A double-redundant electric turning and sway reduction mechanism and aircraft landing gear

Abstract

The invention discloses a double-redundant electric turning and swing reduction mechanism and an aircraft landing gear. The mechanism comprises a driving motor, an outer cylinder, a rotating cylinder and a piston rod; the outer cylinder has a first stepped hole and a piston rod along its axial direction. The second stepped hole communicated with the lower end, the driving motor is fixed in the first stepped hole, the upper part of the rotating cylinder is sleeved in the second stepped hole, and the rotating cylinder can rotate in the circumferential direction relative to the outer cylinder assembly but cannot move axially, The upper end of the rotating cylinder is connected with the drive motor assembly; the upper part of the piston rod is provided with a piston which is sealed and slidably arranged in the rotating cylinder; components. This mechanism replaces the traditional hydraulically driven turning and oil damping sway reduction mechanism. It reduces the total weight and failure rate of the landing gear, and simplifies the structure and control of the turning and sway reduction system. The needs of reliability, maintainability, high work efficiency and low cost.

Description

technical field [0001] The invention relates to the technical field of aircraft landing gear, in particular to a double-redundant electric turning and swing reduction mechanism and an aircraft landing gear. Background technique [0002] The turning and sway reduction systems of the landing gear of aircraft (especially large and medium-sized aircraft) still use hydraulic drive and oil damping. Emergency backup devices, etc., therefore, there are problems such as complicated control, bulky structure, large energy loss, many fault points, and difficult maintenance and repair, which makes the turning and swing reduction systems of the landing gear less reliable, safe, maintainable, and supportive. , many failures and difficult to diagnose, and heavy weight. [0003] In order to comprehensively improve the tactical performance of modern aircraft, especially modern military aircraft, the traditional hydraulic-driven and oil-damped landing gear turning and sway reduction systems c...

AI Technical Summary

Problems solved by technology

[0002] At present, the turning and anti-swaying systems of the landing gear of aircraft (especially large and medium-sized aircraft) still use hydraulic drive and oil damping. It needs to be equipped with hydraulic oil source, hydraulic pump and various hydraulic control valves, hydraulic control actuators and connecting oil pipes. Emergency backup devices, etc., so there are problems such as complex control, complex and bloated structure, large energy loss, many fault points, and difficult maintenance and repair, which makes the reliability, safety, maintainability, and support of the landing gear turning and sway reduction systems not high. , many faults and difficult to diagnose, and heavy

[0003] In order to comprehensively improve the tactical performance of modern aircraft, especially modern military aircraft, the traditional hydraulic drive and oil damping landing gear steering and anti-sway systems are no longer suitable for double redundancy, safety, low failure rate, easy diagnosis, and maintenance , simple structure integration, low weight, and simple system control technology development requirements

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