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.

There is disclosed in one example an unmanned vertical lift aircraft, comprising: an airframe; a drive system configured for vertical takeoff and landing (VTOL); a power plant to power the drive system; and an internal cargo bay comprising a fore aperture and an aft aperture, the fore and aft apertures having dimensions substantially conforming to a cross section of the internal cargo bay, and the internal cargo bay comprising a substantially linear and open volume between the fore and aft apertures.

There is disclosed in one example an unmanned vertical lift aircraft, comprising: an airframe; a drive system configured for vertical takeoff and landing (VTOL); a power plant to power the drive system; and an internal cargo bay comprising a fore aperture and an aft aperture, the fore and aft apertures having dimensions substantially conforming to a cross section of the internal cargo bay, and the internal cargo bay comprising a substantially linear and open volume between the fore and aft apertures.

UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.

UAV configurations and battery augmentation for UAV internal combustion engines, and associated systems and methods are disclosed. A representative configuration includes a fuselage, first and second wings coupled to and pivotable relative to the fuselage, and a plurality of lift rotors carried by the fuselage. A representative battery augmentation arrangement includes a DC-powered motor, an electronic speed controller, and a genset subsystem coupled to the electronic speed controller. The genset subsystem can include a battery set, an alternator, and a motor-gen controller having a phase control circuit configurable to rectify multiphase AC output from the alternator to produce rectified DC feed to the DC-powered motor. The motor-gen controller is configurable to draw DC power from the battery set to produce the rectified DC feed.

A hybrid engine system includes: an engine; a generator driven by the engine to output electrical energy; a battery configured to store electrical energy produced by the generator or supply electrical energy together with the generator; and a controller configured to control the engine, wherein the controller includes a torque meter for measuring torque of an output shaft of the engine and a current meter for measuring output current of the generator, and is further configured to change a control mode of the engine when a reduction rate of at least one of the torque and the current is greater than a set value while the engine is operating in a fly mode.

An unmanned aerial vehicle includes a power generator, a first electrical component, a second electrical component, a main battery capable of being charged with power generated by the power generator, a sub-battery, and a charging circuit connecting the second electrical component and the sub-battery. The sub-battery is configured to be charged by receiving power from the second electrical component through the charging circuit, and configured to supply power to the first electrical component.

An unmanned aerial vehicle includes a power generator, a first electrical component, a second electrical component, a main battery capable of being charged with power generated by the power generator, a sub-battery, and a charging circuit connecting the second electrical component and the sub-battery. The sub-battery is configured to be charged by receiving power from the second electrical component through the charging circuit, and configured to supply power to the first electrical component.

An unmanned aerial vehicle includes a plurality of electric motors each to drive a respective one of a plurality of first rotors included in a plurality of rotors, an internal combustion engine, an electric generator that is driven by the internal combustion engine to generate electric power, a battery to store the electric power, and a controller configured or programmed to control flight of the unmanned aerial vehicle and to change an upper limit of a flight altitude of the unmanned aerial vehicle according to a charging state of the battery.

An unmanned aerial vehicle includes a plurality of electric motors each to drive a respective one of a plurality of first rotors included in a plurality of rotors, an internal combustion engine, an electric generator that is driven by the internal combustion engine to generate electric power, a battery to store the electric power, and a controller configured or programmed to control flight of the unmanned aerial vehicle and to change an upper limit of a flight altitude of the unmanned aerial vehicle according to a charging state of the battery.