A spoiler mechanism for an aircraft includes a spoiler fore-section and a spoiler aft-section. The spoiler fore-section includes a forward end configured to couple to a wing structure of an aircraft and a hinge end. The hinge end includes a first hinge coupling and a first retainer portion. The spoiler aft-section includes a second retainer portion and a second hinge coupling coupled to the first hinge coupling of the spoiler fore-section. The first retainer portion and the second retainer portion are configured to engage one another when the spoiler aft-section is aligned with the spoiler fore-section, and the first retainer portion and the second retainer portion are configured to disengage from one another responsive to the spoiler aft-section pivoting upward relative to the spoiler fore-section.

Provided are vertical tail structures with symmetry action slat systems. Specifically, a vertical tail structure comprises a main element and a leading edge element. The leading edge element comprises a first slat body and a second slat body that are symmetrically positioned on either side of a longitudinal centerline of the vertical tail structure. Each slat body is configured to move between a retracted position and an extended position to increase a camber sag of an airfoil of the vertical tail structure and thereby increase a maximum aerodynamic yawing moment provided by the vertical tail structure. In a first operable mode, each of the slat bodes are in the respective retracted position. In a second operable mode, one of the slat bodies is in the respective extended position. The extended position of each of the slat bodies includes a pitch angle and an extension distance from the main element.

A wing apparatus and aircraft are described providing greater maneuverability and efficiency for vertical takeoff and landing vehicles. Use of a fowler flap is shown in combination with a sliding panel. The sliding panel can nest within a wing similar to a fowler flap. During vertical maneuvers the sliding panel can be moved forward and on top of the wing. This can alleviate download during vertical maneuvers while minimizing drag as forward flight begins.

A wing apparatus and aircraft are described providing greater maneuverability and efficiency for vertical takeoff and landing vehicles. Use of a fowler flap is shown in combination with a sliding panel. The sliding panel can nest within a wing similar to a fowler flap. During vertical maneuvers the sliding panel can be moved forward and on top of the wing. This can alleviate download during vertical maneuvers while minimizing drag as forward flight begins.

Apparatus for obstructing air flow through an aperture in an aircraft wing where a movable anti-icing duct extends through the aperture are disclosed. An exemplary apparatus comprises a base member (40) configured to be secured to the duct and a first seal member (42) configured to obstruct air flow through the aperture. The first seal member comprises a proximal portion (42A) connected to the base member and a distal portion (42B) configured to movably contact an inner surface of a skin of the wing. The use of such apparatus may reduce the amount of leakage flow from the high pressure lower wing surface to the low pressure upper wing surface through the aperture and thereby reduce the loss of lift associated with such leakage flow.

Apparatus for obstructing air flow through an aperture in an aircraft wing where a movable anti-icing duct extends through the aperture are disclosed. An exemplary apparatus comprises a base member (40) configured to be secured to the duct and a first seal member (42) configured to obstruct air flow through the aperture. The first seal member comprises a proximal portion (42A) connected to the base member and a distal portion (42B) configured to movably contact an inner surface of a skin of the wing. The use of such apparatus may reduce the amount of leakage flow from the high pressure lower wing surface to the low pressure upper wing surface through the aperture and thereby reduce the loss of lift associated with such leakage flow.

Described herein is an auxiliary support system for a flap coupled to a wing of an aircraft. The auxiliary support system comprises a base fixable relative to the wing. The auxiliary support system also comprises a first track engagement assembly fixed to the base. The auxiliary support system further comprises a second track engagement assembly fixed to the base. The auxiliary support system additionally comprises a track arm attachable to the flap and comprising a first rail, movably engaged with the first track engagement assembly, and a second rail, movably engaged with the second track engagement assembly. The first rail is spaced apart from and non-parallel to the second rail.

Described herein is an auxiliary support system for a flap coupled to a wing of an aircraft. The auxiliary support system comprises a base fixable relative to the wing. The auxiliary support system also comprises a first track engagement assembly fixed to the base. The auxiliary support system further comprises a second track engagement assembly fixed to the base. The auxiliary support system additionally comprises a track arm attachable to the flap and comprising a first rail, movably engaged with the first track engagement assembly, and a second rail, movably engaged with the second track engagement assembly. The first rail is spaced apart from and non-parallel to the second rail.

A ducted wing is configured to be connected to an aircraft. The ducted wing includes an array of integrated jetfoils. Each jetfoil includes a propulsor fan, an upper wing portion, and a lower wing portion that extends past an end of the upper wing portion. Each jetfoil includes a duct formed between the upper wing portion and the lower wing portion where the propulsor is within the duct. Furthermore, each jetfoil may have one or more flaps at the leading edge or the trailing edge of the jetfoil. The jetfoil may have flaps that control either the inlet area or the outlet area of the propulsor fan as well as flaps that control whether the aircraft can operate in one of a plurality of different takeoff modes.

A ducted wing is configured to be connected to an aircraft. The ducted wing includes an array of integrated jetfoils. Each jetfoil includes a propulsor fan, an upper wing portion, and a lower wing portion that extends past an end of the upper wing portion. Each jetfoil includes a duct formed between the upper wing portion and the lower wing portion where the propulsor is within the duct. Furthermore, each jetfoil may have one or more flaps at the leading edge or the trailing edge of the jetfoil. The jetfoil may have flaps that control either the inlet area or the outlet area of the propulsor fan as well as flaps that control whether the aircraft can operate in one of a plurality of different takeoff modes.