Abstract: Aerodynamic structures and methods of forming aerodynamic structures are disclosed herein. The aerodynamic structures include a first skin region that includes a first skin edge and a second skin region that includes a second skin edge. The first skin region and the second skin region are angled relative to one another and define a gap between the first skin edge and the second skin edge. The aerodynamic structures also include a trailing edge structure that extends within the gap and between the first skin edge and the second skin edge. The aerodynamic structures further include a plurality of blind fasteners. A first subset of the plurality of blind fasteners operatively interconnects the first skin region and the trailing edge structure. A second subset of the plurality of blind fasteners operatively interconnects the second skin region and the trailing edge structure. The methods include methods of forming the aerodynamic structures.

Abstract: A method of using a split winglet includes providing an aircraft having a winglet attach fitting attaching a split winglet to a wing. The split winglet has an upper winglet and a lower winglet. The method additionally includes maintaining the winglet attach fitting and winglet at a first height relative to a fuselage when the aircraft is non-flying, and moving the winglet attach fitting and winglet to a second height relative to the fuselage when the aircraft is flying, the second height being higher than the first height.

Abstract: A manufacture and process for a winglet formed as a unitary structure by laying up and co-curing three ply-sets in a bifurcated configuration, without metal and fasteners, comprising three continuous surfaces: a first ply-set comprising a first continuous surface forming: an outboard surface of an upper blade; an outboard portion of a root region; and an outboard surface of a lower blade; a second ply-set forming a second continuous surface forming an inboard surface of the upper blade and an upper skin of the root region; and a third ply-set forming a third continuous surface forming an inboard surface of the lower blade and a lower skin of the root region . . . continuous surface. The root region being integral in the bifurcated configuration, matching a shape of an airfoil of a tip of a wing, and comprising two supports that comprise an additional ply-set shaped to receive an attachment system.

Abstract: Drainage devices intended to prevent the reentry of drained fluids, the devices including a base having a contact surface for mounting over a drainage opening in an aerodynamic surface, a mast portion connected to the base and extending away from the contact surface of the base, and a top portion connected to the end of the mast portion, the top portion having a periphery that is greater than the periphery of the mast portion and including an exit port. The top portion may include a cantilevered fence portion extending upstream relative to the aerodynamic surface, and the drainage devices may be part of a system including a first opening and a second opening in the aerodynamic surface, the second opening upstream from the first opening, where a drainage device is mounted over the first opening and the cantilevered fence portion of the drainage device extends upstream toward the second opening.

Abstract: A method of using a split winglet includes providing an aircraft having a winglet attach fitting attaching a split winglet to a wing. The split winglet has an upper winglet and a lower winglet. The method additionally includes maintaining the winglet attach fitting and winglet at a first height relative to a fuselage when the aircraft is non-flying, and moving the winglet attach fitting and winglet to a second height relative to the fuselage when the aircraft is flying, the second height being higher than the first height.

Abstract: Provided is an aircraft propulsor thrust reverser with a fastening system. The fastening system may include a male spool and a female spool configured to be threaded into the male spool. The male spool and the female spool may be coupled to a honeycomb structure and may evenly distribute force to the honeycomb structure to prevent plastic deformation of a honeycomb core of the honeycomb structure.

Abstract: A method of securing a split winglet to a wing tip of an aircraft includes fastening an upper winglet to an upper winglet attachment portion of a wing attach fitting having a wing attachment portion. The method further includes fastening a lower winglet to a lower winglet attachment portion of the wing attach fitting. The method additionally includes fastening the wing attachment portion to the wing tip using tension fasteners installed from an inboard side of the wing tip to secure the split winglet to the wing.

Abstract: A tooling apparatus for manufacturing a composite structure may include a rigid outer tool for receiving a composite layup, a tubular inner vacuum bag in contact with the composite layup and defining an inner vacuum chamber, and an outer vacuum bag covering at least a portion of the rigid outer tool. The outer vacuum bag and the tubular inner vacuum bag may collectively define an outer vacuum chamber containing the composite layup. An outer bag vacuum source may be fluidly coupled to the outer vacuum bag for applying an outer bag vacuum pressure on the outer vacuum chamber. An inner bag vacuum source may be fluidly coupled to the tubular inner vacuum bag for applying an inner bag vacuum pressure on the inner vacuum chamber during application of the outer bag vacuum pressure on the outer vacuum chamber.

