New objectives have been set for GFRP (Glass Reinforced Polymer) compo-site materials, for aeronautical structures. This essentially involves the trade-off between strength and lightness of structures. They also have good resistance to corrosion and abrasion. GFRP composites are made by free molding and finished with dedicated drill holes often for riveting assembly. Delamination associated with CNC drilling processes is a serious industrial problem. It serves as a qualification standard for GFRP composites for aeronautical structures. The purpose of this work is to develop a decision rule to minimize delamination defects during CNC drilling. The response sur-face methodology (RSM) is used. The diameter of the tool (∅) is considered in the configuration of the CN drilling by taking advantage of the expected functionality. Thus, the RSM methodology is used to establish objective modeling that correlates the drilling circumstances with the delamination fault. Therefore, the delamination is a quadratic function of the feed rates and the tool diameter. This optimizes the tool diameter and feed rate to improve the industrial performance indicators of riveted assemblies.
Nasser et al. (Thu,) studied this question.