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An analysis method suitable for prediction of strain fields in a stiffened composite panel containing a center crack is presented. The analysis is based on the superposition of anisotropic elasticity solutions for an infinite plate. Strain field predictions are made for two panel configurations and compared with strain gage data. Reasonable comparisons between predictions and measurements are obtained. This paper lays the foundation for the predictions of the damage tolerance of stiffened composite panels that will be discussed further in a second paper.
Structural engineer, Boeing Commercial Airplane Group, Advanced Composites Development, Seattle, WA
Associate professor, University of Washington, Seattle, WA
Stock #: CTR10465J