共固化复合材料/铝蜂窝夹层结构性能  

Properties of Co-Curing Composite Panel/Aluminium Honeycomb Sandwich Structure

作　　者：潘玲英[1] 孙宏杰[1] 尹亮[1] 林娜[1] 杨智勇[1] 

机构地区：[1]航天材料及工艺研究所,北京100076

出　　处：《宇航材料工艺》2012年第4期55-57,共3页Aerospace Materials & Technology

摘　　要：采用共固化工艺制备了碳纤维增强复合材料面板/铝蜂窝夹层结构。通过考察固化压力对复合材料面板性能的影响确定了共固化的成型压力,对比分析了不同规格铝蜂窝及其夹层结构的力学性能。结果表明,对于薄面板,成型压力对面板力学性能的影响较小,规格为0.04 mm×4 mm的铝蜂窝制备的夹层结构具有更高的比强度和比刚度,且成型工艺性好。Composite panel/aluminium sandwich structure was fabricated by the co-curing process. The effect of processing pressure on the properties of composite panel was investigated to determine the co-curing pressure. The properties of aluminium honeycomb with different dimension parameter and their sandwich structures were also tested and analyzed. The results show that the processing pressure has little effect on the properties of thin composite panel. The sandwich structure fabricated by the aluminium honeycomb of 0.04 min×4 mm has high specific strength and modulus, and is easier to fabricate. Therefore, it has more widely potential applications.

关 键 词：共固化 复合材料 铝蜂窝 夹层结构 性能 

分 类 号：V467[航空宇航科学与技术—航空宇航制造工程]