机翼盒段静态破坏试验夹具补强的数值模拟

Numerical Simulation on Clamping Fixture of Composite Wing Box in Static Broken Test

针对复合材料中厚蒙皮机翼盒段静态弯曲破坏试验中盒段加载部分遭到破坏试验无法进行的问题,运用Abaqus对盒段局部破坏部分建立三维有限元模型进行应力分析。结果表明:盒段加载部分刚度分配不均,致使外力在加载螺栓中分布不均,导致结构加载部分局部应力集中造成强度不足引起破坏。重新优化设计夹具并对盒段加载部分提出了三种补强试验装置的设计方案,根据应力分析和对比,确定了最终的补强试验装置。补强后的盒段顺利通过了试验,解决了工程难题。

Aiming to the problem of the broken of the load part of wing box in the static bending experiment,which was used in the thick skin,the stress was ananlyzed by 3D-finite element model which was established by Abaqus.The results show that the non-uniform distributed pin load which is caused by non uniform rigidity distribution of the broken structure leads to the stress concentration,the stress concentration makes the structure damage.Three remedial treatments for the new clamping fixture is presented.According to the contrast of the contours of Mises stress,the final improved clamping fixture is confirmed.The improved clamping fixture can pass the test,solving the problems in engineering.