Transverse rigid rotor blade helicopter

Abstract

The invention discloses a transverse rigid rotor blade helicopter, which comprises a fuselage, wings disposed at two sides of the fuselage, wing piers disposed on the wings, a main driving device disposed inside the fuselage, power transmission shafts disposed in the wings, rotor driving shafts disposed in the wing piers; propeller hubs, and blades; the invention is characterized in that: universal joints are disposed between the rotor driving shafts and the propeller hubs, and the blades are hinged to the propeller hubs in an axial direction. According to the invention, the position of the rotor rotating plane is not changed by complicated cyclic pitch control of routine rotor helicopters; the propeller hubs have simple structures; the rotor is simple in dynamics, and simple in operation, has high flying aerodynamic efficiency, good maneuverability, and low power dissipation.

Description

technical field [0001] The invention relates to a tandem helicopter, in particular to a tandem rigid rotor blade helicopter of a new configuration. Background technique [0002] The rotor of the existing conventional rotor helicopter consists of a hub and several blades, the hub is fixedly installed on the rotor shaft, and the blades are installed on the on the hub. The axial hinge makes the blade generate the axial variable pitch motion, and the flapping hinge and the shimmy hinge make the blade generate the flapping motion and the shimmy motion. As the blade rotates, it interacts with the surrounding air, creating a pulling force perpendicular to the plane of rotation of the rotor. If the plane of rotation of the rotor is horizontal, the pulling force is vertically upward, and the helicopter flies vertically. If the rotor rotation plane is tilted, the pulling force is tilted, and the helicopter flies in the direction of the pulling force tilting. If you lean forward, y...

AI Technical Summary

Problems solved by technology

In the process of the rotor tilting forward, the bending of the aerodynamic wake of the rotor leads to extremely complex aerodynamic changes, which makes the control of the helicopter extremely complicated, and often causes the flight accident of the helicopter during the rotor tilting process.

In addition, when this type of horizontal tilt-rotor helicopter is flying in helicopter mode, it is also necessary to perform complex periodic pitch-variable control of the rotor.

Therefore, this type of transverse tilt-rotor helicopter has more prominent problems such as more complicated structure, more complicated flight control, and more complicated mechanics involved.

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