The high-precision modeling and collision simulation of UAVs should be conducted to achieve the dynamic response of UAV and assess UAV safety. In this paper, a high-precision finite element model of small rotor logistics UAVs on the market was built in LS-DYNA. The process to model the connection structure between a range of parts of a UAV was elucidated in detail. The bolt, damping spring and rivet & thread were respectively simulated with “NRB + beam”, “NRB + discrete” and “spot weld”. By a series of static and dynamic material tests, the constitutive parameters of main materials of UAV structure were determined. Besides, a reasonable explicit time step was set by regulating the mass scaling of local elements. To verify whether the finite element model of UAV is accurate, UAV underwent a developed full-scale crash test. As revealed from the experimentally achieved results, the trend of impact load over time in collision simulation significantly complied with the experimentally achieved results, and the discrepancy between the maximum impact load peak and the experimentally achieved results only took up 6.54%. Moreover, the vital damaged parts, damaging process and failure mode of the UAV structure in the crash test were accurately characterized in the collision simulation. Thus, the UAV modeling and collision simulation was verified to exhibit feasibility. Lastly, with the verified UAV high-precision model, the impacting process, possible damaged parts and failure modes of UAV at the variety of angles and speeds were assessed. Accordingly, the proposed high-precision modeling and collision simulation of small rotor UAV is capable of saving the physical and time resources of UAV structural strength experiments, as well as effectively assessing the structural safety and improving the design of small rotor UAVs.

应进行无人机高精度建模和碰撞仿真，以实现无人机的动态响应和评估无人机的安全性。本文利用LS-DYNA建立了市场上小型旋翼物流无人机的高精度有限元模型。详细阐述了对无人机的一系列部件之间的连接结构进行建模的过程。螺栓、阻尼弹簧和铆钉螺纹分别用“NRB+梁”、“NRB+离散”和“点焊”模拟。通过一系列静态和动态材料试验，确定了无人机结构主要材料的本构参数。此外，通过调节局部元素的质量缩放来设置合理的显式时间步长。为验证无人机有限元模型是否准确，无人机进行了研制的全尺寸碰撞试验。实验结果表明，碰撞模拟中冲击载荷随时间的变化趋势与实验结果明显吻合，最大冲击载荷峰值与实验结果的差异仅占6.54%。此外，在碰撞模拟中准确表征了无人机结构在碰撞试验中的重要损坏部位、损坏过程和失效模式。因此，验证了无人机建模和碰撞模拟的可行性。最后，利用经过验证的无人机高精度模型，评估了无人机在各种角度和速度下的撞击过程、可能损坏的部件和故障模式。因此，