摘要
复合材料具有比强度高、比刚度高等优良特性,因此被广泛应用于航空航天结构中。但是复合材料结构抗冲击性能差,当结构在制造和使用过程中受到外来冲击后,会造成多种形式的损伤,降低其承载能力。本文采用数值计算和试验相结合的方法,研究铺层顺序对复合材料层合板冲击后剩余压缩强度的影响。计算结果表明,当层合板较薄时,调整铺层顺序对层合板冲击性能的影响很小;随着层合板厚度逐渐增加,调整铺层顺序后,层合板冲击接触力和剩余压缩强度值变化越大;在层合板总厚度和各方向单层比例一定的情况下,将0°层靠近内侧铺设能得到较高的剩余压缩强度值。
Composites are widely used in aerospace structures because of the high specific strength and stiffness characteristics; but the impact resistance of composites structures is poor; it can cause a variety of forms of damage when the structure suffers impact during manufacture and work-and once it happened,the bearing capacity will be reduced heavily. This article adopts the method of combining numerical calculation and experiment to research the effect of the stacking sequence on the residual compressive strength after impact. The results indicate that when laminates are thin,the stacking sequence has little effect; as the thickness of laminates increase,changing the stacking sequence will make the impact contact force and residual compressive strength values change greatly; a higher compressive strength value can be achieved when the zero stacking is in the inner side.
出处
《飞机设计》
2015年第2期5-10,14,共7页
Aircraft Design
关键词
复合材料层合板
铺层顺序
冲击损伤
剩余压缩强度
composite laminates
stacking sequence
impact damage
residual compressive strength
