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.