摘要
在某型飞机疲劳关键部位全尺寸盒段损伤容限试验过程中,综合利用声发射技术及常规检查方法,监测裂纹的萌生及扩展。利用有限元数值模拟技术模拟裂纹扩展速率,结合损伤监测情况,确定合理的裂纹检查周期,确保试验获得准确有效的试验数据。通过数值模拟及试验验证证明了声发射监测技术在损伤容限试验中的有效性。
In quasi-full-size box segment damage tolerance test of certain aircraft fatigue critical parts, acoustic emission technology and conventional inspection methods can be taken advantage of to monitor crack initiation and propagation. Finite element simulation technology can be used to simu- late the crack growth rate, combined with damage monitoring to determine a reasonable crack inspec- tion cycle so as to ensure accurate test valid test date. Numerical simulation and experimental verifi- cation,proves the effectiveness of the monitoring of acoustic emission technology in damage toler- ance test.
出处
《飞机设计》
2017年第1期28-30,63,共4页
Aircraft Design
关键词
损伤监测
声发射
损伤容限
裂纹扩展
damage identification
acoustic emission
damage tolerance
crack propagation