Abstract: An apparatus for supporting a wing flap of an aircraft includes a support fitting configured to be coupled to a wing of the aircraft. The apparatus also includes a first link, pivotably coupled to the support fitting and configured to be pivotably coupled to the wing flap, and a second link, separably coupled to the support fitting and configured to be pivotably coupled to the wing flap.

Abstract: Structural composite airfoils include a primary structural element and a secondary structural element defining the trailing edge of the structural composite airfoil. The primary structural element includes an upper skin panel, a lower skin panel, and a middle C-channel spar that is coupled to the upper skin panel and the lower skin panel. The upper skin panel extends from an upper leading edge end to an upper trailing edge end, and the lower skin panel extends from a lower leading edge end to a lower trailing edge end. The lower leading edge end of the lower skin panel is coupled to the upper leading edge end of the upper skin panel within the leading edge region of the primary structural element.

Abstract: Structural composite airfoils include a primary structural element, a secondary structural element defining the trailing edge of the structural composite airfoil, and a discrete leading edge structure defining the leading edge of the structural composite airfoil. The primary structural element includes an upper skin panel, a lower skin panel, and a middle C-channel spar that is coupled to the upper skin panel and the lower skin panel. The discrete leading edge structure is coupled to the upper leading edge end of the upper skin panel and to the lower leading edge end of the lower skin panel. The upper skin panel may include a first panel bend adjacent the discrete leading edge structure, and the lower skin panel may include a second panel bend adjacent the discrete leading edge structure.

Abstract: Structural composite airfoils include a front C-channel spar having an upper flange coupled to an upper skin panel, and a lower flange coupled to a lower skin panel. The lower skin panel includes a joggle adjacent a lower leading edge end, with the joggle being positioned forward of the front C-channel spar. An upper skin surface of the lower leading edge end faces an internal volume defined between the upper skin panel and the lower skin panel. A lower skin surface of the lower leading edge end faces an internal surface of the upper leading edge end of the upper skin panel, and the lower leading edge end of the lower skin panel is coupled to the upper leading edge end of the upper skin panel forward of the front C-channel spar. The leading edge has a bullnose shape defined by the upper skin panel.

Abstract: Structural composite airfoils include a primary structural element and a secondary structural element defining a trailing edge of the structural composite airfoil. The primary structural element includes an upper skin panel, a lower skin panel, and a middle C-channel spar that is coupled to the upper skin panel and the lower skin panel. An upper flange of the middle C-channel spar is coupled to the upper skin panel, while a lower flange of the middle C-channel spar is coupled to the upper skin panel and the lower skin panel. An internal volume is defined by the upper skin panel and the lower skin panel aft of the middle C-channel spar, and is defined by the upper skin panel forward of the middle C-channel spar. The leading edge region of the primary structural element defines the leading edge of the structural composite airfoil.

Abstract: An apparatus for supporting a wing flap of an aircraft includes a support fitting configured to be coupled to a wing of the aircraft. The apparatus also includes a first link, pivotably coupled to the support fitting and configured to be pivotably coupled to the wing flap, and a second link, separably coupled to the support fitting and configured to be pivotably coupled to the wing flap.

Abstract: Structural composite airfoils include a front C-channel spar having an upper flange coupled to an upper skin panel, and a lower flange coupled to a lower skin panel. The lower skin panel includes a joggle adjacent a lower leading edge end, with the joggle being positioned forward of the front C-channel spar. An upper skin surface of the lower leading edge end faces an internal volume defined between the upper skin panel and the lower skin panel. A lower skin surface of the lower leading edge end faces an internal surface of the upper leading edge end of the upper skin panel, and the lower leading edge end of the lower skin panel is coupled to the upper leading edge end of the upper skin panel forward of the front C-channel spar. The leading edge has a bullnose shape defined by the upper skin panel.

Abstract: Structural composite airfoils include a primary structural element and a secondary structural element defining the trailing edge of the structural composite airfoil. The primary structural element includes an upper skin panel, a lower skin panel, and a middle C-channel spar that is coupled to the upper skin panel and the lower skin panel. The upper skin panel extends from an upper leading edge end to an upper trailing edge end, and the lower skin panel extends from a lower leading edge end to a lower trailing edge end. The lower leading edge end of the lower skin panel is coupled to the upper leading edge end of the upper skin panel within the leading edge region of the primary structural element.

Abstract: Structural composite airfoils include a primary structural element, a secondary structural element defining the trailing edge of the structural composite airfoil, and a discrete leading edge structure defining the leading edge of the structural composite airfoil. The primary structural element includes an upper skin panel, a lower skin panel, and a middle C-channel spar that is coupled to the upper skin panel and the lower skin panel. The discrete leading edge structure is coupled to the upper leading edge end of the upper skin panel and to the lower leading edge end of the lower skin panel. The upper skin panel may include a first panel bend adjacent the discrete leading edge structure, and the lower skin panel may include a second panel bend adjacent the discrete leading edge structure.

