Aerospace series . carbon fibre reinforced plastics . unidirectional laminates . determination of the apparent interlaminar shear strength 航天航空系列.碳纤维增强塑料.单向层压板.表观层间剪切强度的测定
Aerospace series - carbon fibre reinforced plastics - unidirectional laminates - tensile test parallel to the fibre direction ; german version en 2561 : 1995 航空航天系列.碳素纤维增强塑料.单向塑料层压制品.纤
Aerospace series - carbon fibre reinforced plastics - unidirectional laminates ; flexural test parallel to the fibre direction ; german version en 2562 : 1997 航空航天系列.碳纤维增强塑料.单向层压塑料.与纤维方
Aerospace series - carbon fibre reinforced plastics ; unidirectional laminates - tensile test perpendicular to the fibre direction ; german version en 2597 : 1998 航空航天系列.碳纤维增强的塑料.无向叠层材料.垂直纤
Aerospace series - carbon fibre reinforced plastics - unidirectional laminates ; determination of apparent interlaminar shear strength ; german version en 2563 : 1997 航空航天系列.碳纤维增强塑料.单向层压制品.表观层压
High - performance components can be composed of a stack of unidirectional laminates or 2d woven fabric plies arranged in a sequence chosen to optimize the mechanical properties 按照设计好的组分材料以及编织方案进行排列的二维编织复合材料表现出了很高的力学性能。
Based on the concept of a modified fatigue modulus , a cumulative strain damage model , which is able to consider the influence of in - plane multi - axial stresses and mean stress to the fatigue behavior of unidirectional laminates , is proposed 论文各章的主要工作有： ( 1 )以疲劳模量概念为基础，建立累积应变损伤模型。
An losipescu - type of fixture , which had been previously used for the static shear strength tests of unidirectional laminates or metal materials , was proved useful for the shear static and fatigue tests of multidirectional laminates ( 6 )进行mdyb - 3座舱盖有机玻璃撞击损伤剩余强度和疲劳裂纹扩展试验，发现撞击损伤引致的疲劳裂纹的扩展规律与理想的表面裂纹明显不同。
In this research , fatigue life of laminate composite is predicted phenomenologically , dealing mainly with in - plane stresses without accounting for out - of - plane failures such as delamination . fatigue modulus is used as a physical parameter which helps to describe the basic fatigue behaviour of unidirectional laminates and obtain expressions for cumulative damages defined by strains . based on some typical fatigue test data for unidirectional composite laminates , a cumulative fatigue damage model is presented for predicting the fatigue life of multidirectional laminates with arbitrary stacking sequence under complicated fatigue loadings 本文以碳纤维/树脂基t300 / qy8911层压结构为研究对象，从唯象的观点出发，以疲劳模量为参量构造损伤函数，基于几组最典型的单向板疲劳试验数据，建立单向板在多轴循环应力作用下的疲劳寿命模型，并以此为基础，发展同种材料体系的任意铺层形式的多向层压板在复杂循环载荷作用下的疲劳寿命预测方法。
With the typical on - axis fatigue tests to get the relative s - n curves of unidirectional laminates , executed at certain stress ratio , it is possible to predict the fatigue life of multidirectional laminates subjected to cyclic stresses of different stress ratios . this would tremendously reduce test costs for laminate structures 考虑了层压板中单向层面内多轴应力和平均应力的影响，在已知单向板在确定应力比下受典型单轴循环应力的s - n曲线的基础上，预测任意铺叠次序层压结构在不同应力比的循环载荷下的疲劳寿命。
