 20-30% lighter than their conventional metal parts.
Keywords: Composite Material, FEA,Stiffness.

Scope of the Article: Composite Materials