Mechanical droop for spoiler operation

A method for mechanically operating an aircraft wing, comprising:

• rotating a torque tube at a first rate of rotation, wherein the rotation of the torque tube causes a downward rotation of a control surface, wherein the torque tube is coupled to a gearing assembly comprising an output shaft;
• reducing, via the gearing assembly, the first rate of rotation of the torque tube to a second rate of rotation that is less than the first rate of rotation;
• rotating the output shaft at the second rate of rotation, wherein the output shaft is coupled to a rotational member, and wherein a rotational center of the output shaft and a rotational center of the rotational member are concentric;
• rotating the rotational member, wherein the rotational member is coupled to a first end of a linear actuator at a forward attach point, wherein the linear actuator comprises the first end and a second end, and wherein the forward attach point is eccentric to the rotational center of the rotational member, wherein the rotational member comprises a first leg and a second leg coupled by a curved portion, wherein the first leg and the second leg of the rotational member straddle the first end of the linear actuator, and wherein a pin joint extends from the first leg, through the first end of the linear actuator, to the second leg;
• and
• translating the forward attach point relative to the aircraft wing based on the rotation of the rotational member.

An aircraft comprising:

• an aircraft wing, wherein the aircraft wing comprises a first control surface positioned adjacent to a second control surface;
• a system for mechanical operation of the aircraft wing, wherein the system comprises:
• a torque tube coupled to the first control surface, wherein the torque tube is rotatable at a first rate of rotation to cause a downward rotation of the first control surface relative to the aircraft wing;
• a gearing assembly coupled to the torque tube, wherein the gearing assembly comprises an output shaft, and wherein the torque tube is configured to rotate the output shaft, via the gearing assembly, at a second rate of rotation that is less than the first rate of rotation of the torque tube;
• a rotational member coupled to the output shaft of the gearing assembly, wherein the output shaft is rotatable to drive a rotation of the rotational member, and wherein a rotational center of the output shaft and a rotational center of the rotational member are concentric;
• and
• a linear actuator comprising a first end and a second end, wherein the first end of the linear actuator is coupled to the rotational member at a forward attach point, wherein the forward attach point is eccentric to the rotational center of the rotational member, and wherein the rotational member is rotatable to cause a translation of the forward attach point relative to the aircraft wing;
• and
• wherein the rotational member comprises a first leg and a second leg coupled by a curved portion, wherein the first leg and the second leg of the rotational member straddle the first end of the linear actuator, and wherein a pin joint extends from the first leg, through the first end of the linear actuator, to the second leg, and
• wherein the second control surface is coupled to the second end of the linear actuator, and wherein the forward attach point is translatable, via rotation of the rotational member, to cause a downward rotation of the second control surface relative to the aircraft wing.