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.

A multi-monocopter system is provided, including a plurality of monocopters. Each monocopter includes: a flight controller, disposed on a housing member, operable to control a flight of the monocopter in an individual flight mode and a flight of the plurality of monocopters collectively in a cooperative flight mode; a wing member; a thrust unit; and a magnetic connector coupled to the housing member. The magnetic connector is configured to be connectable to corresponding magnetic connectors of other monocopters of the plurality of monocopters via a magnetic force to operate in the cooperative flight mode. When in the cooperative flight mode during flight, the flight controller is operable to control a rotational speed of the plurality of monocopters collectively to produce a centrifugal force that exceeds the magnetic force for separating the plurality of monocopters connected via the magnetic force to convert the cooperative flight mode to the individual flight mode.

A multi-monocopter system is provided, including a plurality of monocopters. Each monocopter includes: a flight controller, disposed on a housing member, operable to control a flight of the monocopter in an individual flight mode and a flight of the plurality of monocopters collectively in a cooperative flight mode; a wing member; a thrust unit; and a magnetic connector coupled to the housing member. The magnetic connector is configured to be connectable to corresponding magnetic connectors of other monocopters of the plurality of monocopters via a magnetic force to operate in the cooperative flight mode. When in the cooperative flight mode during flight, the flight controller is operable to control a rotational speed of the plurality of monocopters collectively to produce a centrifugal force that exceeds the magnetic force for separating the plurality of monocopters connected via the magnetic force to convert the cooperative flight mode to the individual flight mode.

Disclosed are devices, systems and methods for mission-adaptable aerial vehicle. In some aspects, a mission-adaptable aerial vehicle includes a configuration having swappable, manipulatable, and interchangeable sections and components connectable by a connection and fastening system able to be modified by an end-user in the field. In some embodiments, a mission-adaptable aerial vehicle can be configured to include a main center body extending along a longitudinal direction, a wing with a lateral cross-sectional airfoil shape, and/or stabilizer and control surface structures with corresponding cross-sectional airfoil shapes.

A vertical take-off and landing vehicle (100) includes a hollow fuselage (102) accommodating a power source (112-1,112-2); a fixed wing (106) is perpendicularly configured on the hollow fuselage (102) which accommodates avionics; a payload (110) detachably fixed to a mounting holder (108) of the fixed wing (106) through a vertical cavity (104) of the hollow fuselage (102). The fixed-wing (106) configured on the hollow fuselage (102) enables electrical communication from the power source (112-1,112-2) to the avionics for lifting and vertical landing of the payload (110) by the vehicle (100). An unmanned aerial vehicle (UAV) (200) includes a fuselage (202) having a tail rotor (204) inclinedly positioned where a rotational axis of the tail rotor (204) is positioned at a first predefined angle (X) relative to a horizontal axis of the fuselage (202) for providing axial thrust to facilitate horizontal movement of the UAV (200) and aerodynamics with reduced drag.

A vertical take-off and landing vehicle (100) includes a hollow fuselage (102) accommodating a power source (112-1,112-2); a fixed wing (106) is perpendicularly configured on the hollow fuselage (102) which accommodates avionics; a payload (110) detachably fixed to a mounting holder (108) of the fixed wing (106) through a vertical cavity (104) of the hollow fuselage (102). The fixed-wing (106) configured on the hollow fuselage (102) enables electrical communication from the power source (112-1,112-2) to the avionics for lifting and vertical landing of the payload (110) by the vehicle (100). An unmanned aerial vehicle (UAV) (200) includes a fuselage (202) having a tail rotor (204) inclinedly positioned where a rotational axis of the tail rotor (204) is positioned at a first predefined angle (X) relative to a horizontal axis of the fuselage (202) for providing axial thrust to facilitate horizontal movement of the UAV (200) and aerodynamics with reduced drag.

A craft is provided comprising: a propulsion system; a fuselage coupled with the propulsion system, wherein the fuselage is configured to carry a payload and fuel for the propulsion system; and a pre-assembled wing coupled with the fuselage; wherein the craft is designed to take-off without using a runway and does not have landing gear to land.

A craft is provided comprising: a propulsion system; a fuselage coupled with the propulsion system, wherein the fuselage is configured to carry a payload and fuel for the propulsion system; and a pre-assembled wing coupled with the fuselage; wherein the craft is designed to take-off without using a runway and does not have landing gear to land.