六旋翼植保无人机飞行框架的结构设计与试验

为了达到无人机轻量化的要求，以碳纤维材质为机身主体，设计了一套六旋翼植保无人机的飞行框架。基于ANSYS对该框架关键结构部件的刚度和强度进行了静力学分析，根据分析结果，将单层中心固定板改为了双层结构并在机臂之间加入了加强筋。分析表明：优化设计后，无人机中心板形变量降低了104.36倍，最大应力降低了13.15倍，而质量仅增加了1.9%。最后通过实际飞行振动试验，基于LabVIEW对植保无人机机身3个不同位置竖直方向的振动信号进行小波变换降噪处理和时、频域计算评估，振动最大RMS值为1.69 g，小于飞行控制系统振动报警阈值2.5 g，表明其在稳定性和操控能力上具有良好的表现。

Structural design and experiment for six-rotor plant protection UAV flight frame

In order to meet the requirements of lightweight UAV (unmanned aerial vehicle), this paper used carbon fiber material as the main body of the fuselage, and designed a set of six-rotor plant protection UAV flight frame. Based on ANSYS, the rigidity and strength of the key structural components of the frame were statically analyzed. According to the analysis results, the single-layer central fixed plate was changed to a double-layer structure, and stiffeners were added between the rotor arms. The analysis showed that: after optimizing the design, the UAV center plate shape variable was reduced by 104.36 times, and the maximum stress was reduced by 13.15 times, but the mass was only increased by 1.9%. During the actual flight vibration experiment, based on wavelet domain denoise and calculation for vibration signal, time and frequency domain on three different location of flight frame were acquired by LabVIEW. The maximum RMS value of vibration was 1.69 g, which was less than the vibration alarm threshold of flight control system 2.5 g, indicating that it has a good performance in stability and control ability.