Jam protection and alleviation for control surface linkage mechanisms

摘要

An aircraft comprising: a flight control surface and a rigid hinged panel both pivotably coupled to a wing; a drive linkage which links the flight control surface to the panel so that rotation of the former drives rotation of the latter, the drive linkage comprising first and second links, a first joint which pivotably couples the first and second links to each other, and a second joint which pivotably couples the first link to the flight control surface; and a cam track structure mounted to the wing, the cam track structure comprising first and second cam surfaces having extra run-out space at both ends thereof to prevent jamming. At least one of the links comprises a weakened portion which is designed to fail when a structural overload is produced due to jamming. Additional features can be added to the mechanism to block, shield, and shed other obstruction avenues.

主权项

1. An aircraft comprising:
an airfoil-shaped body; a flight control surface coupled to the airfoil-shaped body and comprising a leading edge; a flaperon catcher fitting comprising a flaperon catcher rib attached to the leading edge of the flight control surface and a pair of flaperon catcher plates attached to the rib by at least one fusing fastener designed to shear when a structural overload is produced due to jamming; a panel coupled to the airfoil-shaped body; a hinge attached to the panel; a drive linkage which couples the rib of the flaperon catcher fitting to the hinge, wherein the drive linkage comprises a first joint rotatably coupled to the hinge, a second joint, a third joint rotatably coupled to the flaperon catcher plates, first and second links having respective first ends rotatably coupled to the first joint and respective second ends rotatably coupled to the second joint, third and fourth links having respective first ends rotatably coupled to the second joint and respective second ends rotatably coupled to the third joint; an actuator pivotably coupled to the airfoil-shaped body and to the flight control surface, the flight control surface moving relative to the airfoil-shaped body in response to a force applied by the actuator; a cam track structure mounted to the airfoil-shaped body, the cam track structure comprising first and second cam surfaces; and an actuator relief valve that prevents the actuator from generating load greater than a relief valve setting, wherein a structural fuse capability of the fusing fasteners is set higher than an actuator capability at the relief valve setting, wherein the second and third joints of the drive linkage are trapped in the first and second cam surfaces respectively of the cam track structure, and wherein each of the first through fourth links comprises first and second link segments fastened together by first and second fusing fasteners which are designed to fail when a structural overload is produced due to jamming, whereby upon such failure the first and second link segments are free to rotate about the respective joints to which they are coupled so that the first and second link segments become misaligned.