机身加筋壁板环向裂纹损伤容限试验与分析

机身壁板是飞机结构中的主要承力构件,也是损伤的主要产生部位,研究机身加筋壁板的裂纹扩展规律和剩余强度特性具有重要意义。在轴向拉伸载荷作用下,对含环向裂纹的机身加筋壁板进行损伤容限试验;利用ANSYS有限元软件对试验件进行应力强度因子分析,估算裂纹扩展寿命;基于线弹性断裂力学准则和线弹性断裂力学加塑性修正准则,计算剩余强度特征曲线,并对比分析计算结果和试验结果。结果表明:计算得到的裂纹扩展寿命与试验结果的相对误差为6.3%,满足工程要求;线弹性断裂力学加塑性修正准则估算的剩余强度更为合理,误差仅为2.6%,且偏安全。

Damage Tolerance Test and Analysis of Stiffened Fuselage Panel with Circumferential Crack

Experimental study on a stiffened fuselage panel with circumferential crack subjected to axial tension load was presented. The performance of the crack growth and characteristic of the residual strength for fuselage panel were investigated by damage tolerance experiment. Stress intensity factors (SIF) of experimental structure were analyzed by using ANSYS software. The crack propagation life was evaluated. The residual strength curves were calculated based on the linear elastic fracture mechanics and linear elastic fracture criterion modified by yield correction, respectively. The research indicates analysis results agree well with the crack propagation test data. The relative error is 6.3%, and the calculation accuracy satisfies the requirement of engineering. The estimation results using linear elastic fracture criterion modified by yield correction is more reasonable than using linear elastic fracture mechanics. The relative error is 2.6%.