Abstract: Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a middle track connected to an aerodynamic surface and configured to move along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track are configured to interface with one or more outer surfaces of the plurality of intermediate tracks; a plurality of outer tracks, each including a flange and configured to interface with one or more inner surfaces of the plurality of intermediate tracks; and an actuator configured to control a position of the middle track and a position of the plurality of intermediate tracks via a plurality of linkages.

Abstract: Thermal anti-icing systems are disclosed. An example anti-icing system includes a housing defining an inner recess, a first support fitting, a second support fitting spaced away from the first support fitting. The housing is positioned between the first support fitting and the second support fitting. The first support fitting, the second support fitting and an outer wall of the housing define a heating chamber that is fluidly separated from the inner recess.

Abstract: Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a plurality of outer tracks, wherein each outer track of the plurality of outer tracks includes: an inner outer roller channel; and an outer inner roller channel positioned above the inner outer roller channel; an aerodynamic surface connected to a carrier, wherein the carrier includes rollers configured to move within inboard inner roller channels of the plurality of outer tracks; and a plurality of fixed rollers mounted to one or more longitudinal structural elements in an aerodynamic structure, wherein the plurality of fixed rollers are disposed within the outer roller channels of the plurality of outer tracks.

Abstract: Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a middle track connected to an aerodynamic surface and configured to move along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track are configured to interface with one or more outer surfaces of the plurality of intermediate tracks; a plurality of outer tracks, each including a flange and configured to interface with one or more inner surfaces of the plurality of intermediate tracks; and an actuator configured to control a position of the middle track and a position of the plurality of intermediate tracks via a plurality of linkages.

Abstract: Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a plurality of outer tracks, wherein each outer track of the plurality of outer tracks includes: an inner outer roller channel; and an outer inner roller channel positioned above the inner outer roller channel; an aerodynamic surface connected to a carrier, wherein the carrier includes rollers configured to move within inboard inner roller channels of the plurality of outer tracks; and a plurality of fixed rollers mounted to one or more longitudinal structural elements in an aerodynamic structure, wherein the plurality of fixed rollers are disposed within the outer roller channels of the plurality of outer tracks.

Abstract: A skin panel configured for attachment to an aircraft structure is constructed of a composite material and has a continuous, smooth outer surface; a continuous, smooth inner surface that is configured for attachment to an aircraft structure; a peripheral edge that extends entirely around the skin panel and has a continuous, smooth surface and a plurality of cavities inside the material of the skin panel. The cavities reduce the weight of the skin panel without significantly detracting from the compression strength and tensile strength of the skin panel.

Abstract: A flap support fairing system incorporates a fairing attached to a flap and deployed downward with the flap during flap extension. The fairing has an inboard butterfly portion mounted with an inboard hinge and an outboard butterfly portion mounted with in outboard hinge. A fairing deployment mechanism is responsive to flap extension and is configured to rotate the inboard butterfly portion laterally inboard about the inboard hinge relative to an airflow direction and to rotate the outboard butterfly portion laterally outboard about the outboard hinge relative to the airflow direction. Upon flap extension, rotation of the inboard and outboard butterfly portions reduces impingement of a core engine plume on the deployed fairing.

Abstract: A trailing edge flap actuation mechanism has a flap drive link with a first end pivotally coupled to a fore flap structure of a flap and a second end pivotally coupled to an underwing support structure. An aft tension link has a leading end pivotally coupled proximate an aft end of the underwing support structure and a trailing end coupled to a mid-section structure of the flap. An actuator, when actuated, rotates the flap drive link about a first pivot axle to move the flap between a retracted position and a deployed lowered position. The actuator, including a ball-screw drive shaft having a universal joint, is positioned in a cove above the underwing support structure whereby the extent that the underwing support structure protrudes below the wing is reduced.

Abstract: A flap support fairing system incorporates a fairing attached to a flap and deployed downward with the flap during flap extension. The fairing has an inboard butterfly portion mounted with an inboard hinge and an outboard butterfly portion mounted with in outboard hinge. A fairing deployment mechanism is responsive to flap extension and is configured to rotate the inboard butterfly portion laterally inboard about the inboard hinge relative to an airflow direction and to rotate the outboard butterfly portion laterally outboard about the outboard hinge relative to the airflow direction. Upon flap extension, rotation of the inboard and outboard butterfly portions reduces impingement of a core engine plume on the deployed fairing.

