Flight control device and method for increased rigging precision
AssigneeEaton Intelligent Power Limited
InventorsDaniel Henry Roberts, Tyler Quincey Curtis, Richard Strong Wallace, Jr.
Life of this patent
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Abstract
The present disclosure relates to a flight control device that can be mounted to a body of a wing of an aircraft to reduce or eliminate backlash in electromechanical actuators (EMAs). The flight control device can include a flight control member and first and second actuators for moving the flight control member relative to the wing of the aircraft. The first and second actuators can be mechanically isolated from one another except for their mutual connection to the flight control member. The first and second actuators can cooperate to apply torsional loading to the flight control member about an axis of the flight control member to reduce or eliminate backlash.
Claims18
A method of rigging a flight control member mounted on an aircraft wing, the flight control member defining an axis that extends along a length of the flight control member, the method comprising the steps of:
- providing first and second actuators for moving the flight control member relative to a main body of the aircraft wing, the first and second actuators being mechanically isolated from one another except for their mutual connection to the flight control member;
- controlling actuation of the first and second actuators such that the first and second actuators cooperate to apply torsional loading to the flight control member to reduce or eliminate backlash;
- and
- establishing a neutral position of the flight control member after the backlash has been removed by measuring an angle of the flight control member at a midpoint between the first and second actuators.
A method of controlling a movement of a flight control member adapted to be mounted on an aircraft wing, the flight control member includes a plurality of actuators, the method comprising:
- providing the plurality of actuators for moving the flight control member relative to a main body of the aircraft wing, the plurality of actuators being mechanically isolated from one another except for their mutual connection to the flight control member;
- and
- controlling actuation of the plurality of actuators such that the plurality of actuators cooperate to apply torsional loading to the flight control member to reduce or eliminate backlash;
- wherein the flight control member includes an electronic controller for coordinating operation of the plurality of actuators as the flight control member is moved relative to the main body of the wing;
- wherein the method comprises determining in flight when the flight control member is in at least one predetermined position relative to the main body of the wing, and wherein the determination that the flight control member is in the at least one predetermined position causes the electronic controller to implement programming which controls actuation of the plurality of actuators such that the plurality of actuators cooperate to apply torsional loading to the flight control member to reduce or eliminate the backlash.
Dependencies are inferred from the claim text.