A fuselage structure of an aircraft is described. The fuselage structure comprises a fuselage skin; and a plurality of frame elements (30) spaced apart from each other in a direction parallel to the longitudinal axis of the aircraft for supporting the fuselage skin. The fuselage skin consists of a plurality of interconnected fiber-reinforced composite skin panels (6) extending between and connected to each pair of frame elements. The composite skin panel also includes a reinforcement (66) integrally formed in each of the composite skin panels. A method for manufacturing a fuselage skin is also described. The composite skin panels may be interconnected and/or connected to the frame elements by inductive weld connections.

    本发明描述了一种飞行器的机身结构。机身结构包括:机身蒙皮;以及多个框架元件(30),其在平行于飞行器纵向轴线的方向上彼此隔开,以用于支撑机身蒙皮。机身蒙皮由多个互连的纤维增强复合蒙皮壁板(6)组成,纤维增强复合蒙皮壁板(6)在各对框架元件之间延伸并且连接到各对框架元件。复合蒙皮壁板还包括一体形成在各个复合蒙皮壁板中的加强件(66)。本发明还描述了一种用于制造机身蒙皮的方法。复合蒙皮壁板可以通过感应焊接连接互连和/或连接到框架元件。


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    Titel :

    Fuselage structure of aircraft and method for manufacturing fuselage structure of aircraft


    Weitere Titelangaben:

    飞行器的机身结构及用于制造飞行器的机身结构的方法


    Beteiligte:

    Erscheinungsdatum :

    15.04.2022


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS / B29L INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES , Index-Schema für besondere Gegenstände in Verbindung mit Unterklasse B29C



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