The following conclusions can be drawn: Several product forms and alloys are available; p=1.7-1.9 g cm(exp-3 ). Advanced alloys with good mechanical/technological properties are available. More than 33% increase in specific strength is possible and some alloys with symmetry under tension/compression. HT alloys are applicable until 200 deg C. Fatigue strength (Kt=1.0, R=0.1) is 150-220 MPa. Flammability issue is under discussion between Airbus and the FAA. Intrinsic corrosion behavior of alloys has improved. Green surface protection systems are evaluated, dependent upon alloy. Forming is possible under elevated temperatures. FSW and LBW works well and results in good properties. Buckling behavior of stiffened panels is comparable to aluminium.


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    Title :

    AEROMAG - magnesium suitable for aeronautic applications?


    Contributors:

    Published in:

    Light Metal Age ; 67 , 3 ; 34-39


    Publication date :

    2009


    Size :

    6 Seiten, 15 Bilder, 2 Tabellen, 3 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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