Abstract
Fretting is a major cause of crack formation in aircraft structures like lap joints and dove tail joints. A tightly integrated mechanics-based method to relate fretting crack nucleation to the various parameters that influence it is presented. A finite element model of a rivet and the skin around it was analyzed to provide the stress state under various loads. The model incorporated residual stresses from riveting, plasticity and contact between the various surfaces. A multiaxial fatigue model was used to translate the results into a prediction of life to crack nucleation. Excellent comparisons with a set of controlled lap joint experiments provide the validation of this approach. Effects of the finite width of the experimental specimen were found to be small.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 1219-1226 |
| Number of pages | 8 |
| Journal | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Volume | 2 |
| DOIs | |
| State | Published - 1999 |
| Externally published | Yes |
| Event | Proceedings of the 1999 AIAA/ASME/ASCE/AHS/ASC Structrures, Structural Dynamics, and Materials Conference and Exhibit - St. Louis, MO, USA Duration: Apr 12 1999 → Apr 15 1999 |
All Science Journal Classification (ASJC) codes
- Architecture
- General Materials Science
- Aerospace Engineering
- Mechanics of Materials
- Mechanical Engineering
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