复合材料机身对接壁板双向拉伸试验研究  

Experimental Research on Biaxial Tensile Test of Composite Fuselage Joint Panel

作　　者：陈昊[1] 柴亚南[1] 李新祥[1] 邹鹏 CHEN Hao;CHAI Ya-nan;LI Xin-xiang;ZOU Peng(Aircraft Strength Research Institute of China,Xi’an 710065,China)

机构地区：[1]中国飞机强度研究所,西安710065

出　　处：《科学技术与工程》2018年第23期329-333,共5页Science Technology and Engineering

摘　　要：为研究复合材料机身环向对接壁板受轴向和环向拉伸载荷下的耐久性/损伤容限问题,设计了一种新型壁板双向拉伸试验装置;可在单轴试验机上实现双向拉伸载荷,提高疲劳试验加载频率,降低试验成本。利用有限元分析和各向同性基准件验证试验两种手段对试验装置的有效性进行了评估,满足工程要求。利用双向拉伸试验装置对复合材料机身环向对接壁板进行了耐久性/损伤容限试验,结果表明,机身环向对接壁板满足静强度要求,由于对接区金属和复合材料混合结构的冲击损伤阻抗较强,在耐久性试验和剩余强度试验后未发生损伤扩展。试验结果为复合材料机身设计提供了一定的依据。In order to study the durability and damage tolerance of composite fuselage circumferential joint panel under axial and hoop tensile load,a new fuselage panel biaxial tensile testing technique was designed,which can realize biaxial tensile loading on the unidirectional testing machine,thus increase frequency of fatigue test and save cost.The testing technique was evaluated by finite element model(FEM)and isotropic benchmark specimen tests to conform to engineering requirement.The durability and damage tolerance tests of composite fuselage circumferential joint panel were conducted using the biaxial tensile testing technique.Test results indicated thses as follows.firstly,the static strength meets the design requirement;secondly,the impact resistance was high because of metallic and composite joint structure;thirdly,initial damage was not propagated after fatigue test and residual test.The results can provide data for design of composite fuselage.

关 键 词：机身壁板 双向拉伸 损伤容限 耐久性 

分 类 号：V216.3[航空宇航科学与技术—航空宇航推进理论与工程]