The invention belongs to the technical field of unmanned aerial vehicle structure design and motion control, and particularly relates to a missile-borne coaxial unmanned aerial vehicle which comprises a vehicle body, an upper foldable vehicle head and a lower foldable vehicle head. The fuselage comprises an unmanned aerial vehicle shell, an upper material bin, a lower material bin and avionics equipment; the foldable machine head comprises power equipment, a folding component, a steering engine, an inner fixing seat and an outer fixing seat. Through the unique folding mechanism design, the coaxial unmanned aerial vehicle attitude control method is changed from hardware, and the folding pieces of the two steering engines replace swashplates of the three steering engines to achieve control decoupling of the rotor wing system; the hardware cost is reduced by reducing the number of steering engines, meanwhile, the design of the folding mechanism is different from the attitude control principle of a conventional coaxial unmanned aerial vehicle, the unmanned aerial vehicle is integrally tightened to meet the missile-borne mechanical configuration which cannot be met by a conventional unmanned aerial vehicle, and the folding mechanism has creative significance.
本发明属于无人机结构设计和运动控制技术领域,具体涉及一种弹载型共轴式无人机,包括机身以及上下两个可折叠式机头;机身包括无人机外壳、上物料仓、下物料仓和航电设备;可折叠式机头包括动力设备、折叠构件、舵机、内固定座和外固定座。本发明通过独特的折叠机构设计,从硬件上改变了共轴式无人机姿态控制方法,两个个舵机的折叠件代替三个舵机的倾斜盘实现旋翼系统的控制解耦;通过减少舵机数量缩减了硬件成本,同时该折叠机构的设计不同于以往的共轴式无人机的姿态控制原理,满足将无人机整体收紧使其满足常规无人机无法满足的作为弹载的机械构型,具有开创性的意义。
Missile-borne coaxial unmanned aerial vehicle
一种弹载型共轴式无人机
2024-02-06
Patent
Electronic Resource
Chinese
IPC: | B64U |