Abstract
The aim of this work is the experimental investigation of fatigue failure in Refill Friction Stir Spot Welding joints. The specimens for the fatigue analysis were made of 0.8-mm-thick and 1.6-mm-thick 7075-T6 aluminium alloy which is used to fabricate aircraft fuselages consisting of a plate skin with a stiffening stringer. The load capacity of joints was determined by tensile/shear tests. Fatigue tests were carried out on an Instron E10000 testing machine at room temperature. High-cycle fatigue tests were carried out under the following conditions: a limited number of cycles equal to 2×106, a frequency of 50 (Hz), and a coefficient of stress cycle R=0.1. Microstructural features of fatigue fractures for different levels of variable load were examined using Scanning Electron Microscopy micrographs. The analysis of the fatigue fractures reveals that the Alclad layer at the bottom of the weld is a kind of structural notch and in this situation can be the location of the initiation of fatigue cracking. It was found that fracture mechanism depends on the value of load amplitude. Analysis of the SEM micrographs of fatigue fractures shown that the thermo-mechanically affected zone and heat affected zone are sources of fatigue failure.
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