小型折叠多旋翼无人机的机翼转轴结构设计

Design of Folding Wing Shaft Structure of Small Type Multiple Rotor UAV

对目前市场上的几种小型折叠多旋翼无人机上转轴中的塑料弹性自位结构和蝶簧弹性自位结构进行了分析,指出其结构上存在利用塑料机身、机翼的变形来产生的自位力不足且难以控制、运动副表面间容易磨损、加工精度较差导致无人机运行稳定性欠佳等问题,提出了一种全金属弹性自位轴承结构设计,将其充当飞行器机身和机翼臂的连接桥梁;用金属摩擦副取代塑料摩擦副,用正弦形摩擦面和弹簧结构使自位力大小可控;用模块化设计思想提高制造精度和加工、装配效率。结果表明,采用该设计可以克服上述缺点,充分满足飞行器精确、稳定、长久运行的性能要求,同时还可降低制造成本。

The elastic self position structure of plastic and elastic self-aligning structure of sphenoid spring for some small folding multi rotor UAV are analyzed.It is pointed out that the existing structure using plastic fuselage and wing deformation resulting the elastic force is insufficient and difficult to control.The movement between friction surfaces is easy to wear and the poor machining precision leads to poor stability of UAV.A kind of full metal elastic self-designed bearing structure is put forward,which will serve as a bridge to link aircraft fuselage and wing arm.Taking metal friction instead of plastic friction with sinusoidal friction surface and spring structure makes the self-force controllable.The manufacturing precision,processing efficency and assembly efficiency are improved with the idea of modular design.The results show that this design can overcome these shortcomings,fully meet the performance requirements of precise,stable and long-term operation of aircraft,and also reduce manufacturing costs.