An aircraft includes cruise propellers, lifting propellers, an energy battery and a power battery. The energy battery is electrically connected to the cruise propellers, and the power battery is electrically connected to the lifting propellers.

An aircraft includes a first battery, provisions for transport that are powered by a second battery, and a management system for transferring energy between the first battery and the second battery.

Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Systems, methods, and apparatus may actively adjust 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 unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one pre-set condition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one pre-set condition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one pre-set condition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.

An unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one pre-set condition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one pre-set condition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one pre-set condition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.

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.

Apparatus and methods for limiting trailing edge deflection in aircraft folding wing tips are disclosed herein. An example aircraft wing disclosed herein includes a fixed wing portion. The fixed wing portion includes an outboard rib. The aircraft wing also includes a wing tip moveably coupled to the fixed wing portion. The wing tip is moveable between an extended position and a folded position. The wing tip includes an inboard rib that is disposed in a trailing edge section of the wing tip. The wing tip includes a stop plate coupled to the inboard rib. The stop plate extends inboard from the inboard rib such that when the wing tip is in the extended position, the stop plate is disposed below a portion of the outboard rib of the fixed wing portion to limit upward deflection of the trailing edge section of the wing tip relative to the fixed wing portion.

Apparatus and methods for limiting trailing edge deflection in aircraft folding wing tips are disclosed herein. An example aircraft wing disclosed herein includes a fixed wing portion. The fixed wing portion includes an outboard rib. The aircraft wing also includes a wing tip moveably coupled to the fixed wing portion. The wing tip is moveable between an extended position and a folded position. The wing tip includes an inboard rib that is disposed in a trailing edge section of the wing tip. The wing tip includes a stop plate coupled to the inboard rib. The stop plate extends inboard from the inboard rib such that when the wing tip is in the extended position, the stop plate is disposed below a portion of the outboard rib of the fixed wing portion to limit upward deflection of the trailing edge section of the wing tip relative to the fixed wing portion.

An aircraft wing (1) has a wing tip device (3) joined thereto. The root (7) of the wing tip device (3) is joined to the tip of the wing (1) at a first connection (11). An external strut (9) extends between the wing (1) and the wing tip device (3), the strut (9) being joined to the wing (1) at a second connection (13). The second connection (13) is inboard of the first connection, such that loadings on the wing tip device (3) generated during use, are transferred, via the strut (9), to a location on the wing (1) that is inboard of where the root (7) of the wing tip device (3) is joined to the tip of the wing.

An aircraft wing (1) has a wing tip device (3) joined thereto. The root (7) of the wing tip device (3) is joined to the tip of the wing (1) at a first connection (11). An external strut (9) extends between the wing (1) and the wing tip device (3), the strut (9) being joined to the wing (1) at a second connection (13). The second connection (13) is inboard of the first connection, such that loadings on the wing tip device (3) generated during use, are transferred, via the strut (9), to a location on the wing (1) that is inboard of where the root (7) of the wing tip device (3) is joined to the tip of the wing.