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A study of secondary instabilities in postbuckling composite aerostructures

Published online by Cambridge University Press:  03 February 2016

B. G. Falzon  and
M. Cerini
B. G. Falzon
Affiliation:
Department of Aeronautics, Imperial College, London, UK
M. Cerini
Affiliation:
Adams Kara Taylor, London, UK
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Abstract

A number of experimental studies have shown that postbuckling stiffened composite panels, loaded in uniaxial compression, may undergo secondary instabilities, characterised by an abrupt change in the buckled mode-shape of the skin between the supporting stiffeners. In this study high-speed digital speckle photogrammetry is used to gain further insight into an I-stiffened panel’s response during this transient phase. This energy-dissipating phenomenon will be shown to be able to cause catastrophic structural failure in vulnerable structures. It is therefore imperative that an accurate and reliable methodology is available to predict this phenomenon. The shortcomings of current non-linear implicit solution schemes, found in most commercially-available finite element codes, are discussed. A robust and efficient strategy, which utilises an automated quasi-static/pseudo-transient hybrid scheme, is presented in this paper and validated using a number of experimental tests. This approach is shown to be able to predict mode-jumping with good accuracy.

Type
Research Article
Information
The Aeronautical Journal , Volume 111 , Issue 1125 , November 2007 , pp. 715 - 729
Copyright
Copyright © Royal Aeronautical Society 2007 

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