飞行器防隔热构件多采用胶粘形式与冷结构连接,在严酷的飞行振动环境中易发生脱粘损伤,有必要利用地面环境试验考核其环境适应性,并在试验后及时判断结构健康状态。本文提出一种基于结构特征级扫描响应谱均方根偏差(Root Mean Square De...飞行器防隔热构件多采用胶粘形式与冷结构连接,在严酷的飞行振动环境中易发生脱粘损伤,有必要利用地面环境试验考核其环境适应性,并在试验后及时判断结构健康状态。本文提出一种基于结构特征级扫描响应谱均方根偏差(Root Mean Square Deviation,RMSD)的损伤定位方法,可得到结构全部区域的损伤概率分布云图,实现结构损伤识别与定位。以一种防隔热材料构件为研究对象,在仿真分析和试验研究中应用该方法对结构的特征级扫描响应谱进行分析,实现了结构脱粘损伤识别与准确定位。展开更多
A shear-lag model is applied to study the stress transfer around a broken fiber within unidirectional fiber-reinforced composites(FRC) subjected to uniaxial tensile loading along the fiber direction.The matrix damage ...A shear-lag model is applied to study the stress transfer around a broken fiber within unidirectional fiber-reinforced composites(FRC) subjected to uniaxial tensile loading along the fiber direction.The matrix damage and interfacial debonding,which are the main failure modes,are considered in the model.The maximum stress criterion with the linear damage evolution theory is used for the matrix.The slipping friction stress is considered in the interfacial debonding region using Coulomb friction theory,in which interfacial clamping stress comes from radial residual stress and mismatch of Poisson's ratios of constituents(fiber and matrix).The stress distributions in the fiber and matrix are obtained by the shear-lag theory added with boundary conditions,which includes force continuity and displacement compatibility constraints in the broken and neighboring intact fibers.The result gives axial stress distribution in fibers and shear stress in the interface and compares the theory reasonably well with the measurement by a polarized light microscope.The relation curves between damage,debonding and ineffective region lengths with external strain loading are obtained.展开更多
文摘飞行器防隔热构件多采用胶粘形式与冷结构连接,在严酷的飞行振动环境中易发生脱粘损伤,有必要利用地面环境试验考核其环境适应性,并在试验后及时判断结构健康状态。本文提出一种基于结构特征级扫描响应谱均方根偏差(Root Mean Square Deviation,RMSD)的损伤定位方法,可得到结构全部区域的损伤概率分布云图,实现结构损伤识别与定位。以一种防隔热材料构件为研究对象,在仿真分析和试验研究中应用该方法对结构的特征级扫描响应谱进行分析,实现了结构脱粘损伤识别与准确定位。
文摘A shear-lag model is applied to study the stress transfer around a broken fiber within unidirectional fiber-reinforced composites(FRC) subjected to uniaxial tensile loading along the fiber direction.The matrix damage and interfacial debonding,which are the main failure modes,are considered in the model.The maximum stress criterion with the linear damage evolution theory is used for the matrix.The slipping friction stress is considered in the interfacial debonding region using Coulomb friction theory,in which interfacial clamping stress comes from radial residual stress and mismatch of Poisson's ratios of constituents(fiber and matrix).The stress distributions in the fiber and matrix are obtained by the shear-lag theory added with boundary conditions,which includes force continuity and displacement compatibility constraints in the broken and neighboring intact fibers.The result gives axial stress distribution in fibers and shear stress in the interface and compares the theory reasonably well with the measurement by a polarized light microscope.The relation curves between damage,debonding and ineffective region lengths with external strain loading are obtained.
