摘要
通过某型飞机的一组典型试验件的剪切试验获得的相关试验结果,使用正交各向异性矩形层压平板的剪切屈曲载荷计算公式,选用相关计算参数,并将工程理论计算结果与试验结果进行对比。研究结果发现,对文中典型试验件进行理论计算时,板元参数中当蒙皮铺层厚度选择不考虑加筋桁条底脚而取原铺层厚度、宽度选择考虑加筋桁条底脚支撑作用,计算的最终五组结果与试验值绝对误差均最小,并且小于5%。
According to related calculation parameters,this paper compares the buckling critical value calculated by the function for orthotropic composite panel subjected to shear loading with the experimental results of a batch of typical test panels for an airplane program subjected to shear loading. The results show that the original skin lamina thickness considered,the width of the panel related with the stringer foot,four edges simply supported,five theoretical results get fairly well with experimental results,and the absolute error between theoretical result and experimental result is within 5%.
作者
杨俊清
孟庆功
王俊
YANG Junqing;MENG Qinggong;WANG Jun(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China)
出处
《民用飞机设计与研究》
2019年第2期26-30,共5页
Civil Aircraft Design & Research
关键词
复合材料加筋壁板
剪切屈曲
临界载荷
工程计算
stiffened composite panel
shear buckling
critical loading
engineering calculation
