Assignment Task:

Requirement 
This assignment just focuses on buckling analysis to find out the first buckling load, which is the lowest buckling load and is mostly concerned in practice. Therefore, you can neglect the prebuckling analysis and the postbuckling analysis described in this document. I want you to investigate the effect of the shell thickness and composite materials on the first buckling load of the shell panel with a circular hole without changing the geometry of the structure. You can just use the element type S9R5 to finish all the simulations.   
Consider that the laminate has a basic code [±45]ms. Each layer has the same thickness of 0.0056 in. To investigate the thickness effect, run a set of calculations by changing the value of m from 1 to 5.  Two materials, graphite/epoxy with fibre volume fraction of 70% and glass/epoxy with fibre volume fraction of 45% should be investigated. The materials and their properties can be found from Table 2.2 of the text book. You will find out that you need to provide the shear moduli G13 and G23 for the 3D shell elements. As Table 2.2 does not provide such parameters, you can treat G13 and G23 to have the same value as G12 in your simulations. 
 Write a report with no more than 4 pages to summarize your study. In the report, you should use your own language and your own results to cover:

1. Description of the physical problem:

  •  Geometry and material of the structure with a drawing
  •  Objective of the finite element analysis and boundary conditions 


 2. Description of the finite element model and the method to simulate the problem:  

  •  Show the original mesh of the finite element model and the deformed mesh corresponding to the first buckling mode for only one simulation
  •  Element type and number of elements
  •  The keyword in Abaqus to carry out buckling analysis and the way to find the buckling loads.

3. Description of the results and short discussions:  

  •  Plot the curves to show the first buckling load versus the representative thickness number m for both materials.
  •  Briefly describe the results (curves) and briefly discuss your findings.  

 Laminated composite shells: buckling of a cylindrical panel with a circular hole
Product: Abaqus/Standard  
This example illustrates a type of analysis that is of interest in the aerospace industry. The objective is to determine the strength of a thin, laminated composite shell, typical of shells used to form the outer surfaces of aircraft fuselages and rocket motors. Such analyses are complicated by the fact that these shells typically include local discontinuities —stiffeners and cutouts—which can induce substantial stress concentrations that can delaminate the composite material. In the presence of buckling this delamination can propagate through the structure to cause failure. In this example we study only the geometrically nonlinear behavior of the shell: delamination or other section failures are not considered. 

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  • Posted on : June 03rd, 2019
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