Rivets are widely used as a means of fastening in airframe construction industry. Among the other types of fasteners riveted joints are preferred in such applications due to their permanence after installation and their economical advantages. In a riveted joint, it is known that residual stresses are present as a result of the installation process. Furthermore, during the flight of an aircraft, the fuselage comes across pressurization and depressurization cycle. During one flight pressurization-depressurization cycle is completed and such cycles are repeated throughout the service life of the aircraft. As a result, the panels and the rivets are subjected to fatigue type loading. The integrity of the joint must be maintained against this combination of service loads and the residual stresses. The present study is aimed to develop and analyze three-dimensional finite element model of riveted lap, and then the numerical analysis (SolidWorks Simulation) are carried out to calculate the residual stress values and fatigue values in the riveted lap joint under the effect of varying temperature. The result shows that the fatigue life varies inversely proportion to residual stresses whereas damage varies directly proportion to residual stresses. The maximum residual stress obtained is 292 MPa at temperature of 150°C and the minimum residual stress obtained is 15 MPa at temperature of −50°C. Maximum damage is 60% at 150°C and minimum is 8% at −50°C. Maximum life is 234346 cycles at −50°C and minimum life is 33111 cycles at 150°C.

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