摘要
采用试验、工程算法及有限元方法研究了复合材料加筋板剪切性能。首先进行了剪切试验,试验结果表明:加筋板失效模式为筋条脱粘、蒙皮局部破损,加筋板的破坏载荷是屈曲载荷的1. 14倍。然后,对工程算法进行修正,提出了一种计算屈曲载荷的快速分析方法;工程算法得到的屈曲载荷相对误差为3. 53%。最后,建立了有限元模型,模型考虑了试验件与夹具的连接;通过有限元方法得到的屈曲载荷、屈曲模态及破坏模式与试验结果一致;与试验相比,屈曲载荷、破坏载荷的相对误差分别为2. 21%、14. 4%。
The shear properties of composite stiffened panels were studied by experiments,engineering algorithms and finite element method( FEM). Firstly,shear test was carried out. The results show that the failure modes of stiffened panels are ribs debonding and skin damage,and the failure load of stiffened panels is 1. 14 times of buckling load. Then,the engineering algorithm was corrected and a fast analysis method for calculating the buckling load was proposed. The relative error of the buckling load obtained by this method is 3. 53%. Finally,a finite element model was established,which taken into account the connection between the panel and the fixture.The buckling load,buckling mode and failure mode obtained by the finite element method are consistent with the test. Compared with the test,the relative errors of buckling load and failure load are 2. 21% and 14. 4% respectively.
作者
杨钧超
柴亚南
陈向明
邓凡臣
孙茜
YANG Jun-chao;CHAI Ya-nan;CHEN Xiang-ming;DENG Fan-chen;SUN Qian(Aeronautics Science and Technology Key Laboratory of Full Scale Aircraft Structure and Fatigue,Aircraft Strength Research Institute of China,Xi'an 710065,China;Shenyang Aircraft Design&Research Institute,Shenyang 110035,China)
出处
《科学技术与工程》
北大核心
2019年第7期289-293,共5页
Science Technology and Engineering
基金
工信部民机科研项目(MJ-2015-F-038)资助
关键词
复合材料加筋板
剪切
屈曲
后屈曲
失效模式
composite stiffened panels
shear
buckling
post-buckling
failure mode
