Rigid rotor system for helicopter

Abstract

The invention discloses a rigid rotor system for a helicopter. The rigid rotor system comprises a rigid rotor propeller hub, a rigid rotor pitch control mechanism and rigid rotor paddles, wherein the rigid rotor pitch control mechanism and the rigid rotor paddles are glued integrally and are connected with the rigid rotor propeller hub by virtue of bolts. According to the system disclosed by the invention, deep groove ball bearings and thrust bearings in the conventional teeterboard type propeller hub structure are replaced by joint bearings, so that a series of complex structures such as pitch change shafts, flapping hinges and vertical hinges are removed, and the problems such as complexity of the conventional teeterboard type propeller hub structure, heavy weight and short service life can be solved. Meanwhile, the problems that retreating paddleseasily enter an aerodynamic stalling state so as to reduce the aerodynamic efficiency due to swinging during high-speed forward flight and the like are solved, and the rigid rotor system has the advantages of simple structure, light weight, long service life, high maintainability and the like.

Description

technical field [0001] The invention relates to the field of aviation technology, in particular to a rigid rotor system of a helicopter. Background technique [0002] see figure 1 and figure 2 , the traditional helicopter rotor system generally includes three hinges (that is, three degrees of freedom), which are respectively the traditional rotor pitch variable hinge 4 that controls the change of the pitch angle of the traditional rotor blade 1, allowing the traditional rotor blade 1 to operate in flight. The traditional rotor flapping hinge 3 that swings up and down and the traditional rotor swing hinge 5 that allows the traditional rotor blade 1 to move back and forth during flight. [0003] The main cause of the waving motion of the traditional rotor blade 1 is that when the helicopter flies forward, the rotation motion of the traditional rotor blade 1 and the forward flight motion are superimposed. Taking the counterclockwise rotation of the rotor in the top view as a...

AI Technical Summary

Problems solved by technology

[0006] (1) Complex mechanical structure, heavy weight, short life and poor maintainability;

[0007] (2) When flying forward at high speed, the compensation effect of the angle of attack generated by the waving of the backward blade makes it easier to enter the aerodynamic stall state, thereby reducing its aerodynamic efficiency

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