飞机舱门密封系统的仿真分析与优化设计

Simulation Analysis and Optimization Design of Sealing System of Aircraft Cabin Door

对飞机舱门(简称舱门)密封系统进行仿真分析,通过正交试验对密封带的结构和材料进行优化设计。结果表明:密封带的截面圆角半径对舱门密封系统的应力产生影响,密封带的截面圆角半径为3.5 mm时舱门密封系统的压缩应力最小,最大接触应力最大;密封带的内部增强织物能同时提高舱门密封系统的压缩应力与最大接触应力,但对压缩应力的影响较小;密封带采用35U硅橡胶材料时舱门密封系统的压缩应力与最大接触应力最小,密封带采用75U硅橡胶材料时舱门密封系统的压缩应力与最大接触应力最大;舱门密封系统的压缩应力与最大接触应力随着密封带的硅橡胶材料邵尔A型硬度的增大而增大。当密封带的截面圆角半径为3.5 mm、采用邵尔A型硬度为50度的55U硅橡胶材料、内部有增强织物时,舱门密封系统的密封性能最优。

The sealing system of aircraft cabin door(referred to as cabin door)was simulated and analyzed,and the optimization design of the structure and material of the sealing strip was carried out through orthogonal experiments.The results showed that the section fillet radius of the sealing strip had a significant impact on the stress of the sealing system of cabin door.When the section fillet radius was 3.5 mm,the maximum contact stress of the sealing system was the highest,and the compression stress was the lowest.The internal reinforcement fabric of the sealing strip could simultaneously increase the compression stress and maximum contact stress of the sealing system of cabin door,but had little effect on the compression stress.When the sealing strip was made of 35U silicone rubber material,the compression stress and maximum contact stress of the sealing system of cabin door were the smallest,and when the sealing strip was made of 75U silicone rubber material,the compression stress and maximum contact stress were the largest.Moreover,the compression stress and maximum contact stress increased with the increase of Shore A hardness of the silicone rubber material.When the section fillet radius of the sealing strip was 3.5 mm,55U silicone rubber material with a shore A hardness of 50 degree was used,and a layer of reinforcement fabric was applied,the sealing performance of the sealing system of cabin door was the best.