The invention refers to an integrated composite trailing edge and a manufacturing method thereof. The trailing edge comprises: an integrated main structure comprising: an upper cover (1), lower flanges, and a set of ribs (23) extending between the upper cover (1) and the lower flanges; a set of sandwich type lower panels (22) attachable to the lower flanges of the integrated main structure. The method comprises the steps of providing a set of prepreg laminated preforms over a set of tool modules (7) having a hollow (9) so that each laminated configures a double C-shaped laminated preform (10) having an upper section (15) with a recess (16), two primary (3) and secondary (8) flanges, the upper section (15) partly forming the upper cover (1), the two primary flanges (3) partly forming the ribs (23) and the two secondary flanges (8) forming the lower flanges.


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    Title :

    Aircraft integrated composite trailing edge and manufacturing method thereof



    Publication date :

    2015-06-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS



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