Abstract: A study on the longitudinal panel splice design of composite fuselage structures is carried out in accordance with the design criteria of mechanical joints and pressure differential level. In order to improve the analysis precision and design efficiency for multiple-bolted joints of panel splice, a novel method for calculating the load distribution of multiple-bolted joints is developed by using fastener elements. Combined with failure analysis of single-bolted joints, an evaluation method is presented to predict the failure strength of panel splice joints. Firstly, the feasibility of using fastener elements to determine the load distribution of multiple-bolted joints is confirmed via comparing the FEM result with experimental data. Then the fastener load distribution of panel splice joints is studied by applying fastener elements. Finally, based on the previous analysis of fastener loads, the failure strength of panel splice joints is assessed by failure analysis on single-bolted joints at critical locations. The study provides a very simple and effective approach for strength calibration of multiple-bolted joints.

Key words: composite, fuselage, longitudinal panel splice, multiple-bolted joint, failure analysis