Abstract: Structural composite airfoils include a primary structural element and a secondary structural element defining a trailing edge of the structural composite airfoil. The primary structural element includes an upper skin panel, a lower skin panel, and a middle C-channel spar that is coupled to the upper skin panel and the lower skin panel. An upper flange of the middle C-channel spar is coupled to the upper skin panel, while a lower flange of the middle C-channel spar is coupled to the upper skin panel and the lower skin panel. An internal volume is defined by the upper skin panel and the lower skin panel aft of the middle C-channel spar, and is defined by the upper skin panel forward of the middle C-channel spar. The leading edge region of the primary structural element defines the leading edge of the structural composite airfoil.

Abstract: A structural composite airfoil includes a primary structural element, and a secondary structural element defining a trailing edge of the structural composite airfoil. The primary structural element includes an upper skin panel extending from an upper leading edge end to an upper trailing edge end, a lower skin panel extending from a lower leading edge end to a lower trailing edge end, and a bracket coupled to the upper skin panel. The leading edge region of the primary structural element has a bullnose shape defined by the upper skin panel. The lower skin panel includes an integrally formed front C-channel spar having an upper flange coupled to the upper skin panel. The upper flange is adjacent the lower leading edge end, and the integrally formed front C-channel spar is coupled to the bracket, thereby coupling the upper skin panel to the integrally formed front C-channel spar.

Abstract: Structural composite airfoils include a front C-channel spar having an upper flange coupled to an upper skin panel, and a lower flange coupled to a lower skin panel. The upper skin panel includes a joggle adjacent an upper leading edge end, with the joggle being positioned forward of the front C-channel spar. A lower skin surface of the upper leading edge end faces an internal volume defined between the upper skin panel and the lower skin panel. An upper skin surface of the upper leading edge end faces an internal surface of the lower leading edge end of the lower skin panel, and the upper leading edge end of the upper skin panel is coupled to the lower leading edge end of the lower skin panel forward of the front C-channel spar. The leading edge has a bullnose shape defined by the lower skin panel.

Abstract: A structural composite airfoil includes a primary structural element, and a secondary structural element defining a trailing edge of the structural composite airfoil. The primary structural element includes an upper skin panel extending from an upper leading edge end to an upper trailing edge end, a lower skin panel extending from a lower leading edge end to a lower trailing edge end, and a bracket coupled to the lower skin panel. The leading edge region of the primary structural element has a bullnose shape defined by the lower skin panel. The upper skin panel includes an integrally formed front C-channel spar having a lower flange coupled to the lower skin panel. The lower flange is adjacent the upper leading edge end, and the integrally formed front C-channel spar is coupled to the bracket, thereby further coupling the lower skin panel to the integrally formed front C-channel spar.

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: This disclosure is directed to a methodology for designing spoilers or droop panels and aerodynamic systems including the designed spoilers or the designed droop panels. The spoilers and the droop panels can be deployed on a wing with a flap system, which provides for trailing edge variable camber (TEVC) system. During flight, the fixed portions of the wing, the flaps, the spoilers and droop panels can all deform. The spoilers or the droop panels can each be pre-deformed to a first shape on the ground such that in flight the spoilers or the droop panels deform to a second shape under aerodynamic loads. In the second shape, the spoilers or the droop panels are configured to seal better against the flaps. The spoilers or the droop panels can be configured to seal to the flaps during all of the positions the flaps take as part of the TEVC system.

Abstract: A high-lift device surface and associated method of designing the high-lift device surface is described. Methods include entering one or more flight conditions, and receiving aerodynamic forces at a wing, the wing comprising a fixed portion, a seal coupled to and extending from the fixed portion of the wing, and a high-lift device surface having an as-built shape determined based on an anticipated deformation during flight. Methods also include deforming the high-lift device surface based, at least in part, on the received aerodynamic forces, contacting, based on the deforming, the high-lift device surface with the seal, wherein the deforming causes the high-lift device to deform from the as-built shape to a second shape, and wherein the contacting causes the high-lift device to fully contact the seal to prevent air flow between the seal and the high-lift device surface due to the received aerodynamic forces.

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 high-lift device surface and associated method of designing the high-lift device surface is described. The flap can be attached to a wing on aircraft. The method can involve determining a manufactured shape of the flap. The manufactured flap shape can be deflected in some manner, such as bent or twisted, so that under selected flight conditions, such as cruise, the manufactured flap shape morphs into a second desired shape that satisfies specified constraints, such as geometric and sealing constraints. An advantage of the approach is that the flap doesn't have to be mechanically forced, using mechanical elements, into the second desired shape. The elimination of the mechanical elements results in weight and cost savings to aircraft on which the flap is deployed.

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.