Intra-shaft operation rotor wing device

Abstract

The invention discloses an intra-shaft operation rotor wing device, and belongs to the technical field of controlling rotor wings of helicopters. The intra-shaft operation rotor wing device comprises a rotating ring and fixed ring component, an anti-twist pull rod component, a steering engine, a support component, an upper collective pitch slide block, a lower collective pitch slide block, an upper collective pitch bolt, a lower collective pitch bolt, and a variable-torque pull rod component, wherein the variable-torque pull rod component is fixed on a main rotor wing shaft by virtue of the upper collective pitch bolt and the upper collective pitch slide block, and the upper collective pitch slide bock is inlaid at the upper end of the main rotor wing shaft and can slide up and down; the rotating ring and fixed ring component is fixed at the lower end of the main rotor wing shaft by virtue of the lower collective pitch bolt and the lower collective pitch slide block, and the lower collective pitch slide block is inlaid at the lower end of the main rotor wing shaft and can slide up and down; and the rotating ring and fixed ring component is arranged at the lower part of a main speed reducer and is connected with a rotor wing propeller hub by virtue of the variable-torque pull rod component, and the anti-twist pull rod component and the steering engine are fixed on the rotating ring and fixed ring component. The intra-shaft operation rotor ring device disclosed by the invention adopts an intra-shaft operation transmission mode to reduce sizes and weights of components, and is also beneficial for reducing flight resistance of a helicopter.

Description

technical field [0001] The invention belongs to the technical field of helicopter rotor control, and in particular relates to an in-axis control rotor device. Background technique [0002] Rotor control is an extremely important part of the helicopter rotor system. It mainly transmits the collective pitch and periodic pitch control input from the steering gear to the rotor blades to realize the change of the angle of attack of the blades, thereby controlling the magnitude and direction of the rotor lift and realizing Attitude control of the helicopter. [0003] The typical structure of the rotor control is mainly a ring-type spherical hinge structure, which is mainly composed of a moving ring and a fixed ring assembly, a large bearing, a large ball hinge assembly, a torque arm assembly, an anti-twist arm assembly, and a variable pitch rod assembly. The moving ring and the fixed ring assembly can slide up and down along the guide cylinder fixed on the upper end of the main r...

AI Technical Summary

Problems solved by technology

[0004] The rotor control of the ring-type spherical hinge structure is arranged outside the rotor shaft, which increases the size and weight of the parts, increases the resistance generated during the flight of the helicopter, and is not conducive to the overall layout of the small helicopter

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