The present application discloses an aircraft. The aircraft comprises a first wing and a second wing, a fuselage to which the first wing and the second wing are mounted, a first engine operatively mounted to the first wing, and a second engine operatively mounted to the second wing. The aircraft is configured to vertically take-off and land. The first engine and the second engine are used for both (i) vertical take-off and landing, and (ii) horizontal flight.

The present application discloses an aircraft. The aircraft comprises a first wing and a second wing, a fuselage to which the first wing and the second wing are mounted, a first engine operatively mounted to the first wing, and a second engine operatively mounted to the second wing. The aircraft is configured to vertically take-off and land. The first engine and the second engine are used for both (i) vertical take-off and landing, and (ii) horizontal flight.

The present application discloses a method of assembling or disassembling an aircraft. The assembly method includes a mounting a first engine nacelle to a first wing, mounting a second engine nacelle to a second wing, causing the first wing to be extended relative to a center wing, and causing the second wing to be extended relative to the center wing.

The present application discloses a method of assembling or disassembling an aircraft. The assembly method includes a mounting a first engine nacelle to a first wing, mounting a second engine nacelle to a second wing, causing the first wing to be extended relative to a center wing, and causing the second wing to be extended relative to the center wing.

A repair device and method for repairing damage around the leading edge of a wind turbine blade (20) are provided. The repair device includes a robotic maintenance device (40) and an unmanned aerial vehicle (UAV) (62) that can move the maintenance device (40) between a storage position and an operation position, the former being mounted on a blade (20) of the wind turbine (10). The UAV (62) hovers and remains connected to the maintenance device (40) during operations at the blade (20) to minimize a total operational downtime needed to conduct the repair actions. The UAV (62) is secured to the maintenance device (40) by at least one support line (68) that carries the weight load of the maintenance device (40) and at least two control lines (72) that prevent undesired rotations of the maintenance device (40), thereby improving precision and accuracy of UAV-driven movements of the maintenance device (40). A transport container (24) may also be provided to define the storage position, the transport container (24) including an elongated slot (70) for guiding movement of the lines (68, 72) and the maintenance device (40) during movements into and out of a storage space within the container (24).

Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.

A modular UAV comprising a fuselage, wing panels, a stabilizer, and two booms with vertical stabilizer, each of the booms equipped with an adapter. The wing panels are configured so the adapters of the boom are connectable thereto to form a lock connection. A spar passes through the fuselage, and the wing panels include holders for the spar. Ends of the spar comprise adapters formed as tabs. The lock connection is formed by connection of a turn bushing having a transverse notch to a spring-loaded fastener positioned in each of the wing panels, and of each spar adapter to a respective boom adapter that is hook-shaped, while being fixable by an external lever rigidly coupled to the turn bushing. Each wing panel includes a torque pin coupled to a corresponding fuselage hole displaced along a fuselage axis relative to the spar.

A modular UAV comprising a fuselage, wing panels, a stabilizer, and two booms with vertical stabilizer, each of the booms equipped with an adapter. The wing panels are configured so the adapters of the boom are connectable thereto to form a lock connection. A spar passes through the fuselage, and the wing panels include holders for the spar. Ends of the spar comprise adapters formed as tabs. The lock connection is formed by connection of a turn bushing having a transverse notch to a spring-loaded fastener positioned in each of the wing panels, and of each spar adapter to a respective boom adapter that is hook-shaped, while being fixable by an external lever rigidly coupled to the turn bushing. Each wing panel includes a torque pin coupled to a corresponding fuselage hole displaced along a fuselage axis relative to the spar.

A modular UAV comprising a fuselage, wing panels, a stabilizer, and two booms with vertical stabilizer, each of the booms equipped with an adapter. The wing panels are configured so the adapters of the boom are connectable thereto to form a lock connection. A spar passes through the fuselage, and the wing panels include holders for the spar. Ends of the spar comprise adapters formed as tabs. The lock connection is formed by connection of a turn bushing having a transverse notch to a spring-loaded fastener positioned in each of the wing panels, and of each spar adapter to a respective boom adapter that is hook-shaped, while being fixable by an external lever rigidly coupled to the turn bushing. Each wing panel includes a torque pin coupled to a corresponding fuselage hole displaced along a fuselage axis relative to the spar.

Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.