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In-Plane
Compressive Behaviour of Stiffened Thin-Skinned CFRP Panels
with a Stress Concentrator |
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Introduction
Composite materials are increasingly being used in the
aerospace industry today due to their
excellent specific strength and stiffness characteristics.
Unfortunately the full potential of
efficient composite structures is yet to be realised due
to inadequate practical theories capable of predicting
material failure. Aerospace structures tend to comprise
of thin skins relying upon stiffeners for lateral and
in-plane stability.
The aim of this study is to extend our knowledge in the
field of strength prediction in stiffened
panels subjected to in-plane loading. The panels may include
stress concentrators in the form
of open holes or impact damage. The former is likely to
be encountered in structures that
require cut-outs for the purpose of access or weight reduction
whilst the latter is a shortcoming of composite materials
in that they are susceptible to impact damage.
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