To provide a thermoplastic multi-grid overmolded/co-consolidated aircraft fuselage structure.SOLUTION: An aircraft structure and a method of construction thereof avoid inefficiencies involved in current methods of constructing the aircraft structure, reduce the manufacturing time required for constructing the aircraft structure, and reduce the cost involved in constructing the aircraft structure. The aircraft structure and the method of construction thereof comprise a geodesic or multi-grid framework of intersecting thermoplastic composite strips that are joined to an interior surface of a thermoplastic composite fuselage skin panel through overmolding/co-consolidation of the grid framework and the skin panel.SELECTED DRAWING: Figure 1

    【課題】熱可塑性多重格子オーバーモールド/共固化航空機胴体構造を提供する。【解決手段】航空機構造およびその構築方法は、航空機構造を構築する現在の方法に伴う非効率性を回避し、航空機構造の構築に必要な製造時間を短縮し、航空機構造の構築に伴うコストを削減する。航空機構造およびその構築方法は、格子フレームワークおよび外板パネルのオーバーモールド/共固化によって熱可塑性複合材胴体外板パネルの内面に接合される交差する熱可塑性複合材ストリップの測地線または多重格子フレームワークからなる。【選択図】図1


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    Titel :

    THERMOPLASTIC MULTI-GRID OVERMOLDED/CO-CONSOLIDATED AIRCRAFT FUSELAGE STRUCTURE


    Weitere Titelangaben:

    熱可塑性多重格子オーバーモールド/共固化航空機胴体構造


    Beteiligte:

    Erscheinungsdatum :

    02.04.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Japanisch


    Klassifikation :

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



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