A method for manufacturing a structural component (1) made of composite material reinforced by stiffening stringers (2), the structural component (1) defining, in use, at least part of an outer shell (3) of a carrier (4) and comprising a skin (5) and a plurality of stringers (2) having a hollow cross-section rigidly and integrally fixed to the skin (5), the method comprises the steps of: a) laminating a plurality of first layers (5a) of uncured or pre-cured composite material onto an outer surface (6a) of a cured tool (6) to form a skin (5) such that, in use, a first face (5b) of the skin (5) defining an inner surface of the structural component (1) faces the outer surface (6a) of the tool (6), the inner surface of the structural component (1) facing the inner environment of the carrier (4); b) laminating a respective plurality of second layers (2a) of composite material on the longitudinally hollow expandable inserts (10) to form a plurality of stringers (2), each stringer (2) having a longitudinal axis (B) such that each stringer (2) is at least partially wound on an outer surface (10a) of a respective hollow insert (10), thereby defining a longitudinal cavity (11) of each stringer (2) joined by the associated hollow insert (10), and obtaining a plurality of reinforcing elements (12) in this way, each reinforcing element (12) being defined by a stringer (2) wound on a hollow insert (10); c) positioning each reinforcing element (12) on a second face (5c) of the skin (5) opposite the first face (5b) and, in use, defining an outer surface of the structural component (1) facing the external environment of the carrier (4) and such that the cavity (11) of each stringer (2) faces the second face (5c); d) holding each reinforcing element (12) on the second face (5c) of the skin (5) in a respective fixed position relative to the tool (6); e) accommodating the tool (6), the skin (5) and the reinforcing element (12) in a vacuum bag (13); f) compacting the first layer (5a) forming the skin (5) with the second layer (2a) forming the stringer (2) by applying a vacuum inside the vacuum bag (13); g) after step f), accommodating the tool (6), the skin (5) and the reinforcing element (12) in a further vacuum bag (15); h) sealing the other vacuum bag (15) to define a vacuum chamber (16) therein; i) applying a predetermined temperature and pressure to the outside of the vacuum chamber (16) in order to cure the composite material and to determine the rigid and integral attachment of the stringer (2) to the second face (5c) of the skin (5). A structural component (1) obtained by the above manufacturing method is also described.
一种用于制造复合材料制成的、由加劲桁条(2)增强的结构部件(1)的方法,该结构部件(1)在使用中限定载体(4)的外部壳体(3)的至少一部分并且包括蒙皮(5)和多个桁条(2),该多个桁条(2)具有刚性地且整体地固定到蒙皮(5)的中空截面,该方法包括以下步骤:a)将多个未固化复合材料或预固化复合材料的第一层(5a)层压到固化工具(6)的外表面(6a)上以形成蒙皮(5),使得在使用中限定结构部件(1)的内表面的蒙皮(5)的第一面(5b)面向工具(6)的外表面(6a),该结构部件(1)的内表面面向载体(4)的内部环境;b)在纵向中空可膨胀的插入件(10)上层压相应的多个复合材料的第二层(2a)以形成多个桁条(2),每个桁条(2)具有纵向轴线(B),使得每个桁条(2)至少部分地缠绕在一个相应的中空插入件(10)的外表面(10a)上,从而确定由相关的中空插入件(10)接合的每个桁条(2)的纵向腔(11),并且以这种方式获得多个增强元件(12),每个增强元件(12)由缠绕在一个中空插入件(10)上的一个桁条(2)限定;c)将每个增强元件(12)定位在蒙皮(5)与第一面(5b)相对的第二面(5c)上,并且在使用中限定结构部件(1)的外表面,外表面面向载体(4)的外部环境,并且使得每个桁条(2)的腔(11)面向第二面(5c);d)将蒙皮(5)的第二面(5c)上的每个增强元件(12)保持在相对于工具(6)的相应的固定位置;e)将工具(6)、蒙皮(5)和增强元件(12)容纳在真空袋(13)内;f)通过在真空袋(13)内部施加真空,将形成蒙皮(5)的第一层(5a)与形成桁条(2)的第二层(2a)压实在一起;g)在步骤f)之后,将工具(6)、蒙皮(5)和增强元件(12)容纳在其他真空袋(15)中;h)密封其他真空袋(15)以在其中界定真空室(16);i)向真空室(16)的外部施加预设的温度和压力,以便固化复合材料并确定桁条(2)与蒙皮(5)的第二面(5c)的刚性和整体附接。还描述了通过上述制造方法获得的结构部件(1)。
Method for producing structural component made of composite material reinforced with stiffening stringers, and structural component
用于制造复合材料制成的、用加劲桁条增强的结构部件的方法和结构部件
2023-12-08
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2023
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