旋翼复合材料桨叶弹损穿孔的有限元建模方法  

FINITE ELEMENT MODLEING METHOD OF COMPOSITE ROTOR BLADE WITH BALLISTIC PERFORATION

作　　者：孙中涛[1,2] 王华明 

机构地区：[1]南京航空航天大学无人机研究院,南京210016 [2]直升机旋翼动力学国防科技重点实验室,南京210016

出　　处：《玻璃钢／复合材料》2013年第1期40-43,共4页Fiber Reinforced Plastics/Composites

基　　金：直升机旋翼动力学重点实验室基金资助项目(9140C400202100C40)

摘　　要：军用直升机旋翼桨叶具有抗弹击设计要求。根据复合材料桨叶的结构特点和工作特性,提出了建立复合材料桨叶弹击穿孔有限元模型的等截面节点移除法,该建模方法先采用等截面拉伸建立桨叶典型结构段的三维模型,然后将弹孔处的节点移除以模拟桨叶的弹损状况。所建立的桨叶弹损模型具有较高的置信度和可接受的解算规模,可作为进一步研究复合材料桨叶抗弹击性能的基础。The military helicopter rotor blade has design requirement of sustaining some kind of ballistic damage. According to the structural properties and operating characteristics of composite blades, this article provides an even cross-section and node removed method to build finite elements model of composite blade with ballistic perforation. This modeling method builds three-dimensional model of blade typical section by even cross-section tension, then nodes around bullet holes are removed to simulate ballistic damage of the blade. The model of ballistic blade built in this article has a high degree of confidence and an acceptable solver scale, it can be used for further research of composite blade＇s performance of resisting ballistic damage.

关 键 词：有限元素法 复合材料 旋翼桨叶 弹损穿孔 等截面节点移除法 

分 类 号：TB332[一般工业技术—材料科学与工程] TP391.7[自动化与计算机技术—计算机应用技术]