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 language | English |
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| Title of host publication | International Aerospace Congress 1995: Proceedings; Second Pacific International Conference on Aerospace and Technology; Sixth Australian Aeronautical Conference |
| Publisher | Institution of Engineers, Australia |
| Pages | 639-645 |
| Number of pages | 7 |
| ISBN (Print) | 085825624X |
| Publication status | Published - 23 Mar 1995 |
| Event | International Conference on Aerospace Science and Technology - Melbourne, Australia Duration: 20 Mar 1995 → 23 Mar 1995 |
Conference
| Conference | International Conference on Aerospace Science and Technology |
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| Country/Territory | Australia |
| City | Melbourne |
| Period | 20/03/1995 → 23/03/1995 |