Aircraft wing skin contouring as a result of residual stress distributions induced by shot peening

Abstract

Shot peening is a viable method for the forming of aircraft wing skins to aerodynamic contours. Presently, geometric methods used to calculate peening intensity patterns are approximate. These methods are based on simplifying assumptions which are not valid for complex contours. The scope of the work presented in this thesis is to develop a more accurate method of predicting peening intensity patterns. The finite element is used to model the effects of shot peening. Inversion of the equations to determine an exact solution for the peening intensity pattern is impossible. An approximate solution is found through numerical methods taking into account contour accuracy and peening intensity magnitudes. The resulting procedure produces accurate and reasonable results for the test cases presented, (computer simulations). Verification of the procedure will be completed when the system is field tested on an actual wing skin.