An Experimental Investigation into the Effects of Flanged Holes in Hat-Stiffened Panels Loaded in Uniaxial Compression

Brian G. Falzon, Grant P. Steven

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

The effects of a 100 mm diameter integrally-flanged hole in a hat-stiffenend carbon-fibre composite panel, loaded in uniaxial compression, were investigated and compared with a similar panel containing an unflanged hole. Details of the manufacturing techniques used in the production of the integral flange are presented. The stiffening effects of the flange reduced the bending strains, which may lead to high interlaminar shear strains, around the cutout while increasing the membrane strains. These membrane strains were well below the limit strains for this composite material. The skin in the unflanged hole also underwent a change in buckling mode shape from three longitudinal half-wavelengths to five half-wavelengths. No such change was observed in the flanged panel and this buckled in four longitudinal half-wavelengths. The ultimate strength of both panels was determined by the load carrying capability of the stiffeners.
Original languageEnglish
Title of host publicationInternational Aerospace Congress 1995: Proceedings; Second Pacific International Conference on Aerospace and Technology; Sixth Australian Aeronautical Conference
PublisherInstitution of Engineers, Australia
Pages639-645
Number of pages7
ISBN (Print)085825624X
Publication statusPublished - 23 Mar 1995
EventInternational Conference on Aerospace Science and Technology - Melbourne, Australia
Duration: 20 Mar 199523 Mar 1995

Conference

ConferenceInternational Conference on Aerospace Science and Technology
CountryAustralia
CityMelbourne
Period20/03/199523/03/1995

Fingerprint Dive into the research topics of 'An Experimental Investigation into the Effects of Flanged Holes in Hat-Stiffened Panels Loaded in Uniaxial Compression'. Together they form a unique fingerprint.

  • Cite this

    Falzon, B. G., & Steven, G. P. (1995). An Experimental Investigation into the Effects of Flanged Holes in Hat-Stiffened Panels Loaded in Uniaxial Compression. In International Aerospace Congress 1995: Proceedings; Second Pacific International Conference on Aerospace and Technology; Sixth Australian Aeronautical Conference (pp. 639-645). Institution of Engineers, Australia.