A lift-changing mechanism is configured to change generated by a wing of an aircraft and includes a slit and an opening and closing member. The slit extends in a wingspan direction inside the wing and forms openings on the lower surface of the wing and on the upper surface of the wing respectively. A part of airflow below the lower surface is allowed to flow toward the upper surface through the slit. The opening and closing member is configured to open and close the slit. When the opening and closing member opens the slit, lift generated on the wing is decreased compared with when the slit is closed.

A lift-changing mechanism is configured to change generated by a wing of an aircraft and includes a slit and an opening and closing member. The slit extends in a wingspan direction inside the wing and forms openings on the lower surface of the wing and on the upper surface of the wing respectively. A part of airflow below the lower surface is allowed to flow toward the upper surface through the slit. The opening and closing member is configured to open and close the slit. When the opening and closing member opens the slit, lift generated on the wing is decreased compared with when the slit is closed.

Continuous skin leading edge slats are disclosed. A disclosed example leading edge slat for use with an aircraft includes a single-piece nose skin defining upper and lower external surfaces of the leading edge slat, where the single-piece nose skin is to extend between a fore end and an aft end of the leading edge slat, and a box spar coupled to an inner surface of the single-piece nose skin. The box spar includes lateral walls extending away from the inner surface of the single-piece nose skin. The lateral walls define at least one compartment of the box spar.

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.

Assemblies for air vehicle control surfaces and related methods are disclosed. An example apparatus includes a control surface; a bullnose carried by the control surface, the bullnose moveable relative to the control surface; a first actuator operatively coupled to the control surface to cause the control surface to rotate; and a second actuator operatively coupled to the control surface, the second actuator to cause the bullnose to move from a first position to a second position to cause an opening to be formed relative to the control surface, the movement of the bullnose independent of rotation of the control surface.

A wing for an aircraft, comprising a fixed wing, a foldable wing tip portion mounted to the fixed wing via a first hinge rotatably about a first hinge axis between an extended and folded positions, and an actuation unit to actuate the foldable wing tip portion for movement about the first hinge axis. The actuation unit comprises a link, a first and a second linear actuator. The link is rotatably mounted to the fixed wing via a second hinge, the first linear actuator is rotatably mounted to the fixed wing via a third hinge spaced from the second hinge, and is rotatably mounted to the link via a fourth hinge spaced from the second hinge. The second linear actuator is rotatably mounted to the foldable wing tip portion via a fifth hinge, and is rotatably mounted to the link via a sixth hinge spaced from the second hinge.

A wing for an aircraft, comprising a fixed wing, a foldable wing tip portion mounted to the fixed wing via a first hinge rotatably about a first hinge axis between an extended and folded positions, and an actuation unit to actuate the foldable wing tip portion for movement about the first hinge axis. The actuation unit comprises a link, a first and a second linear actuator. The link is rotatably mounted to the fixed wing via a second hinge, the first linear actuator is rotatably mounted to the fixed wing via a third hinge spaced from the second hinge, and is rotatably mounted to the link via a fourth hinge spaced from the second hinge. The second linear actuator is rotatably mounted to the foldable wing tip portion via a fifth hinge, and is rotatably mounted to the link via a sixth hinge spaced from the second hinge.

An aircraft wing is provided with a shutter mechanism to close a cut-out opening in the leading edge of the wing when a leading edge wing slat associated with the wing leading edge is moved to a deployed condition.

An aircraft wing is provided with a shutter mechanism to close a cut-out opening in the leading edge of the wing when a leading edge wing slat associated with the wing leading edge is moved to a deployed condition.