直升机机身下部复合材料典型结构耐坠特性研究  

ANALYSIS OF CRASH IMPACT BEHAVIOUR OF TYPICAL COMPOSITE COMPONENTS OF HELICOPT ER BOTTOM STRUCTURE

作　　者：倪先平[1] 王永亮[1] 荚淑萍[2] 王鑫伟[1] 许希武[1] 饶浩东[2] 

机构地区：[1]南京航空航天大学,南京210016 [2]中国直升机设计研究所,景德镇333001

出　　处：《复合材料学报》2003年第4期51-57,共7页Acta Materiae Compositae Sinica

摘　　要：　抗坠性能是武装直升机的一项重要要求,设计具有较高抗坠吸能性能的机身下部结构是实现直升机抗坠要求的主要技术途径。研究了多种形式的复合材料结构元件抗坠特性,在元件研究基础上优化选择复合材料波纹梁和厚蜂窝结构组合,提出了一种新颖的具有较高抗坠吸能性能的复合材料组件形式,并利用有限元理论及试验的方法进行了对比研究分析,计算结果和试验结果吻合较好。The anti-crash characteristics are an important requirement of armed helicopters. It is a main technical measure that the bottom fuselage structure possesses high impact energy-absorbing capability. The study of crash impact behavior of typical composite structure components is carried out for the first time in China in this paper. Based on the components study, an optimum new structural assembly of combining composite wave beams and thick honeycomb elements is put forward, which possesses high impact energy-absorbing capability. Theoretical calculating and testing are combined to do this research work. The validation and the effectiveness of theoretical calculating are demonstrated by the results of tests. Also, the study result in this paper has been applied to the practical design of helicopter structures.

关 键 词：复合材料 波纹梁 厚蜂窝 抗坠结构 

分 类 号：TB330.1[一般工业技术—材料科学与工程]