Aircraft landing gear torque link assembly
A torque link assembly for an aircraft landing gear comprising: an upper torque link; a lower torque link; a joint pin arranged to pivotally couple the upper torque link and lower torque link; an electric motor assembly; a sensor arranged to detect movement of the upper torque link or lower torque link and in response to detecting the movement providing a control signal to the electric motor assembly, wherein the electric motor assembly is configured to linearly translate the joint pin with respect to one of the upper or lower torque links.
1 . A torque link assembly for an aircraft landing gear comprising:
an upper torque link;
a lower torque link;
a joint pin arranged to pivotally couple the upper torque link and lower torque link;
an electric motor assembly; and
a sensor arranged to detect movement of the upper torque link or lower torque link and, in response to detecting the movement, provide a control signal to the electric motor assembly,
wherein the electric motor assembly is configured to linearly translate the joint pin with respect to one of the upper or lower torque links.
2 . The torque link assembly according to claim 1 , wherein the electric motor is fixed relative to one of the upper or lower torque links.
3 . The torque link assembly according to claim 2 , wherein the electric motor is fixed relative to the lower torque link.
4 . The torque link assembly according to claim 1 , wherein the electric motor assembly comprises one or more solenoid motors.
5 . The torque link assembly according to claim 4 , wherein the solenoid motor is a linear solenoid actuator type.
6 . The torque link assembly according to claim 1 , wherein the joint pin comprises an outer sleeve which comprises ferromagnetic material.
7 . The torque link assembly according to claim 1 , wherein the motor assembly includes one or more Belleville washers.
8 . The torque link assembly according to claim 1 , wherein the motor is configured to evaluate a vibration magnitude based on the movement, and maintain the force on the joint pin until the vibration magnitude is below a threshold.
9 . The torque link assembly according to claim 1 , further comprising a health monitoring system arranged to record the duration and magnitude of a shimmy vibration event based on the movement.
10 . The torque link assembly according to claim 9 , wherein the health monitoring system is arranged to record a duration and magnitude of the force applied to the joint pin by the electric motor.
11 . An aircraft landing gear assembly including the torque link assembly of claim 1 .