A rotary plate type magneto-rheological damper for aircraft landing gear

Abstract

The invention relates to a rotating plate type magneto-rheological shimmy damper for a landing gear of an aircraft comprising a cylinder tube, end caps, stator assemblies and a rotor assembly, wherein the end caps are coaxially and hermetically mounted at both ends of the cylinder tube; each stator assembly is fixedly and symmetrically mounted in the part of the cylinder tube inside the corresponding end cap; a drive shaft is coaxially arranged in the cylinder tube between the two stator assemblies in a running-through manner; the drive shaft in the cylinder tube is provided with the rotor assembly and drives the rotor assembly to rotate in the cylinder tube; and one end of the drive shaft is provided with a double rocker mechanism. The rotating plate type magneto-rheological shimmy damper for the landing gear of the aircraft is a semi-active shimmy control device which is capable of guaranteeing a minimum damping under zero magnetic field conditions and increasing the adjustment range of damping force of the shimmy damper, and has the advantages of simple structure, low energy consumption, small size, fast response and continuously adjustable direction of the damping force in a large range; and the same overcomes the problems of unmeasured state feedback quantity, large energy consumption of active control force, time delay and spillovers of a traditional passive damper in the prior art, and is useful as an actuator for structural shimmy control.

Description

technical field [0001] The invention belongs to the field of aircraft accessories, and relates to an aircraft landing gear, in particular to a rotating plate magneto-rheological damper for the aircraft landing gear. Background technique [0002] For an aircraft with tricycle landing gear layout, during takeoff and landing roll, the front wheels will vibrate violently from its neutral position. This swing is mainly derived from the alternating rotation of the swinging part of the landing gear around its orientation axis, and the corresponding alternating deformation of the tire and the ground contact part. Aircraft nose wheel shimmy is a very complex self-excited vibration caused by the mutual coupling of the landing gear buffer strut, the lateral vibration of the nose wheel and the torsional vibration of the nose wheel around the axis of the strut. The energy to maintain this self-excited vibration is Provided by the forces and moments that the ground acts on the tires duri...

AI Technical Summary

Problems solved by technology

Shock absorbers are generally divided into piston type and rotary plate type. In the rotary plate type, oil type shock absorbers are more widely used. This kind of orifice is usually passively adjusted with temperature changes. Since it is installed around the oil limit valve rod Two kinds of adjustment springs with different expansion coefficients, the springs will deflect as the temperature changes, so as to adjust the damping force, the traditional shock absorber has limited adjustment range, and the structure is quite complicated

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