摘要
针对机翼典型开口加筋壁板,利用有限元弧长法对典型机翼载荷下的开口加筋壁板进行后屈曲分析,同时结合试验应变数据,进行开口壁板的承载能力和破坏模式研究。结果表明:开口边缘壁板应变水平很高;与长桁相比,壁板应变水平较高且分布均匀;从开口两侧至梁附近,长桁承受的载荷逐渐增大;开口两侧长桁最先发生屈曲,然后向外侧长桁扩展,直至壁板破坏。最后将分析与试验结果进行对比,分析得到的破坏载荷与试验破坏载荷误差在5.1%,分析得到的应变曲线与试验值基本吻合,验证了有限元分析方法的正确性。
Aiming at stiffened panel of wing with typical opening, the post-buckling analysis with typical wing load is carried out by the finite element arc-length method. The carrying capacity and failure modes of stiffened panels with typical opening were explored by analysis and experiments. The results reveal that strain is very high in the neighborhood of the opening and the high strain in skin especially. The load acting on stringers increases from the opening to the spar. Because of weak support, the buckling appears near opening strings first, then expands around finally leads to stiffened panel failure. Comparing the analysis with the test, the error of failure load between them is 5.1%, and the strain curve obtained by analysis agrees with the test, which verifies the correctness of the analysis method in this paper.
出处
《强度与环境》
2016年第3期9-16,共8页
Structure & Environment Engineering
基金
中国航空工业集团创新基金(2014A62340)
国际合作项目(2011DFA72840)
关键词
开口
加筋壁板
后屈曲
弧长法
承载能力
large opening
stiffened panel
post-buckling
arc-length method
carrying capacity
