The invention relates to a coaxial dual-rotor helicopter attitude control mechanism, which comprises a rotor structure and a rotor attitude control system, the rotor structure comprises a main shaft, and an upper rotor and a lower rotor mounted on the main shaft, and the rotor attitude control system comprises a differential control mechanism and a rudder direction control mechanism; the differential control mechanism is used for realizing equivalent synchronous change of elevation angles of the upper rotor and the lower rotor, and the rudder direction control mechanism is used for realizing elevation angle change of each layer of rotor at different positions in a rotating surface. The design is fully differential motion body posture adjustment, synchronous elevation angle adjustment of upper and lower propellers can be realized synchronously, and the total lift force of the aircraft is not changed when the direction of the fuselage is adjusted. The two attitude adjusting systems share one rocker arm control system at the tail end, the structure is simplified, the stability is enhanced, and when the system is applied to the coaxial double-rotor helicopter, the attitude adjusting capacity of the helicopter is enhanced, meanwhile, the flight attitude stability can be greatly improved, and meanwhile the control difficulty is lowered.
本发明涉及一种共轴双旋翼直升机姿态控制机构,包括旋翼结构和旋翼姿态控制系统,旋翼结构包括主轴以及安装在主轴上的上旋翼与下旋翼,旋翼姿态控制系统包括差动控制机构与舵向控制机构;差动控制机构用于实现上旋翼与下旋翼两层旋翼仰角的等量同步变化,舵向控制机构用于实现每层旋翼在旋转面内不同位置的仰角变化。其设计为全差动机身姿态调整,可同步实现上下两层桨的同步仰角调节,在做机身方向调整时飞机总升力大小不变。两套姿态调整系统在末端共用一套摇臂控制系统,精简了结构,增强了稳定性,该套系统在共轴双旋翼直升机上的应用不仅加强了直升机姿态调整能力,同时能大幅度提高飞行姿态稳定性,同时也降低了操控难度。
Attitude control mechanism for coaxial double-rotor helicopter
一种共轴双旋翼直升机姿态控制机构
2024-08-23
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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