复合材料夹层结构机身集中载荷传力研究  

Study on Concentrated Load Transfer of Composite Sandwich Fuselage

作　　者：成强 Cheng Qiang(China Aviation Industry General Aircraft Institute Co.,Ltd.,Zhuhai 519090,China)

机构地区：[1]中航通飞研究院有限公司,广东珠海519090

出　　处：《科学技术创新》2022年第7期181-184,共4页Scientific and Technological Innovation

摘　　要：随着复合材料技术的成熟,越来越多的通用飞机主结构使用了低成本复合材料夹层结构。本文通过对复合材料夹层结构机身承受机翼的集中载荷进行了数值分析和试验研究,结果表明无框、无桁的夹层结构通过设计可作为主承力结构传递较大的集中载荷,并分析得出了螺栓连接影响强度的主要因素。With the maturity of composite technology,more and more general aircraft primary structures are made of low-cost composite sandwich structures.In this paper,numerical analysis and experimental study are conducted on the composite sandwich structure fuselage carrying the concentrated load of the wing.The results show that the sandwich structure without frame or truss can be used as the main loading structure to transfer the concentrated load,and the some factors affecting the strength of bolt connection are analyzed.

关 键 词：通用飞机 复合材料 夹层结构 螺栓连接 

分 类 号：V272[航空宇航科学与技术—飞行器设计]