摘要
当今,使用复合材料补片修复复合材料蒙皮损伤已成为常见做法。然而,目前对损伤位置影响的研究较少,而进行实验研究所需的成本也相对较高。该文利用ABAQUS有限元仿真软件对某型低速飞机的复合材料机翼进行静力学分析,并比较不同位置损伤条件下修复前后的力学性能。结果显示,损伤部位的最大位移与最大应力会随着翼展方向发生变化。此外,贴片修复能有效减少损伤部位承受的应力大小,为复合材料机翼结构损伤修复提供有效手段。
Using composite patch repair to address damage on composite skin is a common practice nowadays.However,there is limited understanding of the influence of damage location,and experimental research on this topic tends to incur relatively high costs.In this study,static analysis of a composite wing of a certain type of low-speed aircraft was conducted using the ABAQUS finite element simulation software.The mechanical performance before and after repair was compared under different damage conditions.The results indicate that the maximum displacement and maximum stress at the damaged area vary with the spanwise direction.Additionally,patch repair can effectively reduce the stress experienced at the damaged area,serving as an effective method for repairing damaged composite wing structures.
出处
《科技创新与应用》
2024年第33期52-55,共4页
Technology Innovation and Application
基金
南京航空航天大学大学生创新创业训练计划项目(202310287097Z)。
