Abstract
The contact at a typical aircraft skin/rivet interface was analyzed using plane and shell finite elements. The focus was on fretting as a crack nucleation mechanism in lap joints. Crack nucleation lives were predicted using a multiaxial fatigue theory. For low remote stresses, an increase in friction coefficient increased life. The opposite was true for high remote stresses. The increase in rivet head clamping pressure increased the crack nucleation life. Plasticity blunted the effects of friction coefficient and clamping.
| Original language | American English |
|---|---|
| Pages (from-to) | 2761-2771 |
| Number of pages | 11 |
| Journal | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Volume | 4 |
| State | Published - 1997 |
| Externally published | Yes |
| Event | Proceedings of the 1997 38th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Part 4 (of 4) - Kissimmee, FL, USA Duration: Apr 7 1997 → Apr 10 1997 |
ASJC Scopus subject areas
- Architecture
- General Materials Science
- Aerospace Engineering
- Mechanics of Materials
- Mechanical Engineering