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针对飞机球面框型材为异形截面的几何特点,基于有限元分析软件Abaqus建立了等效填充离散芯模拉弯成形的有限元模型,通过合理定义边界条件及填充芯模的材料模型,提高了建模效率。根据拉弯过程型材截面弯曲中性层位置不变的假设,建立了夹钳轨迹计算模型,采用位移控制模式对飞机球面框型材拉弯回弹进行了有限元模拟,通过改变中性层位置调整有限元模拟的夹钳轨迹,模拟的回弹结果与实验结果一致,验证了建模方法的有效性。
Aiming at the geometrical characteristics of the profiled section of aircraft spherical frame, Abequs finite element analysis software was used to establish a finite element model of equivalent filling discrete core model. By reasonably defining the boundary conditions and filling the core model, Mode efficiency. According to the assumption that the bending neutral layer position is constant during the bending process, the trajectory calculation model of the clamp is established. The displacement control mode is used to simulate the bending and springing of aircraft spherical frame. By changing the position of the neutral layer, The trajectory of the clamp in the finite element simulation and the simulation of the springback result are consistent with the experimental results, which verify the effectiveness of the modeling method.