Abstract: A composite edge of an aircraft wing includes a composite wing box skin panel, attached to an outward wing spar in an attachment region, and a composite ramp, upon an outer surface of, and co-cured with, the composite wing box skin panel. The composite wing box skin panel has a proximal end and a distal end, with an overhanging edge, with substantially constant thickness and ply count in the attachment region. The composite ramp has a maximum ramp thickness at the distal end, the distal end being set back from the overhanging edge, defining a shoulder on the overhanging edge. A composite wing edge skin panel, having a thickness substantially equal to the maximum ramp thickness, is attached to the composite wing box skin panel at the shoulder and adjacent to the distal end of the ramp.

Abstract: A system for mechanical operation of an aircraft wing includes a torque tube rotatable at a first rate of rotation to cause a downward rotation of a control surface relative to the aircraft wing. A gearing assembly including an output shaft is coupled to the torque tube. The torque tube is configured to rotate the output shaft, via the gearing assembly, at a second rate of rotation less than the first rate of rotation. A rotational member is coupled to the output shaft, and the output shaft is configured to drive a rotation of the rotational member. A first end of a linear actuator is coupled to the rotational member at a forward attach point, which is eccentric to a rotational center of the rotational member. The rotational member is rotatable to cause a translation of the forward attach point relative to the aircraft wing.

Abstract: A wing flap includes a flap body and a torque member. The torque member is integrally formed with at least a portion of the flap body.

Abstract: A wing flap includes a flap body. The flap body includes an upper skin, a lower skin opposite the upper skin, and a plurality of spars that extend between the upper skin and the lower skin. The wing flap also includes a torque member that is coupled to the flap body. A portion of the torque member is contiguous with at least one of the upper skin and the lower skin.

Abstract: A trailing edge flap actuation mechanism has a flap drive link with a first end pivotally coupled to a fore flap structure of a flap and a second end pivotally coupled to an underwing support structure. An aft tension link has a leading end pivotally coupled proximate an aft end of the underwing support structure and a trailing end coupled to a mid-section structure of the flap. An actuator, when actuated, rotates the flap drive link about a first pivot axle to move the flap between a retracted position and a deployed lowered position. The actuator, including a ball-screw drive shaft having a universal joint, is positioned in a cove above the underwing support structure whereby the extent that the underwing support structure protrudes below the wing is reduced.

Abstract: A wing flap includes a flap body. The flap body includes an upper skin, a lower skin opposite the upper skin, and a plurality of spars that extend between the upper skin and the lower skin. The wing flap also includes a torque member that is coupled to the flap body. A portion of the torque member is contiguous with at least one of the upper skin and the lower skin.

Abstract: A wing assembly comprises a raked wing tip having an outboard portion hinged to one of a main wing having at least one moveable control surface and an inboard raked wing tip portion. The outboard portion of the raked wing tip does not carry any moveable flight control surfaces.

Abstract: An aerodynamic control surface including an upper panel having an upper panel aft end portion, a lower panel having a lower panel aft end portion, mechanical fasteners connecting the upper panel aft end portion to the lower panel aft end portion, and a fairing having a fairing forward end portion and a fairing aft end portion, wherein the fairing forward end portion is connected to either the upper panel or the lower panel, and wherein the fairing aft end portion is connected to the other of the upper panel or the lower panel.

Abstract: A wing flap includes a flap body. The flap body includes an upper skin, a lower skin opposite the upper skin, and a plurality of spars that extend between the upper skin and the lower skin. The wing flap also includes a torque member that is coupled to the flap body. A portion of the torque member is contiguous with at least one of the upper skin and the lower skin.

Abstract: A wing flap includes a flap body and a torque member. The torque member is integrally formed with at least a portion of the flap body.

Abstract: A wing flap includes a flap body. The flap body includes an upper skin, a lower skin opposite the upper skin, and a plurality of spars that extend between the upper skin and the lower skin. The wing flap also includes a torque member that is coupled to the flap body. A portion of the torque member is contiguous with at least one of the upper skin and the lower skin.