Weight functions for composite repairs to stiffened panels |
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| Affiliation: | 1. Department of Aerospace Engineering, University of Michigan, Ann Arbor, MI 48109-2140 2, USA;2. Boeing-Egtvedt Chair, William E Boeing Department of Aeronautics and Astronautics, 211E Guggenheim Bldg, Seattle, WA 98195, USA |
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| Abstract: | This paper presents a weight function technique for calculating the stress intensity factors for composite repairs to cracks emanating from an internal notch, corrosion blend out, or a free edge under arbitrary loading in rib stiffened panels. The predictions are compared with both finite element and experimental values. This methodology represents a significant extension to existing assessment and design formulae that are currently limited to the case of uniform loading and flat unstiffened panels. |
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