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An experimental investigation of the post-buckled efficiency of Z-section stringer-skin panels

Published online by Cambridge University Press:  04 July 2016

A. Rothwell
A. Rothwell*
Affiliation:
College of Aeronautics, Cranfield Institute of Technology
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Extract

A stiffened panel, designed so that failure in compression will occur afterinitial buckling, suffers a loss of axial stiffness due mainly to buckling of the skin between stringers and a consequent loss of flexural rigidity of the panel as a whole. The stringers will then carry an increasing proportion of the total compressive load, provided that the stringers themselves are of sufficient buckling resistance. Failure — due either to flexural buckling of the complete panel or to some other mode of stringer failure — can occur at a load substantially in excess of skin buckling. Behaviour of this kind is commonly found in very light structures for which it may be desirable to concentrate the load carrying capacity in certain discrete members, with a minimum gauge skin in between. However, a post-buckled design may also be preferred in rather more heavily loaded structures, in an attempt to reduce the loss of efficiency in a practical design when some restriction on, say, minimum stringer pitch is imposed. The purpose of the present series of tests is to investigate the post-buckled efficiency of a particular family of Z-section stringer-skin panels, of a design representative of current practice, with a stringer pitch chosen to be close to one-third of the effective panel length.

Type
Research Article
Information
The Aeronautical Journal , Volume 85 , Issue 840 , January 1981 , pp. 29 - 33
Copyright
Copyright © Royal Aeronautical Society 1981 

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References

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