This paper will discuss the results of friction stir welding AA6056 and AA6013 aluminum alloys for thin sections within the fuselage. The mechanical (tensile strength, fatigue, fatigue crack propagation and fracture toughness) and the corrosion (intergranular, exfoliation and stress corrosion cracking) coupon data gained so far, have lead to friction stir welding large panels for barrel testing. This barrel has the dimensions of an Airbus A330 wide body. This presentation covers the results out of the European projects WAFS and TANGO. The mechanical and corrosion data of the AA6056T6 and AA6013T6 in 4 mm thickness are given. For property improvements a water-cooling system was used on the AA6056T6. For this alloy type no difference in mechanical and corrosion properties was observed. All the gained coupon properties are far superior to the riveted solutions today so that large panels for damage-tolerant and barrel fatigue and static testing were welded. During this study the basic understanding of friction stir welding thin section components was improved by characterizing welds. The tensile test results are in the range of 80% to 90% of base material properties. The fatigue results show a drop of about 10% to base material, which is an improvement of today's riveting by 50%. The fatigue crack propagation behavior is better or like base material, even in the more critical area of the TMAZ. The fracture toughness results of the welds are in the range of the base material. The corrosion tests reveal no susceptibility to intergranular, exfoliation and stress corrosion cracking. The used water-cooling system showed no further property improvement for this alloy. Subsequently to obtaining this data, large panels for damage tolerant and barrel testing were friction stir welded.
Friction stir welding of aerospace alloys
2003
5 Seiten, 5 Bilder
Aufsatz (Konferenz)
Datenträger
Englisch
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