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利用有限元软件建立了某型飞机复合材料-金属连接结构件模型,以改进的Camanho损伤退化模型作为失效判定准则,模拟了该连接结构件的拉伸性能和损伤累积过程并进行了试验验证。结果表明:在加装防弯夹具后,复合材料-金属连接结构件的拉伸试验结果更加准确,拉伸破坏模式由拉脱破坏变为挤压破坏;在较小的拉伸载荷下,其应变随载荷的增加呈线性增大,在金属上的应变明显大于复合材料层合板上的;损伤从复合材料和金属连接螺栓处产生,随载荷的增大逐渐累积并沿螺栓挤压方向扩展;模拟得到的最终破坏载荷为90kN,与试验值的相对误差仅为6.5%,证明了模拟结果的准确性。
A finite element software was used to establish a composite model of the aircraft-metal link structure. The improved Camanho damage degradation model was used as a failure criteria to simulate the tensile properties and damage accumulation process of the aircraft. The experimental verification was carried out. The results show that the tensile test results of the composite-metal connection structure are more accurate after the anti-bending fixture is installed, and the tensile failure mode changes from pull-off failure to extrusion failure. Under the small tensile load, The strain increases linearly with the increase of load, and the strain on the metal is obviously greater than that of the composite laminates. The damage is generated from the composite material and the metal connecting bolt, and gradually accumulates with the load increase and expands along the direction of bolt extrusion. The final failure load obtained by simulation is 90 kN, which is only 6.5% relative to the experimental value, which proves the accuracy of the simulation results.