摘要
根据纤维曲线铺放的变刚度复合材料层合板层内铺层角度的参考路径制备出铺层顺序分别为[±45/±〈45/60〉2/±〈15/30〉]s和[±45/±〈15/30〉/±〈45/60〉/±〈30/45〉]s的变刚度复合材料层合板,并对该变刚度复合材料层合板在拉伸和弯曲载荷作用下的损伤破坏过程进行了试验研究,获得了该复合材料层合板的损伤破坏演化过程。通过对纤维直线和纤维曲线铺放的复合材料层合板的拉伸和弯曲试验进行对比,结果表明:在拉伸载荷作用下纤维曲线铺放比纤维直线铺放的复合材料层合板的极限载荷和强度提高了49%和42%,在弯曲载荷作用下的极限载荷和强度提高了28%和32%;纤维直线铺放的复合材料层合板的断口破坏较为严重。纤维曲线铺放的变刚度复合材料层合板的结构性能得到了显著提高。
According to the path of variable-stiffness composite laminates layer angle, vaiable-stiffness composite was produced following ply sequence of [ ±45/±（45/60） 2/±（15/30）] s and [±45/± （15/30）/± （45/60）/±（ 30/45 ） ]s.Tension and bending damage failure process experiment have been done for the variable-stiffness composite, and the composite failure evolution was ob- tained.Tension and bending properties of variable-stiffness composite laminates were compared with that of straight fiber laminates. The results show that tension failure load and strength is increased by 49% and 42%, bending failure load and strength is increased by 28% and 32% ;fracture of the composite laminate with straight fiber is seriously damaged. Variable-stiffness composite can improve structure properties significantly.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2013年第6期826-830,共5页
Journal of Solid Rocket Technology
基金
天津市应用基础与前沿技术研究计划重点项目(11JCZDJC23000)
关键词
纤维曲线铺放
变刚度复合材料
极限载荷
强度
试验研究
fiber placement
variable-stiffness composite
ultimate load
strength
experimental research
