Structure responses in the riveted and the friction stir welded stringer panel under the tensile loading

摘要

In this paper,applications of friction stir welding in the integral fuselage structure are studied.In order to compare with the traditional riveted stringer panel,the integral panels are joined by two ways: one is by single-row rivets and the other one is by friction stir welding.Two kind finite element models are built by Abaqus 6.10.Stress distributions are analyzed and compared.For welded panel,a FORTRAN program of the SIGINI subroutine is made to input the residual stress profile to the finite element model of friction stir welded panel.Compared with the rivet joint,friction stir welded joint can reduce the weight of fuselage.In the same applied stress,the sample joint with rivets has the higher stress areas around the rivet hole,the sample joint with friction stir welding avoids the stress concentration in junctions.