Course control system for coaxial helicopter

Abstract

The invention discloses a course control system for a coaxial helicopter. The course control system is arranged between an upper rotor wing and a lower rotor wing in the coaxial helicopter. The course control system comprises a small course control wing, a small control wing propeller hub, a course control sliding ring and a small wing variable-pitch rocker arm. The small control wing propeller hub is fixedly connected with a lower rotor wing shaft. The small course control wing comprises a small wing connecting rod and a small wing. The small wing is in connection with a bearing in the circumferential direction of the small control wing propeller hub through the small wing connecting rod. The course control sliding ring is of a bearing structure. An inner circle of the course control sliding ring is in axial sliding connection with the lower rotor wing shaft. The small wing variable-pitch rocker arm is of a structure of three small wing connecting rods, wherein two small wing connecting rods are hinged, then the two ends of the two hinged small wing connecting rods are connected with the small wing connecting rod and the inner circle of the course control sliding ring, and the other small wing connecting rod is connected with an outer circle of the course control sliding ring. Therefore, the propeller blade angle of a wing face can be controlled to be changed and the torque of the lower rotor ring shaft is controlled by driving the small wing variable-pitch rocker arm with a steering engine. The course control system has the advantages that control over the course of the coaxial helicopter is achieved, and course control torque and lift changes of the helicopter are reduced.

Description

technical field [0001] The invention relates to a heading control system, in particular to a heading control system for a coaxial helicopter. Background technique [0002] At present, the coaxial helicopter heading control system adopted at home and abroad has various forms: [0003] Form 1: The heading control of the coaxial helicopter is realized by adjusting the rotation speed of the upper and lower rotor shafts. [0004] Form 2: By changing the blade angle of the upper and lower rotors or installing a drag plate on the rotor blades to change the moment caused by the aerodynamic resistance of the upper and lower rotors, the heading control of the coaxial helicopter is realized. This form of directional control force is relatively large, mainly due to the need to change the entire blade angle of the upper and lower rotors or one of the secondary rotors. [0005] For Form 1, the heading control scheme of adjusting the rotation speed of the upper and lower rotor shafts wil...

AI Technical Summary

Problems solved by technology

[0008] In order to overcome the shortage of the existing coaxial helicopter heading control system due to excessive steering torque and the resulting change in lift force, the present invention proposes a heading steering system for a coaxial helicopter, which can reduce the heading steering torque and reduce the Changes in lift caused by heading maneuvers

Images