The invention relates to an integral outer wing and a manufacturing method thereof. The integral outer wing comprises a front beam (1), a middle beam (2), a rear beam (3), a skin (4) and a stringer (5), the front beam (1), the middle beam (2) and the rear beam (3) are arranged between the skins (4), and the stringer (5) is arranged on the skins (4); the manufacturing method comprises the following steps that S1, a C-shaped long beam and an omega-shaped stringer are laid on a core mold, a core mold is assembled, and an I-shaped long beam is obtained; s2, a skin is laid on the assembled core mold, and an integral outer wing prefabricated body is manufactured; s3, the integral outer wing prefabricated body is placed in a forming mold, glue injection curing is conducted through an RTM technology, and an integral outer wing crude finished product is obtained; and S4, carrying out edge cutting and polishing on the rough finished product to obtain a final integral outer wing. Compared with the prior art, the surface of the whole outer wing has no step difference, the lift force of the outer wing can be improved, the integration degree is high, the number of fasteners is greatly reduced, and the assembly time is shortened.
本发明涉及一种整体外翼及其制造方法,整体外翼包括前梁(1)、中梁(2)、后梁(3)、蒙皮(4)和长桁(5);所述前梁(1)、中梁(2)和后梁(3)设置在蒙皮(4)之间,长桁(5)设置在蒙皮(4)上;制造方法包括以下步骤:S1:在芯模模具上铺贴C型长梁、Ω型长桁,并将芯模组装,获得工字型长梁;S2:在组装芯模模具上铺贴蒙皮,制得整体外翼预制体;S3:整体外翼预制体放在成型模具里,通过RTM工艺注胶固化制得整体外翼粗成品;S4:粗成品经过边缘切割、打磨获得最终整体外翼。与现有技术相比,本发明整体外翼表面无阶差,可提升外翼升力,整体化程度高,大大降低紧固件数量,减少装配工时。
Integral outer wing and manufacturing method thereof
一种整体外翼及其制造方法
2024-05-28
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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