The design, development and testing of an in situ consolidated thermoplastic composite support structure for the ducted tail rotor and vertical fin of a medium helicopter was preceded by a series of material characterization tests. The base material chosen for this component is APC-2/AS4. The thickness of the laminate ranges from 0.115 inch to 0.291 inch. The outer surface is covered by two plies of off-axis APC-2/S-2 glass fiber reinforced tape. A full-scale component was subjected to static tests, up to ultimate load, for five different maneuver conditions. It was then tested to failure for a yaw maneuver condition that has the greatest combined loading. Failure occurred at 237% of limit load. The cost savings exceeded program goals. Weight savings were more than twice as great as was targeted. This was achieved by completely altering the structural concept from the metal prototype configuration, in order to minimize the part count and make optimum use of the strength tailoring possible with composites.


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    Titel :

    Development of a complex fiber-placed carbon/PEEK airframe component


    Beteiligte:
    Tessnow, K.E. (Autor:in)


    Erscheinungsdatum :

    1999


    Format / Umfang :

    15 Seiten, 9 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




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