The invention relates to the technical field of aircraft design, in particular to an aircraft empennage leading edge composite material curing process, an aircraft empennage leading edge comprises an outer panel, a honeycomb sandwich layer and an inner panel which are sequentially laid from outside to inside, and the aircraft empennage leading edge composite material curing process sequentially comprises the steps that S1, the inner panel is laid on a male mold, and the inner panel is laid on a female mold; curing the inner panel; s2, an inner layer adhesive film is laid on the inner panel, a honeycomb sandwich layer is laid on the inner layer adhesive film, and the honeycomb sandwich layer is cured; s3, paving an outer layer adhesive film on the honeycomb sandwich layer; and S4, an outer panel is laid on the outer layer adhesive film, a female die is placed on the outer panel, the male die is removed, the inner panel, the honeycomb sandwich layer and the outer panel are sealed on the female die through a vacuum bag, and then the outer panel is cured in an autoclave. By adopting a mode of changing male mold paving to female mold curing, and by sequentially paving and step-by-step curing from inside to outside, the non-uniform paving, debonding and crushing of the honeycomb sandwich layer are effectively avoided.
本发明涉及飞机设计技术领域,尤其涉及一种飞机尾翼前缘的复材固化工艺,飞机尾翼前缘包括从外至内依次铺贴设置的外面板、蜂窝夹芯层和内面板,飞机尾翼前缘的复材固化工艺依次包括:步骤S1、在阳模上铺贴内面板,并对内面板进行固化;步骤S2、在内面板上铺贴内层胶膜,在内层胶膜上铺贴蜂窝夹芯层,并对蜂窝夹芯层进行固化;步骤S3、在蜂窝夹芯层上铺贴外层胶膜;步骤S4、在外层胶膜上铺贴外面板,在外面板上放置阴模,去掉阳模并采用真空袋将内面板、蜂窝夹芯层和外面板密封在阴模上,然后于热压罐内对外面板进行固化。采用阳模铺贴转阴模固化的方式,通过从内至外依次铺贴和分步固化,有效避免了蜂窝夹芯层铺贴不均匀、脱粘及压溃。
Composite material curing process for leading edge of empennage of airplane
飞机尾翼前缘的复材固化工艺
2023-04-07
Patent
Electronic Resource
Chinese
M28-05 AIRPLANE EMPENNAGE FATIGUE TEST REALISATION
British Library Online Contents | 2003
|Airplane empennage and elevator jamming adjusting method
European Patent Office | 2023
|Bird-impact-resistant reinforcer for front edge of A-shaped airplane empennage
European Patent Office | 2023
|Vertical empennage and fuselage connecting structure and airplane
European Patent Office | 2024
|