Study on analysis and prediction of riveting assembly variation of aircraft fuselage panel

This investigation is performed to develop a methodology for the variation analysis and prediction of aircraft fuselage panel riveting assembly. Firstly, according to the manufacturing process of the part of the aircraft fuselage panel, the method of influence coefficient (MIC) based on key feature deviation is proposed. Secondly, the mechanism of component deformation in riveting process is expounded, and the method to approximately compute the global distortion, caused by rivet deformation, of the fuselage panel is presented. The proposed method is illustrated through a case study on the riveting assembly process of a sidewall panel, the local plastic deformation near the riveting holes is ignored but the computing resources are saved, the complex and time-consuming computation are avoided. The reasonableness of the proposed method is verified by the measurement data of the prototypes.