发动机舱大开口口盖的结构设计和计算分析

Structural Design and Numerical Analysis of the Composite Cover on the Aircraft Engine Nacelle's Large Opening

飞机发动机舱是飞机结构的重要组成部分,考虑发动机的拆卸、安装通道,以及在日常飞行时,对发动机进行检查和维护的通道,常常需要对发动机舱进行大开口设计。研究大开口口盖的复合材料设计是航空工业发展的一项重要技术,利用复合材料的高比强度、比刚度和优良的耐腐蚀、耐疲劳特性以及可设计性,可以带来良好的减重效果和较高的结构效率。对复合材料夹心结构进行有限数值计算和冲击损伤分析,验证其用发动机舱大开口口盖采用复合材料结构设计的可行性,对以后飞机的大型口盖的结构设计有一定的指导意义。

The aircraft engine nacelle is a important part of an airplane structure. For the engine assembly and disassembly processes, and for the routine engine maintenance, the aircraft engine nacelle is needed to be designed with a large opening. Composite material design of the cover on a large opening is a important technique for aircraft industry development. With high specific strength, high specific rigidity, high corrosion resistance, excellent fatigue property and preferable designability, composite materials were chosen to reduce structural weight and achieve better structural efficiency. Static simulation and impact calculation of the hybrid composite sandwich cover validated the design of structure and material compositions, providing reference for the future design of covers on large openings of aircraft engine nacelles.