Buckling Analysis of Laminated Composite Panel with Elliptical Cutout Subject to Axial Compression

<table>Comparison of the buckling load of laminated composite panel shells versus (a) ratios <svg height="15" id="M24" style="vertical-align:-2.22495pt" version="1.1" viewbox="0 0 23.700001 15" width="23.700001" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink">
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</svg> and (b) <svg height="14.85" id="M25" style="vertical-align:-2.22495pt" version="1.1" viewbox="0 0 30.487499 14.85" width="30.487499" xmlns="http://www.w3.org/2000/svg" xmlns:xlink="http://www.w3.org/1999/xlink">
<g transform="matrix(.017,-0,0,-.017,.062,12.012)"><path d="M559 163q-23 -66 -68 -163h-474l6 26q62 4 79.5 19.5t28.5 75.5l78 409q7 35 8.5 49t-8 25t-24 13t-51.5 5l5 28h266l-6 -28q-65 -5 -79.5 -18t-25.5 -74l-76 -406q-10 -57 14 -75q12 -13 96 -13q93 0 126 29q41 40 76 109z" id="x1D43F"></path></g><g transform="matrix(.017,-0,0,-.017,9.769,12.012)"><path d="M368 703l-264 -866h-60l265 866h59z" id="x2F"></path></g><g transform="matrix(.017,-0,0,-.017,16.772,12.012)"><path d="M780 372q0 -191 -178 -297q-128 -75 -335 -75h-250l7 27q61 7 77 22t28 76l77 398q11 62 0 76.5t-77 22.5l6 28h292q164 0 258.5 -67.5t94.5 -210.5zM678 375q0 119 -73 180.5t-201 61.5q-62 0 -82 -13q-17 -7 -25 -53l-80 -427q-8 -47 -4 -62t26 -20q24 -6 80 -6
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</svg>, for elliptical cutout with constant cutout width and various cutout heights.</table>

Modelling and Simulation in Engineering

fig6

Figure 6

Figure 6: Buckling Analysis of Laminated Composite Panel with Elliptical Cutout Subject to Axial Compression 