The invention relates to an aircraft wing component, a wing assembly comprising the same, and methods for manufacturing the component and the assembly. A trailing edge structure of an aircraft wing issubjected, in use, to high temperature efflux from an aircraft's engines. Such elevated temperatures can detrimentally effect the ultimate tensile strength of the trailing edge. The aircraft wing component comprises a composite material having: a first portion (14) comprising a metal matrix (16) containing reinforcing material (17); and a second portion (15) comprising a metal matrix (18) containing a plurality of hollow metal ceramic spheres (19), the second portion being adjacent a surface (20) of the composite material. The provision of two portions, one of which contains a reinforcing material and the other comprising hollow spheres means that the composite material has both structural strength and heat shielding qualities where they are needed most in the component. The portion of the composite material containing the hollow metal ceramic spheres acts as an embedded layer of heat insulation.

    本发明涉及一种飞行器机翼部件、包括这种飞行器机翼部件的机翼组件,以及制造这种部件和组件的方法。飞行器机翼的后缘结构件在使用中经受来自飞行器的发动机的高温外排物。这种升高的温度会不利地影响后缘的极限拉伸强度。飞行器机翼部件包括复合材料,该复合材料具有:第一部分(14),第一部分(14)包括包含增强材料(17)的金属基体(16);以及第二部分(15),第二部分(15)包括包含多个中空金属陶瓷球体(19)的金属基体(18),第二部分与复合材料的表面(20)相邻。设置两个部分、其中一者包括增强材料并且另一者包括中空球体意味着部件在最需要结构强度和隔热性质的位置具有结构强度和隔热性质两者。复合材料的包含中空金属陶瓷球体的一部分用作隔热的嵌入层。


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    Titel :

    Aircraft wing component


    Weitere Titelangaben:

    飞行器机翼部件


    Beteiligte:

    Erscheinungsdatum :

    2020-09-22


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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