Abstract
For many years shot peering has been used to provide fatigue resistance and form to airplane wing skins at the Boeing Commercial Airplane Company. In this process, the peening intensities used to form a new wing skin have been obtained through the use of approximate geometric relationships, along with a considerable amount of trial and error testing. This paper describes a numerical model that has been applied to replicate the shot peening process used at Boeing. The model is used to predict peening intensities and the initial size of the skin (flat pattern) given an arbitrary aerodynamic contour requirement. Discussion focuses on the finite element method and special optimization techniques used in the approach.
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