A water sampling method includes acquiring, by an unmanned aerial vehicle, a sampling depth at which a water sample is to be taken. The sampling depth is sent by a portable electronic device or is a preset default depth. The method further includes calculating a descending distance based on the sampling depth and a distance between the unmanned aerial vehicle and a water surface, controlling the water sampler to descend for the descending distance, sampling, by the water sampler, a water sample, and sending a sampling result to a ground station or the portable electronic device.

A UAV with vertical takeoff and landing (VTOL) function having a plurality of lift propellers; a cabin engaged with a plurality of lift propellers; a water propulsion system engaged with the cabin to push the cabin in a forward direction when the cabin is at least partially immersed in water; at least one water inlet engaged with the water propulsion system; the cabin is a cargo hold or a passenger cabin. The UAV provided by the disclosure can realize vertical takeoff and landing in the water area, and fly, drive and navigate freely in the whole area.

The present invention relates to an unmanned vehicle including:—a vehicle chassis (2) that has at least one actuator (3) involved in the driveability of the vehicle (1);—a set of on-board electronic components, namely at least one on-board electronic/computer control system;—a telecommunication unit; and—a geolocation unit. According to the invention, the on-board electronic components are arranged within a carrier so as to form, together, a removable technical unit (5) that is removably mounted on the vehicle chassis (2). The technical unit (5) and the vehicle chassis (2) include a mechanical/electrical interface unit (7) that are suitable, on one hand, for the releasable mechanical attachment of the removable technical unit (5) to the vehicle chassis (2) and, on the other hand, for the releasable electrical connection of the technical unit (5) to the at least one driveability actuator (3).

The present invention relates to an unmanned vehicle including:—a vehicle chassis (2) that has at least one actuator (3) involved in the driveability of the vehicle (1);—a set of on-board electronic components, namely at least one on-board electronic/computer control system;—a telecommunication unit; and—a geolocation unit. According to the invention, the on-board electronic components are arranged within a carrier so as to form, together, a removable technical unit (5) that is removably mounted on the vehicle chassis (2). The technical unit (5) and the vehicle chassis (2) include a mechanical/electrical interface unit (7) that are suitable, on one hand, for the releasable mechanical attachment of the removable technical unit (5) to the vehicle chassis (2) and, on the other hand, for the releasable electrical connection of the technical unit (5) to the at least one driveability actuator (3).

The invention provides a firefighting float plane having a fuselage and two floats mounted to the fuselage. The fuselage has a water tank with open and closed configurations. In some embodiments, the water tank is integrated into the fuselage, and/or both the water tank and the fuselage have a generally triangular cross-sectional configuration. The water tank has a closed bottom in its closed configuration and an open bottom in its open configuration. In some embodiments, the plane has specified ratio of water tank holding capacity to total power of two engine assemblies. It can optionally also have the above-noted fuselage configuration, tank configuration, or both. In some embodiments, the plane has dual propellers, two engine assemblies, and two tail booms, optionally together with specified ratio of water tank holding capacity to total power of two engine assemblies. It may also have the above-noted fuselage configuration, tank configuration, or both.

The invention provides a firefighting float plane having a fuselage and two floats mounted to the fuselage. The fuselage has a water tank with open and closed configurations. In some embodiments, the water tank is integrated into the fuselage, and/or both the water tank and the fuselage have a generally triangular cross-sectional configuration. The water tank has a closed bottom in its closed configuration and an open bottom in its open configuration. In some embodiments, the plane has specified ratio of water tank holding capacity to total power of two engine assemblies. It can optionally also have the above-noted fuselage configuration, tank configuration, or both. In some embodiments, the plane has dual propellers, two engine assemblies, and two tail booms, optionally together with specified ratio of water tank holding capacity to total power of two engine assemblies. It may also have the above-noted fuselage configuration, tank configuration, or both.

Provided is a taxiing system for steering an amphibious aircraft on a body of water with a steering means, a control console and a power source all in operable and electrical communication. The steering means is a jet drive coupled to an impeller assembly mounted inside each float. Alternatively the steering means is a propulsion system with a pair of tunnel-type thrusters mounted inside the floats in the aircraft. The control console operates the taxiing system during steering and at least one electromagnetic lock during docking.

Provided is a taxiing system for steering an amphibious aircraft on a body of water with a steering means, a control console and a power source all in operable and electrical communication. The steering means is a jet drive coupled to an impeller assembly mounted inside each float. Alternatively the steering means is a propulsion system with a pair of tunnel-type thrusters mounted inside the floats in the aircraft. The control console operates the taxiing system during steering and at least one electromagnetic lock during docking.

The present invention relates to a multipurpose and long endurance Hybrid Unmanned Aerial Vehicle (HUAV) with the combined functions of a Vertical Take-off and Landing (VTOL) and a fixed wing operation. The HUAV may take-off and land vertically on both land and water, and perform a mid-air transition from a VTOL mode to a fixed wing mode. The HUAV includes an airframe, a fixed wing unit having at least one forward thrust motor, one or more VTOL units mounted on a tail boom, and a fuselage of the airframe. Each of the one or more VTOL units includes at least one VTOL motor, and a control unit configured to control on-board transition of the HUAV between the VTOL mode and the fixed wing mode by controlling at least one forward thrust motor and at least one VTOL motor.

The present invention relates to a multipurpose and long endurance Hybrid Unmanned Aerial Vehicle (HUAV) with the combined functions of a Vertical Take-off and Landing (VTOL) and a fixed wing operation. The HUAV may take-off and land vertically on both land and water, and perform a mid-air transition from a VTOL mode to a fixed wing mode. The HUAV includes an airframe, a fixed wing unit having at least one forward thrust motor, one or more VTOL units mounted on a tail boom, and a fuselage of the airframe. Each of the one or more VTOL units includes at least one VTOL motor, and a control unit configured to control on-board transition of the HUAV between the VTOL mode and the fixed wing mode by controlling at least one forward thrust motor and at least one VTOL motor.