An aerial vehicle is disclosed having a hybrid drive unit and a rotor unit wherein the hybrid drive unit includes at least a combustion engine, a generator and a first electric motor and the rotor unit includes a first rotor. The combustion engine is configured to drive the generator to produce electricity, and the generator is coupled to the first electric motor in such a way that the first electric motor is feedable with electricity from the generator. The rotor unit includes a second rotor and the hybrid drive unit includes a second electric motor, wherein the generator is coupled to the second electric motor in such a way that the second electric motor is feedable with electricity from the generator. The first rotor is driven by the first electric motor and the second rotor is driven by the second electric motor.

An energy supply system, which is a system constituting a regional power system in a target region, includes a power transmission system including a first power generation facility and a second power generation facility, a power transmission and distribution system that supplies power to each consumer, a management system, and an unmanned flying object. The unmanned flying object has a transport function of transporting a cargo and a power supply function of supplying power to an outside. When the amount of power supplied by the power transmission system is less than the amount of power required by the power transmission and distribution system, the management system performs a power adjustment process of supplying power from the unmanned flying object to the power transmission and distribution system by using the power supply function of the unmanned flying object.

An energy supply system, which is a system constituting a regional power system in a target region, includes a power transmission system including a first power generation facility and a second power generation facility, a power transmission and distribution system that supplies power to each consumer, a management system, and an unmanned flying object. The unmanned flying object has a transport function of transporting a cargo and a power supply function of supplying power to an outside. When the amount of power supplied by the power transmission system is less than the amount of power required by the power transmission and distribution system, the management system performs a power adjustment process of supplying power from the unmanned flying object to the power transmission and distribution system by using the power supply function of the unmanned flying object.

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.

An adaptable lattice structure (110, 120, 130, 140) for a an Unmanned Aerial System, UAS, comprising: a plurality of lattice voxels (100, 102), wherein each lattice voxel (100, 102) comprises: a plurality of same shape elements (10, 12); wherein each same shape element (10, 12) comprises a plurality of connector elements (20), wherein the plurality of connector elements (20) are configured to temporarily couple a first same shape element (10) to at least a second same shape element (12); wherein the plurality of same shape elements (10, 12) are configured to be temporarily coupled so as to form a three dimensional lattice voxel (100); and wherein at least one of the connector elements (20) on a first lattice voxel (100) is configured to temporarily couple the first lattice voxel (100) to a second lattice voxel (102) after the formation of the first lattice voxel (100) and the second lattice voxel (102).

A spin stabilized aircraft may include a plurality of wings that passively spin stabilize the aircraft, causing the apparatus to move in a direction opposite that of a wind source. The aircraft may also include two or more propulsive arms that actively stabilize the aircraft in absence of wind or a decrease in altitude.

A vertical take-off aircraft with a propulsion drive for generating a driving force being effective in a horizontal direction and with a lift drive for generating a lifting force being effective in a vertical direction includes a motor for providing mechanical energy for the propulsion drive and a first generator for providing electrical energy for the lift drive. Moreover, the aircraft includes an exhaust gas turbocharger for the motor with a first turbine being driven by an exhaust gas flow of the motor, wherein the first turbine is configured to provide mechanical energy for the propulsion drive.

A propulsion system for a ducted fan vertical takeoff and landing aircraft (VTOL) powered by multiple electric motors with two, counter rotating electric motors comprising the primary thrust generation within a ducted fan component and 3 or more external electric motors providing lift, stability and directional control of the aircraft. Through the use of counter rotating ducted fans, the aircraft does not require the need for internal statorseither fixed or adjustable angle. Power to the electric motors is sourced by either onboard batteries, a ground based power source via a ground to aircraft tether, or an on board fuel cell or combustion engine driving an alternator.

A cooling system includes a rotor (VTOL rotor, cruise rotor) for generating at least one of lift or thrust of an aircraft, a component group formed of a plurality of electrical components for rotating the rotor, and a cooling circuit for cooling the component group, wherein a plurality of the component groups corresponding to a plurality of the rotors are provided, and the plurality of component groups are cooled by the same cooling circuit.

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.