The present invention provides a foldable wing which comprises a wing supporting skeleton, a sliding rail, a skin supporting rib, a skin and a wing movement unit. The wing supporting skeleton comprises a horizontal beam, a longitudinal beam, a wing front edge beam, a wing trailing edge beam, a fixture connector and a sliding block, The wing supporting skeleton is a triangular girder for maintaining planar and sectional shapes of the foldable wing, supporting the skin supporting rib and the skin, and sustaining an aerodynamic load from the skin and a load of a fuselage. After the triangular girder is subjected to a force of the wing movement unit, a shape and an area of the triangular girder are changed so as to achieve folding and unfolding of the foldable wing. A rotocraft and a glider using the foldable wing are also provided.

Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Disclosed are systems, methods, and apparatus for actively adjusting the position and/or configuration of one or more propeller blades of a propulsion mechanism to generate different sounds and/or lifting forces from the propulsion mechanism.

Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Disclosed are systems, methods, and apparatus for actively adjusting the position and/or configuration of one or more propeller blades of a propulsion mechanism to generate different sounds and/or lifting forces from the propulsion mechanism.

Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Disclosed are systems, methods, and apparatus for actively adjusting the position and/or configuration of one or more propeller blades of a propulsion mechanism to generate different sounds and/or lifting forces from the propulsion mechanism.

An aircraft is disclosed having a wing, the wing having a fixed wing with a wing tip device moveably mounted about a hinge at the tip thereof. The wing tip device is operable between a flight configuration, and a load alleviating configuration for load alleviation during flight. The aircraft includes a restraining assembly operable between a restraining mode in which the wing tip device is held in the flight configuration using a restraining force such as by a brake, and a releasing mode in which the restraining force on the wing tip device is released, such that the wing tip device may adopt the load alleviating configuration.

Methods, apparatus, and articles of manufacture to control and monitor a folding wingtip actuation system are disclosed. An example apparatus includes a sequence and control module to determine whether to control a movement of a folding wingtip assembly coupled to a wing of an aircraft, the sequence and control module is to determine actions during a first stage and a second stage to complete in sequence to move the folding wingtip assembly, determine a status of a first component of the folding wingtip assembly based on a sensor measurement, in response to the status being a non-responsive status, replace a first input from the first component with a second input from a second component, and control the movement of the folding wingtip assembly based on the actions and the second input.

An air mobility may include a wing portion extending from a fuselage of the air mobility; a folded portion provided at an edge portion of the wing portion, configured to extend from the wing portion to form a part of the wing portion during unfolding of the folded portion, and configured to move to overlap with the wing portion during folding of the folded portion, so that an area of air resistance in a vertical direction of the wing portion is reduced; an actuator connected to the folded portion and configured to provide power to the folded portion, so that the folded portion is unfolded or folded to the wing portion; and a controller connected to the actuator and configured to control the actuator, so that the folded portion is folded during vertical takeoff or landing of the fuselage, and configured to control the actuator to unfold the folded portion during cruising of the fuselage.

An aircraft with wing tip devices, for example, folding wing tips, is disclosed. The folding wing tip may have a flight configuration for use during flight, and a ground configuration for use in ground-based operations. The ground configuration creates a shorter wing span than when the aircraft is in the flight configuration. A hinge arrangement protrudes beyond an outer surface of the fixed wing and wing tip device. In order to reduce the aerodynamic effect of the protruding hinge a fairing may be provided. In the flight configuration the fairing comprises a rear portion with a concave surface, such that the fairing acts as a lift-generating surface when the aircraft is in flight.

This invention discloses a new foil design for generating and changing lift in a fluid dynamic environment. The vessel/aircraft can change foil's lift coefficient by using independently rotatable and locking tubes with at least one flat area attached to axles which enables modification of the surface conformation of the foil. The foil is provided with means to control a pitch, a roll and a yaw motion and to control the position and stability of the aircraft. In one embodiment the foil is capable of maintaining lift upon inversion, or flipping of a vessel. In another embodiment the invention provides a novel device and methodology for modifying foil surface configurations for in-motion fluid dynamic efficiency.

This invention discloses a new foil design for generating and changing lift in a fluid dynamic environment. The vessel/aircraft can change foil's lift coefficient by using independently rotatable and locking tubes with at least one flat area attached to axles which enables modification of the surface conformation of the foil. The foil is provided with means to control a pitch, a roll and a yaw motion and to control the position and stability of the aircraft. In one embodiment the foil is capable of maintaining lift upon inversion, or flipping of a vessel. In another embodiment the invention provides a novel device and methodology for modifying foil surface configurations for in-motion fluid dynamic efficiency.