Automatic numerical determination of peening stress from objective shape.

The large thin-walled components in aerospace industry, such as wing panels of aircraft, are usually shaped with peen forming process by blasting numerous shots on the component to introduce compressive residual stresses in the surface layer. To obtain an objective shape, peening parameters are designed to introduce reasonable peening stresses, which are determined with physical trial and error traditionally. In this paper, an automatic numerical approach based on ABAQUS software is proposed to determine the peening stresses inversely from the objective shape. The approach consists of representation of peening stress field, monitoring of simulating shape, and performance of automatic calculation. With the approach, peening stresses in strip peened plates are inversely determined from measured bending curvatures. The variations of the peening stress field with peening parameters are obtained. The obtained peening stresses are compared with the results of regularly impacting simulations. The comparison shows an acceptable agreement and indicates the potential of the approach to determine the needed peening stresses for forming the aerospace components. [ABSTRACT FROM AUTHOR]