大展弦比混杂纤维复合材料机翼的强度及失效分析  

Strength and failure analysis of hybrid fiber composite wings with high aspect ratio

作　　者：张升 刘菊蓉[1,2] 杨哲 王军利 王康杰[1] 王佳欢 ZHANG Sheng;LIU Jurong;YANG Zhe;WANG Junli;WANG Kangjie;WANG Jiahuan(School of Mechanical Engineering,Shaanxi University of Technology,Hanzhong 723001,China;Shaanxi Key Laboratory of Industrial Automation,Hanzhong 723001,China;Shaanxi Tianxingjian Internet of Vehicles Information Technology Co.Ltd.,Xi'an 710200,China)

机构地区：[1]陕西理工大学机械工程学院,陕西汉中723001 [2]陕西省工业自动化重点实验室,陕西汉中723001 [3]陕西天行健车联网信息技术有限公司,陕西西安710200

出　　处：《兵器材料科学与工程》2024年第4期113-120,共8页Ordnance Material Science and Engineering

基　　金：陕西省重点研发计划项目(2023-YBGY-385);陕西省自然科学基础研究计划项目(2023-JC-YB-018);陕西理工大学2023年校级创新基金项目(SLGYCX2313);陕西理工大学机械工程学院2024年研究生创新基金项目(SLGJX202402)。

摘　　要：以大展弦比机翼为研究对象,基于经典层合板理论和Tsai-Wu失效准则,考虑几何非线性效应,用流固耦合数值模拟方法,重点研究碳/玻纤维混杂比、铺层相对位置、铺层角度对机翼强度及失效特性的影响。研究表明:碳/玻纤维混杂比=8∶2为最佳纤维混杂比,机翼可兼顾高强度、低成本;玻璃纤维铺设在蒙皮对称中面位置时,机翼的强度及安全性更高,玻璃纤维铺设位置的变化不会对机翼的弹性变形产生显著影响;在不同混杂比下,以±45°铺层角度铺设的机翼整体力学性能更稳定,失效概率更低。Based on the classical laminate theory and Tsai⁃Wu failure criterion,the effects of carbon/glass fiber hybrid ratio,relative position of layering and layering angle on the strength and failure characteristics of high aspect ratio wings were studied by fluid⁃structure coupling numerical simulation method.The results show that the best fiber hybrid ratio of carbon/glass fiber is 8∶2,and the wings can take into account both high strength and low cost.The strength and safety of the wing are higher when the glass fiber is laid in the middle plane of the skin symmetry,and the change of the glass fiber laying position does not have a significant effect on the elastic deformation of the wing.Under different hybrid ratios,the overall mechanical properties of the wings laid at±45°bedding angle are more stable and the failure probability is lower.

关 键 词：大展弦比 几何非线性 碳/玻纤维 混杂复合材料 失效分析 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]