This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Residual Strength of an Aluminum Panel with a Centric Hole and One Cracked Ligament
Technical Paper
1999-01-1574
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
The residual strength of an aluminum panel with a centric hole and one cracked ligament was investigated experimentally. Each of the 7075-T6 aluminum panels which were tested included a cracked ligament of varying length on one side of the centric hole and an uncracked ligament on the other side of the hole. The failure of such a panel subjected to uniform tensile loading normally occurs according to the lower of two modes: brittle fracture or a net section type of yielding. On the other hand, the question of whether one or both ligaments fail is not easily answered. Results show that one or two ligament failure depends upon test conditions such as crack length and loading method. For short crack lengths, the uncracked ligament will fail almost simultaneously with the failure of the cracked ligament. In the case of long crack lengths, the ligament with the crack will completely fracture, followed by arrest until the load is increased so as to cause failure (by yielding) in the remaining uncracked ligament. Test results also show that the loading method used by the test machine also affects the ligament failure process. Some results for panels subjected to fastener loading are also discussed.
Recommended Content
Magazine Issue | AEROSPACE ENGINEERING 2013-02 |
Technical Paper | Benchmarking Study of Aluminum Front Suspension Components |
Technical Paper | Honeycomb Specimens Under Combined Compressive and Shear Displacement Conditions |
Authors
Topic
Citation
Myose, R., Smith, B., Seneviratne, W., Khalil, S. et al., "Residual Strength of an Aluminum Panel with a Centric Hole and One Cracked Ligament," SAE Technical Paper 1999-01-1574, 1999, https://doi.org/10.4271/1999-01-1574.Also In
References
- Newman, J.C. Jr Predicting Failure of Specimens with Either Surface Cracks or Corner Cracks at Holes NASA TN D-8244 June 1976
- Bowie, O.L. Analysis of an Infinite Plate Containing Radial Cracks Originating at the Boundary of an Internal Circular Hole J. Math. & Phys. 25 1956 60 71
- Feddersen, C.E. Evaluation and Prediction of Residual Strength of Center Cracked Tension Panels ASTM 486 1970