The invention discloses a composite material integrated fuselage structure and a manufacturing method, the structure comprises a barrel section forming die, an inner skin-bulkhead barrel section, an adhesive, an R area filler and an outer skin, the barrel section forming die is a male die, adopts a combined frame structure steel die and is used for forming the inner skin-bulkhead barrel section; the inner skin-bulkhead barrel section is formed by paving a prepreg or a prefabricated body on a barrel section forming die, and finally curing and forming; during paving, the two ends of each section of the inner skin are directly and continuously paved to form a partition frame; each inner skin-bulkhead barrel section is independently cured and formed, and then the adjacent bulkheads are glued through an adhesive; after all the inner skin-bulkhead barrel sections are in butt joint, an outer skin is laid outside the inner skin-bulkhead barrel sections to form an integral fuselage section prefabricated part, and finally the integral fuselage section prefabricated part is solidified to form an integral fuselage structure; wherein for an R area formed between the outer skin and the bulkhead of the adjacent inner skin-bulkhead barrel section, R area filler is firstly laid in the R area before the outer skin is laid.
本发明公开了一种复合材料一体化机身结构及制造方法,所述结构包括桶段成型模、内蒙皮‑隔框桶段、胶粘剂、R区填充物、外蒙皮,其中:桶段成型模为阳模,采用组合式框架结构钢模,用于进行内蒙皮‑隔框桶段的成型;内蒙皮‑隔框桶段采用预浸料或预制体在桶段成型模上铺贴,最后进行固化成型;在铺贴时,直接在每一段内蒙皮的两端连续铺贴,形成隔框;每个内蒙皮‑隔框桶段单独固化成型,然后将相邻的隔框通过胶粘剂胶结;将所有内蒙皮‑隔框桶段对接后,在其外部铺设外蒙皮形成整体机身段预制件,最后固化形成一体化机身结构;其中,对于外蒙皮与相邻的内蒙皮‑隔框桶段的隔框之间所形成的R区,在铺设外蒙皮之前,先在其中铺放R区填充物。
Composite material integrated fuselage structure and manufacturing method
一种复合材料一体化机身结构及制造方法
2024-01-05
Patent
Electronic Resource
Chinese
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