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IN Part I of this paper, the basic equations were established for the various modes of instability of flat sandwich panels subjected to lengthwise compression. Whilst these equations are valuable in determining the strength of a given panel they do not give a direct indication of the crosssectional dimensions of a panel required to carry a given load, especially if the panel is to be the optimum, i.e. of minimum weight.
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Aug 1, 1960
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