基于失稳疲劳的加筋复合材料层合板设计  

Buckling Fatigue Design for Stiffened Laminated Composite Panels

作　　者：王维阳[1] 李伟[1] 吴江鹏[1] 刘思远[1] 郝欣 Wang Weiyang;Li Wei;Wu Jiangpeng;Liu Siyuan;Hao Xin(AVIC Shenyang Aircraft Design & Research Institute,Shenyang 110035,China)

机构地区：[1]航空工业沈阳飞机设计研究所

出　　处：《航空科学技术》2019年第9期87-91,共5页Aeronautical Science & Technology

摘　　要：本文根据理论分析发现在层合板失稳至出现损伤区间存在一个阶段使得复合材料层合板整体承载呈现线弹性表征阶段的力学行为比较稳定,即使在含有预制损伤情况下仍然具有足够的疲劳安全性能。通过失稳疲劳试验验证了在加筋复合材料层合板失稳线弹性表征阶段48000次循环载荷的测量数据重复性良好且预制损伤未扩展。因此,基于失稳疲劳的加筋复合材料层合板设计可以在保证结构强度设计安全前提下最大限度控制重量指标、发挥材料结构承载能力,满足飞机使用与发展需求。According to the theoretical analysis,it is found that there is a stage between instability and damage of composite panel,which makes composite panel show only geometric nonlinear characterization.The composite panel post-buckling with linear elastic loading characterization is relatively stable,even existing pre-damage.Meanwhile,the buckling fatigue experiments are used to verify the good repeatability of the measurement data,and the pre-fabricated damage is not expanded.Consequently,the technology of the stiffened laminated composite panels design using buckling fatigue influence analysis,can help designers effectively control weight index,make the load-bearing panels work at full capacity,meet the aircraft usage and development requirements.

关 键 词：加筋壁板 复合材料 后屈曲 疲劳强度 仿真分析 

分 类 号：V223[航空宇航科学与技术—飞行器设计]