摘要
在民用飞机复合材料帽型加筋壁板初步设计时,帽型加筋的夹角影响壁板的初始屈曲载荷大小。本文通过工程算法可快速得到初始屈曲载荷随着帽型加筋夹角的变化趋势,确定最优夹角;分别通过有限元模拟和试验测试验证了工程算法得到的变化趋势和最优夹角的正确性;同时表明工程算法得到的初始屈曲载荷小于试验测试结果,说明工程算法偏保守,可为设计师在初步尺寸设计时提供参考;有限元分析得到的初始屈曲载荷与试验结果较接近,说明有限元分析可作为强度校核的一种手段。
In the preliminary design of CFPR hat-stringer panel for civil aircraft,the angle of hat-stringer affects the initial bucking load of panel.Through engineering method,the trend of initial bucking load with the angle of hat-stringer can be quickly obtained,so as to get the optimal angle.The correctness of the change trend and the optimal angle obtained by the engineering mothod was verified through finite element simulation and experimental testing respectively.Meanwhile,it was shown that the initial bucking load obtained by engineering methods is less than the test results,which indicates that the engineering method is conservative and can provide a reference for designers in the initial size design;the initial bucking load obtained by the finite element analysis is close to the test results,which indicates that the finite element analysis can be used as a means of strength check.
作者
何周理
李旭辉
HE Zhouli;LI Xuhui(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)
出处
《高科技纤维与应用》
2021年第4期32-37,共6页
Hi-Tech Fiber and Application
关键词
复合材料
帽型加筋
初始屈曲
有限元
试验
composite laminates
hat-stringer
initial bucking load
finite element
test
