Actuator assembly with redundant drivers and linkages to mitigate fault conditions

A control system for an aircraft comprising:

• a controller to receive an input flight control signal and to generate at least a first driver sub-assembly control signal and a second driver sub-assembly control signal responsive to the input flight control signal;
• an actuator assembly comprising:
• a first driver sub-assembly to generate a first rotational force of a first drive shaft about a drive shaft rotational axis in response to the first driver sub-assembly control signal;
• a first driver link having a proximate end coupled to the first drive shaft and configured, when operational, to rotate in a first plane perpendicular to the drive shaft rotational axis in response to the first rotational force;
• a first driver bearing assembly coupled to a distal end of the first driver link;
• a first output link having a proximate end coupled to first driver bearing assembly;
• a second driver sub-assembly to generate a second rotational force of a second drive shaft about the drive shaft rotational axis;
• a second driver link having a proximate end coupled to the second drive shaft and configured, when operational, to rotate in a second plane perpendicular to the drive shaft rotational axis in response to the second rotational force;
• a second driver bearing assembly coupled to a distal end of the second driver link;
• a second output link having a proximate end coupled to second driver bearing assembly;
• an output bearing assembly coupled to distal ends of the first output link and the second output link, wherein the output bearing assembly is configured to move along an arc responsive to rotation of at least one of the first driver link and the second driver link;
• and
• a connecting link having a proximal end coupled to the output bearing assembly;
• and
• a control surface coupled to a distal end of the connecting link at an attachment point, wherein the attachment point is displaced based on an output force of the connecting link to achieve an output displacement.

A method for controlling an actuator assembly for an aircraft, the method comprising:

• obtaining, by a controller, a control input signal for controlling an output state of a control surface and obtaining one or more feedback signals indicative of an operational status of a first driver link driven by a first driver sub-assembly and a second driver link driven by a second driver sub-assembly, wherein the first driver link and the second driver link are coupled to a first output link and second output link respectively, and wherein the first output link and the second output link are jointly coupled to a connecting link coupled to the control surface;
• responsive to the one or more feedback signals indicating a normal operating condition of the first driver link and the second driver link, generating a first driver sub-assembly control signal and a second driver sub-assembly control signal that achieves the output state of the control surface specified in the control input signal by controlling the first driver link and the second driver link to rotate in unison and maintain a substantially fixed driver link angle between the first driver link and the second driver link;
• and
• responsive to the one or more feedback signals indicating a fault condition of the first driver link, generating, by the controller, the first driver sub-assembly control signal to achieve the output state of the control surface specified in the control input signal by controlling the first driver link independently of the second driver link.