摘要
针对大展弦比机翼结构的特点,选定蜂窝夹层、多墙式和一种新型混合式结构进行分析比较。进行了缝纫层合板和无缝纫层合板的冲击后压缩强度试验以及3种形式的复合材料蜂窝夹层板冲击后压缩稳定性试验。实验结果表明,缝纫可提高复合材料层合板冲击后压缩强度和屈曲临界载荷。对3种形式机翼结构进行有限元分析,计算结果表明,新型混合式结构具有明显的减重效果,并可实现一定比例的弯曲和扭转刚度设计。
Based on the structural characteristics of high aspect ratio wing, the sandwich, multi-spar structure and an innovative mixed structure are designed and compared. The experimental investigation is made for the compressive strengths after low speed impact of stitched and non-stitched laminates. The compressive test is conducted for three forms of honeycomb sandwich laminates. The experimental result indicats that stitching can enhance the compressive strength after low speed impact and the buckling load of the composite laminate. The finite element analysis method is adopted to compare the mixed structure with the other two structures. The calculation implies that the innovative mixed structure possesses obvious effect of decreasing weight, and that it can meet the requirement of the ratio of the torsional stiffness to bending stiffness.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2005年第4期450-453,共4页
Acta Aeronautica et Astronautica Sinica
基金
凡舟基金(20030503)资助课题
关键词
大展弦比
复合材料
缝纫层合板
蜂窝夹层
扭转刚度
high aspect ratio
composite material
stitched laminate
honeycomb sandwich
torsional stiffness
