A rotorcraft-convertible motorcar includes a passenger cabin with at least one seat, a pair of front wheels, a central rear wheel, and two pairs of left and right supporting arms located on opposed sides of the passenger cabin, each supporting arm carrying a respective rotor assembly. The supporting arms are pivotally connected to the passenger cabin so that the rotorcraft-convertible car is convertible between an on-road configuration, where the supporting arms with the rotor assemblies are arranged inside a lateral overall size of the passenger cabin, and a flight configuration, where the supporting arms with the rotor assemblies are arranged at least partially outside the overall lateral size of the passenger cabin. The supporting arms and the rotor assemblies are configured so that in the on-road configuration the rotor assemblies are accommodated underneath the passenger cabin, on opposed sides of the central rear wheel.

In one possible embodiment, an amphibious unmanned aerial vehicle is provided, which includes a fuselage comprised of a buoyant material. Separators within the fuselage form separate compartments within the fuselage. Mounts associated with the compartments for securing waterproof aircraft components within the fuselage. The compartments each have drainage openings in the fuselage extending from the interior of the fuselage to the exterior of the fuselage.

An unmanned aerial vehicle kit and a system according to various embodiments of the present invention comprise a first assembly and a second assembly. The first assembly comprises: a housing comprising a processor and a navigation system; at least one first propeller which is connected to or mounted on the housing, and which has a direction set such that the same rotates about a first axis extending in a first direction; at least one first motor which drives the at least one first propeller, and which is configured to be controlled by at least one of the processor and the navigation system; and at least one first electric contact electrically connected to the processor. The second assembly comprises: a frame that can be connected to the first assembly in an attachable/detachable manner; at least one second electric contact that can be electrically connected to the at least one first electric contact when the frame is connected to the first assembly; at least one second propeller which is connected to or mounted on the frame, and which has a direction set such that the same rotates about a second axis that is different from the first axis; and at least one second motor which drives the at least one second propeller, and which is configured to be controlled by at least one of the processor and the navigation system. At least one of the processor and the navigation system is configured to selectively drive the first motor or the second motor according to whether the second assembly has been connected to the first assembly or not, and the first assembly can accordingly transfer a control signal corresponding to the type of the second assembly to the second assembly. Various embodiments other than the embodiments disclosed in the present specification are also possible.

An unmanned aerial vehicle has a flight mode and a compact storage mode. The unmanned aerial vehicle includes an airframe having first and second wings with first and second pylons extending therebetween. A thrust array is coupled to the airframe including two propulsion assemblies coupled to each of the first and second wings. An electric power system is operably associated with the thrust array and operable to provide power to each propulsion assembly. A flight control system is operably associated with the thrust array and operable to independently control the speed of each propulsion assembly. In the flight mode, the first and second wings are substantially parallel with the vertical dimension therebetween at a maximum. In the compact storage mode, the first and second pylons are rotated relative to the first and second wings such that the vertical dimension between the first and second wings is at a minimum.

An unmanned aerial vehicle (UAV) has a flight-only mode with a motor only rotating propellers and not rotating on-board wheels to configure the UAV to fly away from a surface of a structure, and a crawling-only mode in which the UAV is configured to crawl on the surface due to the motor only rotating the wheels while not rotating the propellers. In the flight-only mode, a clutch disengages a motor from the wheels so that the motor only engages the propellers to fly to lift from the surface. In the crawling-only mode, the clutch disengages the motor from the propellers so that the motor only engages the wheels to move the UAV on the surface.

An unmanned aerial vehicle (UAV) has a flight-only mode with a motor only rotating propellers and not rotating on-board wheels to configure the UAV to fly away from a surface of a structure, and a crawling-only mode in which the UAV is configured to crawl on the surface due to the motor only rotating the wheels while not rotating the propellers. In the flight-only mode, a clutch disengages a motor from the wheels so that the motor only engages the propellers to fly to lift from the surface. In the crawling-only mode, the clutch disengages the motor from the propellers so that the motor only engages the wheels to move the UAV on the surface.

An unmanned vehicle includes a body, at least one power source coupled to the body, a flight propulsion system coupled to the at least one power source and configured to propel the unmanned vehicle through air, and a surface propulsion system coupled to the at least one power source and configured to propel the unmanned vehicle along a surface. The unmanned vehicle is configured to switch between a flight configuration in which the unmanned vehicle is propelled through air via the flight propulsion system, and a surface traverse configuration in which the unmanned vehicle is propelled along the surface via the surface propulsion system. In the surface traverse configuration, the surface propulsion system is configured to engage the surface and to maintain the body in a traversing position below the surface as the surface propulsion system propels the unmanned vehicle along the surface.

An unmanned vehicle includes a body, at least one power source coupled to the body, a flight propulsion system coupled to the at least one power source and configured to propel the unmanned vehicle through air, and a surface propulsion system coupled to the at least one power source and configured to propel the unmanned vehicle along a surface. The unmanned vehicle is configured to switch between a flight configuration in which the unmanned vehicle is propelled through air via the flight propulsion system, and a surface traverse configuration in which the unmanned vehicle is propelled along the surface via the surface propulsion system. In the surface traverse configuration, the surface propulsion system is configured to engage the surface and to maintain the body in a traversing position below the surface as the surface propulsion system propels the unmanned vehicle along the surface.

A tunnel operation robot includes a robot body, a walking module, a fixed wing module and a plurality of rotatable wing modules. Both sides of the robot body are provided with cantilever parts, which are collinearly arranged. The walking module is arranged on the robot body. The fixed wing module includes a fixed fan, is fixedly arranged on the robot body, and is configured to provide a pressure for the walking module to be attached to and pressed against the tunnel wall surface. The plurality of rotatable wing modules are respectively arranged on the cantilever parts on both sides of the robot body, and include a rotatable rotating fan and a wind direction adjustment driver. Each rotating fan has a rotation axis parallel to the cantilever parts and an air outlet direction perpendicular to the cantilever parts, and the wind direction adjustment driver is connected to the rotating fan.

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.