A high-lift device includes a flap disposed at a leading edge of a wing, and configured to be retracted in the lower surface and extended toward of the leading edge; a first rotary shaft and a second rotary shaft, the axial direction of the rotary shafts being disposed along the spanwise direction of the wing, respectively; a first link mechanism connected to the first rotary shaft and the flap; and a second link mechanism connected to the second rotary shaft and the flap. When the first link mechanism is driven with the first rotary shaft, the flap is retracted in the lower surface of the leading edge or is extended toward the front of the leading edge. When the second link mechanism is driven with the second rotary shaft, the position or the angle of the flap moved by the first link mechanism is changed.

Example flap actuation systems and related methods are disclosed herein. An example flap actuation system includes a first actuator, a second actuator, a first drive arm coupled to the first actuator and to a flap, a second drive arm coupled to the second actuator and to the flap, a first cam, and a first output shaft. The first cam is to couple to the first drive to enable the first actuator to actuate the flap via the first drive arm. The example flap actuation system includes a second cam and a second output shaft. The first cam is to be uncoupled from the first drive arm in response to a failure of the first actuator. The second actuator is to actuate the flap via the first drive arm and the second drive arm in response to the failure of the first actuator.

Example flap actuation systems and related methods are disclosed herein. An example flap actuation system includes a first actuator, a second actuator, a first drive arm coupled to the first actuator and to a flap, a second drive arm coupled to the second actuator and to the flap, a first cam, and a first output shaft. The first cam is to couple to the first drive to enable the first actuator to actuate the flap via the first drive arm. The example flap actuation system includes a second cam and a second output shaft. The first cam is to be uncoupled from the first drive arm in response to a failure of the first actuator. The second actuator is to actuate the flap via the first drive arm and the second drive arm in response to the failure of the first actuator.

Example flap actuation systems and related methods are disclosed herein. An example control surface actuation system includes processor circuitry to cause a first actuator to generate an output to operatively couple the first actuator to a first drive arm; cause a second actuator to generate an output to operatively couple the second actuator to a second drive arm; cause the first actuator and the second actuator to move a control surface when the first actuator and the second actuator are in an operative state; detect the first actuator as in a failed state; and in response to the first actuator being in the failed state, cause first actuator to refrain from generating the output to disrupt the operative coupling between the first actuator and the first drive arm; and cause the second actuator to move the control surface via the first drive arm and the second drive arm.

Example flap actuation systems and related methods are disclosed herein. An example control surface actuation system includes processor circuitry to cause a first actuator to generate an output to operatively couple the first actuator to a first drive arm; cause a second actuator to generate an output to operatively couple the second actuator to a second drive arm; cause the first actuator and the second actuator to move a control surface when the first actuator and the second actuator are in an operative state; detect the first actuator as in a failed state; and in response to the first actuator being in the failed state, cause first actuator to refrain from generating the output to disrupt the operative coupling between the first actuator and the first drive arm; and cause the second actuator to move the control surface via the first drive arm and the second drive arm.

A bell crank mechanism is configured to at least indirectly link movement of an aircraft wing spoiler-like hinge panel to the movement of a primary flight control device on an aircraft wing trailing edge. The aircraft wing is configured to be fixed to and to extend from an aircraft fuselage, the wing including a leading edge and a trailing edge. The primary flight control device is attached to the trailing edge, and any movement of the control device is directly subject to an aircraft input controller by a linear actuator. The moveable aerodynamic hinge panel, a secondary control device, is situated proximally to the primary flight control device, and the hinge panel is separately attached to the trailing edge. The bell crank mechanism slaves any hinge panel motion to movements of the primary control device.

A force-shunting device including a tube defining a main axis and an inner wall, a first member sliding within the tube, a primary leg arranged obliquely, attached to the first member and including a primary pad in frictional contact with the inner wall, such that, when an external force is applied in a first direction on the first member, the primary leg rubs, or grips by mechanical camming, against the inner wall, the tube thus reacting all or part of the external force, the device including a second member mounted within the tube, sliding along the main axis and securely provided with a driving element of the primary pad so as to reduce the friction on the inner wall, to unprime the rubbing or mechanical camming.

A force-shunting device including a tube defining a main axis and an inner wall, a first member sliding within the tube, a primary leg arranged obliquely, attached to the first member and including a primary pad in frictional contact with the inner wall, such that, when an external force is applied in a first direction on the first member, the primary leg rubs, or grips by mechanical camming, against the inner wall, the tube thus reacting all or part of the external force, the device including a second member mounted within the tube, sliding along the main axis and securely provided with a driving element of the primary pad so as to reduce the friction on the inner wall, to unprime the rubbing or mechanical camming.

A flap actuation mechanism incorporates a flap bracket attached to a flap and coupled to an underwing structure with a pivotal coupling. A crankshaft is configured for over center rotation and has aligned inboard and outboard crank arms extending from axially spaced inboard and outboard journals disposed in the underwing structure and configured to rotate about a rotation axis of the inboard and outboard journals. A crank pin is connected between the inboard and outboard crank arms. An actuating rod has a first end rotatably coupled to the crank pin and a second end coupled to the flap bracket. Rotation of the crankshaft displaces the actuating rod to cause rotation of the flap bracket and the flap.

In order to improve linear drives on aircraft with regards to backlash, gear reduction, self-lock capability, load transfer and wear, a linear drive device is provided that has a first member with engaging teeth, such as a tooth rack and a second member which functions as a drive unit. The second member includes a plurality of movable teeth that are actuated by a cam shaft. The cam shaft has a control cam portion that is shaped such that the movable teeth perform a wave-like motion that forces the first member along its longitudinal direction relative to the second member.