An unmanned aerial vehicle (UAV) is described. The UAV includes a first battery to power multiple first and multiple second electronic components of UAV. A power consumption of each first electronic component is greater than a power threshold. A power consumption of each second electronic component is less than or equal to the power threshold. The UAV includes a generator and a battery management system (BMS). The generator generates an electrical power through rotation of a shaft of a motor of UAV. The BMS charges the first battery using the electrical power generated by the generator when the UAV is during operation and a stored charge of the first battery drops to a first predefined level, and charges a second battery using the stored charge of the first battery when a stored charge of the second battery drops to a second predefined level.

A power module includes a turbine arranged along a rotation axis, an interconnect shaft fixed in rotation relative to the turbine, and a compressor with a regenerative compressor wheel. The regenerative compressor wheel is fixed in rotation relative to the interconnect shaft supported for rotation with the turbine about the rotation axis. Generator arrangements, unmanned aerial vehicles, and methods of generating electrical power are also described.

An engine (100) is provided with a powertrain including a heat engine (1) and an output shaft (A1), an electric motor (2), a battery (40) for supplying the electric motor (2) and a propeller propulsion system including a propeller (3) and a propeller shaft (A3), to which the propeller (3) is coupled. The powertrain includes a system of clutches (E123, E14, E23, E324) designed for different configurations to selectively drive the propeller using the heat engine without transmission of the rotation of the electric motor to the propeller; using the electric motor without transmission of the rotation of the heat engine to the propeller; using combined transmission of the rotation of the heat engine and the rotation of the electric motor to the propeller. The electric motor includes a stator and a rotor mounted for rotation about a shaft rigidly connected, or capable of being coupled, to the propeller shaft.

There is provided a vertical takeoff and landing aircraft (VTOL), having a main propulsion unit (GT engine) with high-pressure and low-pressure turbine shafts installed along a longitudinal axis of a frame to be rotated by pressurized gas jetted on combustion of an air-fuel mixture to produce propulsion force in a longitudinal direction of the frame, high-pressure side and low-pressure side motor generators coaxially attached to the high-pressure and low-pressure turbine shaft, four fans installed on the frame to be rotatable around axes parallel to a vertical axis of the frame, four propulsion units individually connected to the fans to rotate them and generate lift force in a vertical direction of the frame, and a controller. The controller control operation of the main propulsion unit, motor generators and sub propulsion units to obtain propulsion forces in the longitudinal direction and in the vertical direction of the frame.

Disclosed is an imaging method for imaging terrain using a sensor on an unmanned aircraft. The method comprises: acquiring a range of motion of the sensor; acquiring positional information of the terrain; acquiring parameter values relating to aircraft maneuverability; using the acquired information, determining a procedure; performing, by the aircraft, the procedure and simultaneously capturing, by the sensor, a set of images of only parts of the terrain. The procedure comprises the aircraft moving with respect to the area of terrain and the sensor moving with respect to the aircraft such that each point in the area of terrain is coincident with a footprint of the sensor on the ground for at least some time. Also, every point in the area of terrain is present within at least one of the captured images.

Systems, methods, and devices provide a vehicle, such as an aircraft, with rotors configured to function as a tri-copter for vertical takeoff and landing (VTOL) and a fixed-wing vehicle for forward flight. One rotor may be mounted at a front of the vehicle fuselage on a hinged structure controlled by an actuator to tilt from horizontal to vertical positions. Two additional rotors may be mounted on the horizontal surface of the vehicle tail structure with rotor axes oriented vertically to the fuselage. For forward flight of the vehicle, the front rotor may be rotated down such that the front rotor axis may be oriented horizontally along the fuselage and the front rotor may act as a propeller. For vertical flight, the front rotor may be rotated up such that the front rotor axis may be oriented vertically to the fuselage, while the tail rotors may be activated.

A drone system and method for deploying and autonomously refuelling. The drone system includes a base station and a drone. The base station and drone are configured for autonomous refuelling when the drone has landed in the base station. The base station also provides portability and security of the drone.

A drone system and method for deploying and autonomously refuelling. The drone system includes a base station and a drone. The base station and drone are configured for autonomous refuelling when the drone has landed in the base station. The base station also provides portability and security of the drone.

A power supply system includes: a drone including a propeller, a motor for driving the propeller, a power control unit for supplying the motor, a battery storing electric power, a generator for generating the power, an engine for driving the generator, a fuel tank storing fuel to be supplied to the engine, and a power suppling device for supplying the power generated by the generator to a power supply target; a control unit for controlling various operations of the drone; and an operation management unit for controlling the operations of the drone. Upon receipt of a power supply request, the operation management unit flies the drone to the location of the target. After the drone arrives at the target, the control unit causes the generator to generate the power based on a command from the operation management unit to supply the power to the target via the power suppling device.

A power supply system includes: a drone including a propeller, a motor for driving the propeller, a power control unit for supplying the motor, a battery storing electric power, a generator for generating the power, an engine for driving the generator, a fuel tank storing fuel to be supplied to the engine, and a power suppling device for supplying the power generated by the generator to a power supply target; a control unit for controlling various operations of the drone; and an operation management unit for controlling the operations of the drone. Upon receipt of a power supply request, the operation management unit flies the drone to the location of the target. After the drone arrives at the target, the control unit causes the generator to generate the power based on a command from the operation management unit to supply the power to the target via the power suppling device.