| 1. | ( 2 ) a stacking sequence optimization ( sso ) method of composite laminates based on ga is suggested in lower level optimization of hdo
( 2 )提出了基于ga的复合材料层合板叠层顺序优化设计( stackingsequeneeoptimization ，简称550 )方法，用于hno的底层优化设计。 |
| 2. | The influences played by temperature rise , the degree of moisture concentration , fiber volume fraction , shell geometric parameter , total number of plies , stacking sequences and initial geometric imperfections are studied
讨论了温度和湿度，纤维体积比率，壳体几何参数，铺层数，铺层方式和初始几何缺陷等各种参数变化的影响。 |
| 3. | The ultimate strength of cf / ep quasi - isotropic laminates with different stacking sequences is experimentally and numerically investigated to study the influence of stacking structure or loading direction on the strength
摘要以碳纤维环氧树脂层合板为对象，研究了其最终强度与层合结构的关系，对于准各向同性层合板，其弹性性能不随方向变化。 |
| 4. | A three layered magneto - electro - elastic half - space subjected to vertical mechanical loads , charge or magnetomotive force is analyzed as the numerical example , and the calculative results of two different stacking sequences are compared
以在垂直机械载荷或电载荷或磁感应强度作用下三层半无限压电压磁弹性体为算例，并比较了两种不同材料叠放顺序的计算结果。 |
| 5. | Though this approach is reasonable and robust for that specific design , however , it is time consuming , costly and needs to be repeated for designs when structural component has different stacking sequences or subject to different fatigue loading
层压板的疲劳损伤包括纤维断裂、基体破坏和分层等破坏形式，这些形式的破坏可能同时发生，相互影响，表现出十分复杂的疲劳损伤机理。 |
| 6. | In this paper , the residual strength of damaged composite laminates and their repaired structures under unidirectional tensile stress is calculated . the influence of the repair parameters , such as the diameter of the circle patch , the length and the width of the rectangle patch , the thickness of the patch , the stacking sequence is discussed
本文对含损伤复合材料层压板及其修补结构在单向拉伸载荷作用下的剩余强度进行了计算，同时对补片参数对修补效果的影响做了一些研究和探讨，主要做了以下几个方面的工作： 1 |
| 7. | The residual strength of damaged composite laminates and their repaired structures are calculated , and the influence of the repair parameters is discussed by the finite element and program stated above . some useful conclusion can be drawn according to the curves , which show the influence of repair parameters to repair effect . for the laminate which contains a circle hole , the suggested patch shape is circle , the patch size is 2 to 3 times than the diameter of damaged hole , the patch thickness is equal to the parent laminate and the patch stacking sequence is the same as the parent laminate
用所建立的二维有限元模型和编写的有限元程序计算损伤板及其修补结构的剩余强度，并分析了修补参数对修补效果的影响；根据本文计算得到的修补参数对修补效果的影响曲线，可以得到如下结论： ?对于含孔复合材料层压板，当圆形补片与母板铺排顺序相同、直径为损伤孔直径2 3倍、相对厚度为100时能够获得比较好的修补效果。 |
| 8. | Simply supported and multilayered electro - elastic plates : using the theories of simply supported and multilayered magneto - electro - elastic plates , without considering the magneto effect , we can easily get the general solution formulation of simply supported and multilayered electro - elastic plates . four - layered electro - elastic plates with two stacking sequences under a mechanical load or charge are analyzed
对于简支压电弹性层合板问题，根据简支压电压磁弹性层合板问题的理论推导，不考虑其磁耦合效应，令相关系数为零，即可得到多层压电弹性层合板状态变量的表达式。 |
| 9. | In upper level optimization , the thickness and geometry factors of composite skins and webs as well as other structural dimensions are taken as design variables . then , considering the behavior constraints and the side constraints , the structural mass is minimized by the mathematical programming technique . in lower level optimization , the mathematical programming technique or the genetic algorithm ( ga ) is used to search the practical stacking sequence of composite skins and webs to realize the given thickness and geometry factors from upper level optimization
底层优化设西北工业大学博士学位论文计以复合材料蒙皮和腹板等层合板各分层的厚度(或铺层数) 、铺层角和铺层顺序为设计变量，以层合板的几何因子与顶层优化设计给出的最优几何因子之间的误差最小为目标，考虑层合板厚度和制造工艺性约束，采用数学规划方法或遗传算法( geneticalgorithm ，简称ga )求出底层最优设计变量。 |
| 10. | 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。 |
