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Abstract:
Although many components of aircraft and aerospace structures are subjected to biaxial applied loads, the effects on the fracture process of loads applied parallel to an existing crack have not yet been fully appreciated. This report summarizes the study results of Fracture and Fatigue of Aircraft Structural Materials Under Biaxial Loading, which was initiated for the purpose of examining both the theoretical and experimental aspects of this problem. Analytical work addressed various implications of biaxially applied loads on the crack-tip stress field, the stress intensity factor, the angle of initial crack extension, and the critical or fracture loads. Several different geometries were examined including center cracks aligned with and at an angle to the load axes, shear panels, double and multiple cracked bodies. Keywords: Aluminum alloys; Plexiglass. (kt)
| Limitations: |
 APPROVED FOR PUBLIC RELEASE |
| Description: |
Final rept. Oct 78-Dec 79 |
| Pages: |
36 |
| Report Date: |
DEC 79 |
| Contract Number: |
AFOSR-76-3099 |
| Report Number: |
A580512 |
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Keywords relating to this report:
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