Efforts were made to compare similarly configured, riveted aluminum 2024-T3, and GLARE (glass-reinforced aluminum) lap joints to test the effects of a severe corrosive environment on fatigue crack initiation, growth, and residual strength of a typical aging aircraft material and one candidate replacement. Preliminary tests were performed on center-cracked GLARE panels versus monolithic aluminum to investigate the effects of load frequency and environment. Lapped and riveted specimens of each type material were tested in 5 wt. % NaCl solution, distilled water, and in air. The applied gross stress level used was 120 MPa at frequencies of 1 Hz and 10 Hz. The specimens were periodically inspected for cracks and tested to failure. Cracking behavior, fatigue life, and residual strength were compared. Fatigue lives of the aluminum alloy decreased considerably in the presence of moisture with the worst degradation occurring in salt water at the lower 1 Hz frequency. The GLARE joints did not fail even after five projected lifetimes and retained 75 % of their original strength. GLARE, with its superior corrosion fatigue resistance, may make a suitable repair/replacement material in aging aircraft. For example, 'GLARE 3-3/2-0.3' describes a composite of aluminum and cross-plied glass fibers, with 3 aluminum layers and 2 glass layers with individual aluminum sheet thicknesses of 0.3 mm. 'GLARE' in this paper refers to the GLARE 3 configuration.


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    Title :

    Corrosion fatigue of aluminum and GLARE riveted lap joints


    Additional title:

    Schwingungsrißkorrosion von Aluminium- und glasfaserverstärkten Aluminium-Überlappnietverbindungen


    Contributors:


    Publication date :

    1995


    Size :

    10 Seiten, 15 Bilder, 2 Tabellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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