| タイトル | Advances in Structural Integrity Analysis Methods for Aging Metallic Airframe Structures with Local Damage |
| 著者（英） | Rose, Cheryl A.; Harris, Charles E.; Starnes, James H., Jr.; Piascik, Robert S.; Young, Richard D.; Newman, James C., Jr. |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 2003-02-01 |
| 言語 | eng |
| 内容記述 | Analysis methodologies for predicting fatigue-crack growth from rivet holes in panels subjected to cyclic loads and for predicting the residual strength of aluminum fuselage structures with cracks and subjected to combined internal pressure and mechanical loads are described. The fatigue-crack growth analysis methodology is based on small-crack theory and a plasticity induced crack-closure model, and the effect of a corrosive environment on crack-growth rate is included. The residual strength analysis methodology is based on the critical crack-tip-opening-angle fracture criterion that characterizes the fracture behavior of a material of interest, and a geometric and material nonlinear finite element shell analysis code that performs the structural analysis of the fuselage structure of interest. The methodologies have been verified experimentally for structures ranging from laboratory coupons to full-scale structural components. Analytical and experimental results based on these methodologies are described and compared for laboratory coupons and flat panels, small-scale pressurized shells, and full-scale curved stiffened panels. The residual strength analysis methodology is sufficiently general to include the effects of multiple-site damage on structural behavior. |
| NASA分類 | Aeronautics (General) |
| 権利 | Copyright, Distribution within the U.S. granted by agreement |
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