Low-leakage hydraulic shimmy damping compensation loop for aircraft nose wheel turning system

Abstract

The invention relates to a low leakage hydraulic shimmy damping compensation loop for an aircraft nose wheel turning system. The hydraulic shimmy damping compensation loop comprises a turning actuator, pressure sensitive devices, an unloading valve, an anti-leakage device and a compensator. Hydraulic flow and hydraulic pressure are stored in the compensator; the anti-leakage device is arranged atan outlet of the compensator; the unloading valve is arranged at an oil return path of the aircraft hydraulic system; the hydraulic flow enters the compensator through the anti-leakage device under the action of back pressure generated by the unloading valve; the pressure sensitive devices are arranged in a left cavity and a right cavity of the turning actuator, and when the pressure of at least one cavity of the turning actuator exceeds a pressure threshold value, the cavity pressure controls the anti-leakage device to be started through the pressure sensitive devices, so that hydraulic flowin the compensator flows out of the compensator. The hydraulic shimmy damping compensation loop has the advantages that leakage of the compensator of the hydraulic shimmy damping compensation loop isreduced, and hydraulic flow needing to be stored by the compensator is reduced.

Description

technical field [0001] The invention relates to a low-leakage hydraulic pressure reduction compensation circuit for an aircraft front wheel steering system, and belongs to the technical field of aircraft hydraulic control. Background technique [0002] The hydraulic anti-swing reduction of the front wheel of the aircraft quickly attenuates the front wheel shimmy caused by the external load through the damping effect of the throttle valve. The shimmy circuit supplements flow and pressure for the shimmy circuit by setting a compensator. Since the hydraulic energy system no longer provides hydraulic pressure and flow to the nose wheel steering system during aircraft flight, in order to ensure that the hydraulic swing reduction is in the event of hydraulic system failure, the aircraft still has the nose wheel steering hydraulic swing reduction capability during landing, and the compensator needs to To ensure that the aircraft has the pressure and flow required to compensate the...

AI Technical Summary

Problems solved by technology

[0004] Although the traditional hydraulic compensation method can realize hydraulic pressure reduction and oil and pressure compensation during the reduction process, it has the following disadvantages: when the hydraulic reduction circuit is not working, because the compensator is always connected to the reduction circuit, the oil stored in the compensator The liquid leaks continuously through the unloading valve at the oil return, the flow in the compensator decreases continuously, and the pressure gradually decreases

For the aircraft nose wheel steering system, the sway reduction circuit has no pressure supply during the long-term flight of the aircraft, and the oil stored in the compensator needs to increase according to the increase in the no pressure supply time, resulting in an increase in the volume of the compensator, and the weight and weight of the nose wheel steering system. The volume increases accordingly, and the weight of the aircraft increases

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