对基于平面裁切的乙烯-四氟乙烯（ethylene-tetrafluoroethylene,ETFE）气枕进行充气成形试验,利用激光位移计测量气枕矢高,基于三维摄影测量得到的形状,分析了气枕膜面应力分布。采用Peirce模型模拟ETFE膜材的材料力学非线性并进行相...对基于平面裁切的乙烯-四氟乙烯（ethylene-tetrafluoroethylene,ETFE）气枕进行充气成形试验,利用激光位移计测量气枕矢高,基于三维摄影测量得到的形状,分析了气枕膜面应力分布。采用Peirce模型模拟ETFE膜材的材料力学非线性并进行相同充气过程的数值模拟,对比分析数值模拟与实测的气枕矢高和应力分布。结果表明：Peirce模型仅在反映ETFE两个屈服点之间的应力-应变关系上有所偏差;气枕充气完成后矢高约为172 mm,气枕膜面应力最大值集中于气枕中心与各边中点的连线区域;不同内压下的气枕矢高,膜面应力、应变的数值模拟结果与实测结果相对误差均在10%以内。此外,Peirce模型数值模拟结果表明,内压为2 k Pa时气枕膜面出现塑性应变;膜面总应变与塑性应变最大值集中于气枕中心与各边中点连线区域。展开更多
Many joint models available to predict secondary bending moments in the structure have a stiffness mismatch, while this type of structure widely used in aircraft. To determine how to represent a structure with a stiff...Many joint models available to predict secondary bending moments in the structure have a stiffness mismatch, while this type of structure widely used in aircraft. To determine how to represent a structure with a stiffness mismatch in a combined joint （bonded/riveted）, a non-linear finite element analysis was performed. The detailed validation of this analysis identified the composite stiffened skin as the most suitable model in three dimensions. The use of this model for validating the secondary bending moment to calculate the behavior of the stiffener edge is straightforward and reliable. Experiments were performed to determine the distribution of the load in a combined joint under a tensile load that creates a secondary bending moment in a structure with a stiffness mismatch. The influence of related joint design considerations on the load transferred by the joint were examined through a finite element parameter analysis. The results are compared to determine best approach to predict the mechanical behavior at the edge of the stiffener. A close agreement between the finite element analysis and experimental results was obtained. Test observations using a C-scan compared well with the predictions of the onset of crack growth.展开更多
文摘对基于平面裁切的乙烯-四氟乙烯（ethylene-tetrafluoroethylene,ETFE）气枕进行充气成形试验,利用激光位移计测量气枕矢高,基于三维摄影测量得到的形状,分析了气枕膜面应力分布。采用Peirce模型模拟ETFE膜材的材料力学非线性并进行相同充气过程的数值模拟,对比分析数值模拟与实测的气枕矢高和应力分布。结果表明：Peirce模型仅在反映ETFE两个屈服点之间的应力-应变关系上有所偏差;气枕充气完成后矢高约为172 mm,气枕膜面应力最大值集中于气枕中心与各边中点的连线区域;不同内压下的气枕矢高,膜面应力、应变的数值模拟结果与实测结果相对误差均在10%以内。此外,Peirce模型数值模拟结果表明,内压为2 k Pa时气枕膜面出现塑性应变;膜面总应变与塑性应变最大值集中于气枕中心与各边中点连线区域。
文摘Many joint models available to predict secondary bending moments in the structure have a stiffness mismatch, while this type of structure widely used in aircraft. To determine how to represent a structure with a stiffness mismatch in a combined joint （bonded/riveted）, a non-linear finite element analysis was performed. The detailed validation of this analysis identified the composite stiffened skin as the most suitable model in three dimensions. The use of this model for validating the secondary bending moment to calculate the behavior of the stiffener edge is straightforward and reliable. Experiments were performed to determine the distribution of the load in a combined joint under a tensile load that creates a secondary bending moment in a structure with a stiffness mismatch. The influence of related joint design considerations on the load transferred by the joint were examined through a finite element parameter analysis. The results are compared to determine best approach to predict the mechanical behavior at the edge of the stiffener. A close agreement between the finite element analysis and experimental results was obtained. Test observations using a C-scan compared well with the predictions of the onset of crack growth.
