Rotor wing pitch change control device of heligyro

Abstract

The invention relates to a rotor wing pitch change control device of a heligyro. A total propeller pitch sliding bush is arranged in a cavity of a main shaft supporting seat and is connected with a total propeller pitch control mechanism; a main control rod for controlling cyclic pitch changes is in clearance fit in a ball socket of the total propeller pitch sliding bush through a ball head; a synchronous control arm for controlling attack angle changes of a rotor wing is rotatablely connected on the upper part of the main control rod; the lower end of the main control rod is connected with acyclic pitch change control mechanism; a propeller hub is rotatablely sleeved outside the main shaft supporting seat; a propeller hub torque transfer device is connected with the synchronous control arm for controlling the attack angle changes of the rotor wing; the rotor wing is arranged on the propeller hub and is connected with the synchronous control arm for controlling the attack angle changes of the rotor wing; and the circumference of the lower part of the propeller hub is provided with circumferential teeth meshed with an output gear of a gearbox. The rotor wing pitch change control device uses the propeller hub as a main shaft to shorten the axial distance between rotor wing pitch gearboxes and reduce the bearing stress of the main shaft, can reduce the manufacturing difficulty and the cost, and simultaneously is favorable for the centralized lubrication of moving parts to reduce the lubrication cost.

Description

Technical field [0001] The invention relates to the field of rotor helicopters, in particular to a rotor variable pitch control device of a rotor helicopter. Background technique [0002] The pitch and tilt flight attitude of the rotor helicopter in flight is realized by changing the angle of attack of the rotor at different angles by the way of periodic pitch change. The lifting control during flight is realized by controlling the angle of attack of the rotor by the total pitch. The traditional helicopter rotor angle of attack control device includes rotor, rotor main shaft, total pitch sliding sleeve, torque arm, swash plate, pull rod, gear box, the lower end of the rotor main shaft extends into the gear box and the gear set in the gear box The upper end of the rotor main shaft is fixedly connected to the hub in the circumferential direction. The rotor is installed on the hub, the total pitch sliding sleeve is sleeved on the rotor main shaft, and the swash plate hollow sleeve i...

AI Technical Summary

Problems solved by technology

The structure of the control device of this structure is complicated, especially the swash plate is located between the rotor and the gear box and is arranged outside the total pitch sleeve. This takes up a large axial space distance, so that the distance between the rotor and the gear box is relatively long, resulting in a long shaft length of the rotor main shaft, and the bearing of the gear box supporting the rotor main shaft can only be connected with the lower section of the rotor main shaft. The rotor spindle is coordinated, the longer the spindle, the greater the shaking when it rotates, and the greater the stress it bears. The requirements for the production materials and processing of the spindle are very high, resulting in high production costs.

Moreover, the linear speed of the swash plate is very high, and its lubrication requirements are also high. However, because the swash plate is located between the rotor and the gearbox, the swash plate is connected to the overall pitch sliding sleeve through the universal joint connecting rod in the radial direction. The upper end of the swash plate is connected to the torsion arm on each rotor through a tie rod, and the lower end of the swash plate is connected to the control mechanism through a control link. This makes the lubrication system of the swash plate unable to share with the gearbox, and a special lubrication system must be set up to solve the inclination The separate lubrication of the disc increases its manufacturing cost and lubrication cost

At the same time, in order to ensure the stability of the movement of the device, the design of this device is redundant, and the demand for the control force of the helicopter is increased due to the mule effect, which is not conducive to the driving and manipulation of the helicopter.

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