机身壁板双向拉伸试验技术研究  

Research on Biaxial Tension Test Technology for Fuselage Panel

作　　者：陈昊[1] 柴亚南[1] 李新祥[1] Chen Hao;Chai Yanan;Li Xinxiang(Aircraft Strength Research institute of China, Xi′an 710065, Shaanxi, China)

机构地区：[1]中国飞机强度研究所,陕西西安710065

出　　处：《工程与试验》2018年第4期90-94,共5页Engineering and Test

摘　　要：为了进行机身壁板的双向拉伸试验,设计了一种曲梁及连接构件将单向载荷分解为双向载荷,在单向拉伸试验机上实现了双向拉伸加载的试验,并用理论分析和验证试验两种手段对试验装置的有效性进行了评估。评估结果表明,试验装置的加载误差满足工程要求。该试验装置简单,可实现多种载荷比加载,疲劳加载频率较快。A new type of biaxial tension test technology is invented by designing a curved beam and connectors which can resolve the unidirectional load into biaxial load,so as to achieve the composite fuselage panel biaxial tension tests on the unidirectional testing machine.The validity of new biaxial tension device is evaluated by theoretical analysis and tests,and the result of evaluation shows that the loading error meets engineering requirements.The result of fuselage panel biaxial tension tests shows that the new test technology could simplify the test device,realize multiple biaxial loading ratio and increase fatigue loading frequency.At the same time,it indicates that the fuselage panel meets the requirements of static strength and fatigue strength.

关 键 词：双向拉伸 机身壁板 试验技术 

分 类 号：V216.1[航空宇航科学与技术—航空宇航推进理论与工程]