Abstract: Drainage devices intended to prevent the reentry of drained fluids, the devices including a base having a contact surface for mounting over a drainage opening in an aerodynamic surface, a mast portion connected to the base and extending away from the contact surface of the base, and a top portion connected to the end of the mast portion, the top portion having a periphery that is greater than the periphery of the mast portion and including an exit port. The top portion may include a cantilevered fence portion extending upstream relative to the aerodynamic surface, and the drainage devices may be part of a system including a first opening and a second opening in the aerodynamic surface, the second opening upstream from the first opening, where a drainage device is mounted over the first opening and the cantilevered fence portion of the drainage device extends upstream toward the second opening.

Abstract: Systems and methods are provided for an aircraft propulsor thrust reverser with a fastening system. The fastening system may include a male spool and a female spool configured to be threaded into the male spool. The male spool and the female spool may be coupled to a honeycomb structure and may evenly distribute force to the honeycomb structure to prevent plastic deformation of a honeycomb core of the honeycomb structure.

Abstract: A method and apparatus for forming a winglet formed as a one-piece composite for an aircraft is presented. The winglet comprises a first blade, a second blade, and a root region. The first blade includes a first leading edge and a first trailing edge. The second blade includes a second leading edge and a second trailing edge. The second blade is positioned at an angle to the first blade. The root region is co-cured with the first blade and the second blade to form the winglet. The root region is configured to receive an attachment system for attaching the winglet to a wing of the aircraft.

Abstract: A tooling apparatus for manufacturing a composite structure may include a rigid outer tool for receiving a composite layup, a tubular inner vacuum bag in contact with the composite layup and defining an inner vacuum chamber, and an outer vacuum bag covering at least a portion of the rigid outer tool. The outer vacuum bag and the tubular inner vacuum bag may collectively define an outer vacuum chamber containing the composite layup. An outer bag vacuum source may be fluidly coupled to the outer vacuum bag for applying an outer bag vacuum pressure on the outer vacuum chamber. An inner bag vacuum source may be fluidly coupled to the tubular inner vacuum bag for applying an inner bag vacuum pressure on the inner vacuum chamber during application of the outer bag vacuum pressure on the outer vacuum chamber.

Abstract: A method and apparatus for forming a composite winglet for an aircraft is presented. The composite winglet comprises a first blade, a second blade, and a root region. The first blade includes a first leading edge and a first trailing edge. The second blade includes a second leading edge and a second trailing edge. The second blade is positioned at an angle to the first blade. The root region is co-cured with the first blade and the second blade to form the composite winglet. The root region is configured to receive an attachment system for attaching the composite winglet to a wing of the aircraft.

Abstract: A method of securing a split winglet to a wing tip of an aircraft includes fastening an upper winglet to an upper winglet attachment portion of a wing attach fitting having a wing attachment portion. The method further includes fastening a lower winglet to a lower winglet attachment portion of the wing attach fitting. The method additionally includes fastening the wing attachment portion to the wing tip using tension fasteners installed from an inboard side of the wing tip to secure the split winglet to the wing.

Abstract: A winglet attach fitting may include a wing attachment portion, an upper winglet attachment portion, and a lower winglet attachment portion. The upper winglet attachment portion may be coupled to the wing attachment portion and may be configured to support an upper winglet. The lower winglet attachment portion may be coupled to the wing attachment portion and may be configured to support a lower winglet. The wing attachment portion may be removably attachable to a wing tip using fasteners.

Abstract: A method and apparatus for forming a composite winglet for an aircraft is presented. The composite winglet comprises a first blade, a second blade, and a root region. The first blade includes a first leading edge and a first trailing edge. The second blade includes a second leading edge and a second trailing edge. The second blade is positioned at an angle to the first blade. The root region is co-cured with the first blade and the second blade to form the composite winglet. The root region is configured to receive an attachment system for attaching the composite winglet to a wing of the aircraft.