Helicopter rotor wing operating device and rotor wing device

Abstract

The invention discloses a helicopter rotor wing operating device. The helicopter rotor wing operating device comprises a steering engine drive subassembly, a swash plate subassembly and a total torqueslide bar subassembly, wherein the steering engine drive subassembly comprises three linear steering engines having tail ends rotatably connected with an engine body, and three L-shaped operating arms which are correspondingly disposed with the linear steering engines and whose one ends are hinged with output ends of the linear steering engines and middle parts are rotatably connected with the engine body; the swash plate subassembly includes a swash plate and a swash plate rotating shaft sleeved in the swash plate; swash plate support arms are respectively installed in the traverse rolling direction and the pitching direction of the swash plate and are hinged with the other ends of the L-shaped operating arms; the total torque slide bar subassembly includes a central joint bearing disposed at the lower end of a total torque slide bar and a side joint bearing correspondingly disposed at the lower end of a long pull rod; a ball joint of the center joint bearing and the side joint bearing is fixedly connected with the swash plate rotating shaft through a traverse connecting rod. The self-stability and safety of an unmanned helicopter can be improved.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a helicopter rotor control device and a rotor device. Background technique [0002] UAV flight control system, including multi-rotor UAV flight control system and fixed-wing unmanned helicopter flight control system. It is mainly used in the field of plant protection, power line inspection, geographical survey, logistics and transportation and other fields. A complete set of controls for unmanned helicopter flight. Including total moment, longitudinal, lateral and heading four control systems. The total moment control system can change the size of the rotor pull to control the helicopter's ascent and descent. The longitudinal and lateral control system can change the direction of the rotor pulling force in space to control the longitudinal and lateral displacement, pitch and roll motion of the helicopter. The heading control system can change the ...

AI Technical Summary

Problems solved by technology

[0003] First, small unmanned helicopters are limited by the rotor space, and most of them adopt the off-axis control method, which will cause the disadvantages of complex external structure, large system weight, low force transmission efficiency, etc. Big

[0004] Second, the swash plate of traditional unmanned helicopters with periodic variable pitch has a complex structure, generally composed of universal bearings and other accessories, but it is difficult to manufacture and assemble, the production cost is high, and it is not easy to disassemble and maintain

[0005] Third, the control of unmanned helicopters is generally driven by rotary steering gear. Since the circular motion of the steering gear needs to be converted into the required linear motion, it is necessary to design a variety of conversion mechanisms, resulting in complex structures, low operating efficiency, and low force transmission. low efficiency

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