• Optimum design of laminated composite under axial compressive load

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      https://www.ias.ac.in/article/fulltext/sadh/036/01/0073-0085

    • Keywords

       

      Composite laminate; genetic algorithm; buckling; optimum design; finite element.

    • Abstract

       

      In the present study optimal design of composite laminates, with and without rectangular cut-out, is carried out for maximizing the buckling load. Optimization study is carried out for obtaining the maximum buckling load with design variables as ply thickness, cut-out size and orientation of cut-out with respect to laminate. Buckling load is evaluated using a ‘simple higher order shear deformation theory’ based on four unknown displacements $u,v,w_b$ and $w_s$. A C1 continuous shear flexible finite element based on HSDT model is developed using Hermite cubic polynomial. It is observed that for thick anti-symmetric laminates, the non-dimensional buckling load decreases with increase in aspect ratio and increase in fibre orientation angle. There is a decrease in the non-dimensional buckling load of symmetric laminate in the presence of cut-out.

    • Author Affiliations

       

      N G R Iyengar1 Nilesh Vyas2

      1. Department of Aerospace Engineering, Jain University, Jain Global Campus, Jakkasandra Post, Bangalore 562 112, India
      2. Hindustan Petroleum Corporation Limited (HPCL), Mangalore LPG Import Facility, Mangalore 575 006, India
    • Dates

       
  • Sadhana | News

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