Co-universal-shaft type full-rigidity double-rotor helicopter

Abstract

The invention provides a co-universal-shaft type full-rigidity double-rotor helicopter and relates to the technical field of flight equipment. The provided co-universal-shaft type full-rigidity double-rotor helicopter comprises a helicopter body, a rotor shaft, a rotor and a drive device. The rotor shaft comprises an inner rotary shaft and an outer rotary shaft. The rotor comprises an upper rotorand a lower rotor. The inner rotary shaft and the outer rotary shaft are coaxial, are connected with the helicopter body through universal bearing assemblies and can rotate around the same fixed pivotrelative to the helicopter body. The fixed pivot is located on the axis of the inner rotary shaft. The drive device is in transmission connection with the inner rotary shaft and the outer rotary shaft so as to drive the inner rotary shaft to rotate around the axis of the inner rotary shaft and the outer rotary shaft to rotate around the axis of the outer rotary shaft. The upper rotor is fixedly connected to the inner rotary shaft, and the lower rotor is fixedly connected to the outer rotary shaft. The upper rotor and the lower rotor are distributed in a spaced mode in the axial direction of the inner rotary shaft. By the adoption of the provided co-universal-shaft type full-rigidity double-rotor helicopter, the technical problem that a helicopter in the prior art is large in control difficulty is solved.

Description

technical field [0001] The invention relates to the technical field of aviation flight equipment, in particular to a co-cardan shaft fully rigid dual-rotor helicopter. Background technique [0002] Rotary-wing helicopters include various forms, mainly including: single-rotor, coaxial dual-rotor and non-coaxial multi-rotor. [0003] The flight control mechanism of a single-rotor helicopter generally includes a rotor and a tail rotor; when the rotor rotates, it will generate a reaction moment to the helicopter fuselage, which tends to drive the helicopter to rotate around the axis of the fuselage and affect the balance of the fuselage; The tail rotor is installed on the side, and the moment of the fuselage generated by the rotation of the tail rotor is used to balance the reaction moment of the rotor. [0004] When the rotor rotates, the relative air velocity of the forward blades in the rotor that rotates toward the nose is higher than the relative air velocity of the backwa...

AI Technical Summary

Problems solved by technology

[0008] It can be seen from the above that in the prior art single-rotor helicopters and coaxial dual-rotor helicopters, a variable-pitch hinge is generally required between the blades and the rotor shaft, and the pitch-variable control of the blades is carried out through an automatic tilter. It is more complicated and difficult to control; the non-coaxial multi-rotor helicopter needs to control multiple rotors to cooperate with each other, the balance factor is large, and the control is difficult

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