CAJ | 학술논문

对 T700/QY8911缝合复合材料层合板进行了静载拉伸试验和拉-拉疲劳试验，研究了不同缝合方向[0/90]4s 和[0/45/90/-45]2 s 铺层层合板的拉伸和疲劳性能；建立了 T700/QY8911缝合复合材料层合板有限元模型并对其弹性模量进行了模拟。结果表明：缝合能明显提高复合材料层合板抵抗分层破坏的能力；缝合层合板在静拉伸载荷下呈线弹性材料的特点，当载荷达到峰值时，缝合层合板具有后续承载能力，而未缝合层合板在峰值后承载能力出现连续下滑，并发生最终破坏；缝合层合板在拉-拉载荷下的疲劳刚度衰减曲线呈三阶段函数特征；缝合层合板的纵向弹性模量的有限元计算结果与试验结果吻合较好，证实了模型的有效性。
대 T700/QY8911봉합복합재료층합판진행료정재랍신시험화랍-랍피로시험，연구료불동봉합방향[0/90]4s 화[0/45/90/-45]2 s 포층층합판적랍신화피로성능；건립료 T700/QY8911봉합복합재료층합판유한원모형병대기탄성모량진행료모의。결과표명：봉합능명현제고복합재료층합판저항분층파배적능력；봉합층합판재정랍신재하하정선탄성재료적특점，당재하체도봉치시，봉합층합판구유후속승재능력，이미봉합층합판재봉치후승재능력출현련속하활，병발생최종파배；봉합층합판재랍-랍재하하적피로강도쇠감곡선정삼계단함수특정；봉합층합판적종향탄성모량적유한원계산결과여시험결과문합교호，증실료모형적유효성。
The static tensile test and tension-tension fatigue test of T700/QY891 1 stitched composite laminate were conducted,and the tensile and fatigue property of ply [0/90 ]4s and [0/45/90/-45 ]2 s composite laminates at different stitching orientations were studied.The finite element model of T700/QY891 1 stitched composite laminate was established to simulate the elastic modulus.The results show that stitching can significantly improve anti-delamination property of the composite laminates,and the stitched composite laminates under static tensile load showed the characteristics of linear elastic material.The stitched composite laminate had subsequent carrying capacity when the peak load was reached,while the carrying capacity of non-stitched laminates consecutively declined until final destruction.The stiffness degradation curves of stitched composite laminates under the tension-tension fatigue load presented the characteristics of three stages function features.The finite element calculated results of the longitudinal elastic modulus of the stitched composite laminate agreed well with the experimental results,which confirmed the validity of the model.