Friction Stir Welding (FSW) appears to be one of the most attractive joining techniques for aircraft industry because, being a solid state welding process, allows overcoming all the well-known problems related to phase transformation of fusion welding process. In addiction, welding is very attractive in view of the fact that it allow saving weight in aerostructures if compared to the riveting technology. In the present paper, the experimental mechanical characterization of a subcomponent manufactured using the FSW lap joint technique is presented. The coupons simulate a bulkhead panel, i.e. a panel which separates a pressurized ambient of aircraft (i.e. the cabin) by another non-pressurized (i.e. the hold). Such a panel is usually stiffened by extruded parts that are riveted to the panel itself. In this case the extruded parts, with a T shape section, are friction stir welded to the panel by means of two different beads in single lap configuration. Loading conditions have been chosen to simulate two real operative conditions: hoop stress and T-pull. Results allow appreciating the good performances attained by coupons. Some specific features of FSW w.r.t. lap joint, such as hook defect, play a significant role in both the failure occurrences observed during the static tests and in the crack initiation phenomenon observed during the cyclic tests. Care should be put in both process parameters setting and tool design in order to minimize the hook defect occurrence. On the basis of the experimental characterization carried out, the following conclusion can be drawn: 1) FSW appears to be a suitable welding technology to make sound lap joints of extruded parts on rolled sheets. The obtained overlap friction stir welds resulted free of distortions and appreciable defects. 2) Static mechanical properties in hoop stress loading way are very high compared to the skin parent alloy. The joint mechanical efficiency resulted close to one. 3) Static mechanical properties in T-pull loading appear very high if compared with those provided by conventional riveted joints. 4) Fatigue properties are fully governed by the hooking material in the advancing side of beads: this defect plays a significant role in the crack initiation both upon T-pull and hoop stress loading. Its significant role is present at every fatigue stress level, even if the failure modes can be significantly different. As a consequence, much care should be put in setting the process parameters and in designing the tool geometry in order to minimize the hook defect occurrence. Probably an important role, in hook defect occurrence, is played by skin cladding layer too.


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    Title :

    Mechanical characterization of aircraft panels stiffened using friction stir welded extruded sections


    Contributors:
    Prisco, A. (author) / Squillace, A. (author) / Prisco, U. (author) / Bitondo, C. (author) / Serroni, G. (author)


    Publication date :

    2010


    Size :

    6 Seiten, 12 Bilder, 1 Tabelle, 18 Quellen



    Type of media :

    Conference paper


    Type of material :

    Storage medium


    Language :

    English





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