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The Limitations of Wide Strut Analyses for Determination of the Optimum Proportions of Panels Having Unflanged Integral Stiffeners

Published online by Cambridge University Press:  04 July 2016

M. E. Grayley
M. E. Grayley*
Affiliation:
Engineering Sciences Data Unit, Royal Aeronautical Society
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Extract

Determination of the cross-sectional dimensions of panels of least weight typically follows the procedure set out by D. J. Farrar in this JOURNAL 20 years ago. Farrar made the assumption that for panels of least weight the flexural and local instability stresses were coincident. Using this he investigated the Z-section stringer-skin combination and later, using the same method, E. J. Catchpole studied the panel having unflanged integral stiffeners. In both cases the panel is treated as a wide strut, i.e. the flexural buckling load was taken to be the Euler buckling load, no account being taken of the effect of edge restraint.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 73 , Issue 706 , October 1969 , pp. 888 - 890
Copyright
Copyright © Royal Aeronautical Society 1969 

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References

1. Farrar, D. J. The Design of Compression Structures for Minimum Weight. Journal of the Royal Aeronautical, Society, vol 59, No 469, pp 1041–1052, November 1949.Google Scholar
2. Catchpole, E. J. The Optimum Design of Compression Surfaces Having Unflanged Integral Stiffeners. Journal of the Royal Aeronautical Society, Vol. 58, pp 765–768, November 1954.Google Scholar
3. Bruce, J. and Robinson, J. R. The Buckling and Bending of Orthothropic Sandwich Panels in Compression and Shear. Unpublished work at Handley Page Ltd, 1956.Google Scholar
4. Information On the Use of Data Items on Sandwich Panels. Item No 68029, Engineering Sciences Data Unit, Royal Aeronautical Society, October 1968.Google Scholar
5. Design for Minimum Weight. Compression Panels with Unflanged Integral Stiffeners. Item No 69014, Engineering Sciences Data Unit, Roval Aeronautical Society, September 1969.Google Scholar