摘要
主要对带孔复合材料板和螺栓连接复合材料板的三维应力进行计算分析。通过计算分析发现 ,带孔复合材料板在受单向拉伸时 ,在相同载荷 (面应力 )作用下 ,复合材料板的厚度对板的强度影响不大 ,随着厚度的增加 ,板上最大应力值变化不大 ;对于带孔板而言 ,孔的形状对孔周边应力集中程度影响比较大 ,孔为椭圆孔 ,并且长轴方向与载荷方向平行时 ,孔边应力集中程度比较小 ;而当椭圆的短轴与载荷方向平行时 ,应力集中程度最大 ;孔为圆孔时 ,应力集中程度介于上面两种形状之间。对于多孔复合材料板计算发现 ,多孔板在受拉作用下 ,各个孔周围应力分布与孔的位置有关 ,在距离板边沿越近的孔 ,其周围最大等效应力值越大 ;对螺栓连接板而言 ,螺栓的材料参数对板的应力分布影响不大 ,板上最大应力都位于孔的右端稍偏下位置 ;螺栓连接复合材料板在相同的载荷作用下 。
A three-dimensional stress analysis of drilled and bolt-jointed composite laminates is presented.The analysis shows the following important points.When a drilled composite laminate is unidirectionally tensed or compressed,the laminate thickness has a certain influence on the stress distribution along the periphery of hole.As the laminate thickness is increased,the maximum stress on the periphery of hole is raised.For composite laminates with holes,the hole shape has a relative large influence on the degree of stress concentration on the periphery of hole.For composite laminates with an elliptical hole, a load parallel to the major axis produces a small degree of stress concentration,whereas a load parallel to the minor axis results in the maximun stress concentration.For laminates with a round hole,the degree of stress concentration is between the two above cases.It is found out of the analysis of composite laminates with multiple hole that under the actin of tensile load on the laminates,the stress distribution along the periphery of hole depends upon the location of hole,the maximum periphery equivalent stress being greater for a hole closer to the edge of laminate.For bolt-jointed composite laminates,bolt materials have a little effect on the stress distribution on the laminates,and the maximum stress is on the right end of the hole in the lower portion.The maximum equivalent stress on the bolt-jointed laminates increases with the elastic modulus for a given load.
出处
《飞机设计》
2003年第4期24-28,共5页
Aircraft Design
基金
国家自然科学基金 (5 0 0 5 0 16)
航空科学基金 (0 2C5 3 0 11)
航天支撑基金(0 3B5 3 0 0 3 )
留学回国人员基金资助项目
