Coaxial type bending and twisting simultaneous transmission control surface transmission mechanism

Abstract

The invention provides a design scheme of a coaxial type bending and twisting simultaneous transmission control surface transmission mechanism, and aims to solve inherent defects of a common pull rodrocker arm type control surface transmission mechanism for airplanes adopting airfoils with medium and above thicknesses. The mechanism is characterized by comprising a steering engine, a steering engine mounting rib, a needle bearing, a check ring, a coupler, a transmission spline, a control surface, a knuckle bearing, a rotating shaft pin, a control surface mounting rib and a machine body rear beam, wherein the steering engine is connected with the coupler, the needle bearing is arranged on the coupler, a check ring bearing is arranged on the outer side of the needle bearing, the check ringbearing is provided with the steering engine mounting rib, the steering engine mounting rib is connected with the transmission spline, one side of the transmission spline is the control surface, the control surface is provided with the rotating shaft pin, the rotating shaft pin is connected with the knuckle bearing, the knuckle bearing is connected with the control surface mounting rib, and the control surface mounting rib is connected with the machine body rear beam.

Description

technical field [0001] The invention relates to the field of aviation manufacturing, and relates to a coaxial bending and torsion simultaneous transmission rudder surface transmission mechanism. Background technique [0002] At present, the common control rudder transmission form of manned aircraft or medium and large UAVs is the rod rocker transmission mechanism. This form of transmission mechanism can be further divided into the form of the electric steering gear output torque rocker to drive the rudder surface pull rod, or the hydraulic cylinder directly drives the rudder surface rocker, etc. This form of rudder surface transmission has the following disadvantages: [0003] 1) The structure of the rod rocker arm will inevitably cause the transmission mechanism to protrude from the shape of the rudder surface and the shape of the wing surface where it is located. It is necessary to design rectification bulges between the output end of the steering gear and the rudder surfa...

AI Technical Summary

Problems solved by technology

[0003] 1) The structure of the rod rocker arm will inevitably cause the transmission mechanism to protrude from the shape of the rudder surface and the shape of the wing surface where it is located. It is necessary to design rectification bulges between the output end of the steering gear and the rudder surface rocker. The effective lift area reduces the control efficiency of the rudder surface and increases the aerodynamic drag during flight;

[0004] 2) The transmission path formed by the rod rocker structure is longer

There are many accessories of the mechanism, on the one hand, it causes the weight of its transmission structure to be large, and on the other hand, it affects its transmission accuracy;

[0005] 3) For aircraft with stealth performance requirements, the front and rear rectification bulges formed by the rod rocker structure will increase unnecessary reflection and scattering, affecting stealth performance

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