共固化成型无人机用复合材料/蜂窝夹层结构面板的性能  

MECHANICAL PROPERTIES OF PANELS OF CO-CURED SANDWICH STRUCTURE

作　　者：赵鹏飞[1] 赵景丽[1] 何颖[1] 

机构地区：[1]西北工业大学第365研究所,西安710072

出　　处：《玻璃钢／复合材料》2009年第1期62-64,共3页Fiber Reinforced Plastics/Composites

摘　　要：针对无人机结构工程设计和工艺方案需要,通过试验比较几种预浸料在共固化成型工艺状态下制备的蜂窝夹层结构面板与在相同固化工艺条件下制备的层压板的力学性能,得出可直接采用共固化工艺制造无人机飞机机体结构的结论。性能结果显示,由所选择的适用于共固化工艺的预浸料所制备的面板与层压板试样的力学性能基本是相当的,但面板的层间剪切强度却明显比层压板的低。Directing to needs about designing UAV＇s airframe and working out technological process, this article compares the mechanical properties of composite laminates and panels of honeycomb sandwich structure made from different kinds of prepregs at the same cure condition. It comes to the conclusion that co-cure technique can be directly used to make honeycomb sandwich structure used for UAV＇s airframe. The results show that mechanical properties are basically about the same, but the shear strength of the panels is lower than the laminates＇ obviously.

关 键 词：无人机 复合材料 共固化 面板 力学性能 

分 类 号：TB332[一般工业技术—材料科学与工程]