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为研究航天可展结构展开及锁定的动态过程,针对航天工程中广泛应用的微小间隙转动副,提出了一个多点接触碰撞模型及其离散算法。该算法计入了运动副表面波纹、位置误差、轴弯曲变形以及粘滞微滑效应等实际因素。静态接触数值算例与试验结果较为符合。使用不同间隙量,对一端固定的含间隙转动副柔性杆受轴向冲击碰撞的过程进行了动力学仿真。计算结果表明:该模型能描述接触力和变形接近量的非线性关系与滞回特性,模型参数易于获得,便于在结构设计阶段数值仿真中使用。
In order to study the dynamic process of the spacecraft deployable structure and its locking, a multi-point contact collision model and its discrete algorithm are proposed for the micro-gap rotary pair widely used in aerospace engineering. The algorithm takes into account the actual surface ripple, position error, shaft bending deformation and viscous micro-slip effect and other practical factors. The numerical results of static contact are in good agreement with the experimental results. Using different clearances, the dynamic simulation of the axial impact collision of the flexible rod with gap rotating at one end was carried out. The calculation results show that the model can describe the nonlinearity and hysteretic characteristics of contact force and deformation approximation. The model parameters are easy to obtain and can be easily used in the numerical simulation of structural design stage.