A power distribution circuit for an electrically powered aircraft includes a plurality of batteries and a plurality of electric propulsion systems. A plurality of isolated power distribution circuits each couple a battery of the plurality of batteries to two or more electric propulsion systems. The plurality of electric propulsion systems are positioned on the aircraft to apply balanced forces to the aircraft such that in the event of a failure, the aircraft remains stable and only experiences a loss in altitude or speed.

A multiple energy source management system for an integrated hydrogen-electric engine is disclosed, the system includes a first and a second energy source providing energy to the integrated hydrogen-electric engine. A pre-charge load to provide an energy demand to a selected energy source. A sensor monitoring a power output from the first and/or second energy source. A relay to switch between the first and second energy sources. A computer system to receive an output energy of the first energy source, determine if the output energy is below a threshold value, switch the relay from the first state to the third state for a predetermined period of time, based on the determination, pre-charge the second energy source by the pre-charge load; and switch the relay to the second state after the predetermined period of time.

A flight control device performs a flight control process for causing an eVTOL to fly. In a step of the flight control process, the flight control device determines whether the eVTOL is capable of maintaining a stable attitude. In the step, it is determined whether the eVTOL is capable of maintaining the stable attitude even if driving of an abnormal motor is stopped. In the step, it is determined whether the eVTOL is capable of maintaining the stable attitude even if the abnormal motor continues driving. When it is determined that the eVTOL is capable of maintaining the stable attitude, the flight control device performs output adjustment of at least one of a normal motor and the abnormal motor to maintain the eVTOL at the stable attitude.

An electrical system for connecting a rotary electric machine to de networks operating at different voltages V and W where V>W, the electric machine has N=4 polyphase winding sets. The electrical system includes a first set of N=4 ac-dc converter circuits connected in a modular multilevel configuration, each ac-dc converter circuit having a respective index n=(1, . . . , 4) and an ac interface for connection with a corresponding nth winding set, and in which the modular multilevel configuration has P=5 dc outputs each having a respective index p=(1, . . . , 5), and a set of N=4 dc-dc converter circuits each having a respective index n=(1, . . . , 4) and being configured to convert dc power between a voltage V/4 at a first dc interface and a voltage W at a second dc interface.

A thermal management system includes a refrigeration circuit that cools at least a first coolant that circulates around a battery cooling loop. Refrigerant of the refrigeration circuit is cooled at a liquid-cooled condenser and at an air-cooled condenser. In certain examples, the liquid-cooled condenser is cooled by coolant circulating along a propeller arrangement cooling loop. In certain examples, the coolant from the propeller arrangement cooling loop may be combined with coolant from the battery cooling loop.

An aircraft includes: rotors each driven by an electric motor; a PCU that converts AC power output from a generator into DC power; an inverter that converts DC power supplied from the PCU into AC power and outputs the AC power to the electric motor; a DC wire that connects the PCU and the inverter; and an AC wire that connects the inverter and the electric motor. The AC wire is disposed in a direction orthogonal to a direction in which rotation shafts of the generator and a gas turbine extend.

There is provided an electrical power system comprising: a DC voltage source, a DC electrical network, a DC to AC to DC converter having a primary side connected to the DC voltage source and a secondary side connected to the DC electrical network, and a controller configured to control the DC to AC to DC converter, wherein the controller is configured to: monitor an electrical current or voltage between the DC voltage source and the DC electrical network; determine, based on the monitored electrical current or voltage, whether the DC electrical network is in a fault condition; and increase a switching frequency of the primary side of the DC to AC to DC converter in response to a positive determination that the DC electrical network is in a fault condition.

Systems and methods for backlash measurement and monitoring are disclosed for an actuator having a motor end and an output end. The method may include: driving the motor end of the actuator to one endpoint; measuring, using a first sensor, a motor-end initial position value associated with the motor end; measuring, using a second sensor, an output-end initial position value associated with the output end; driving the motor end of the actuator to another endpoint; measuring a motor-end final position value using the first sensor and an output-end final position value using the second sensor; determining a backlash value based on the motor-end initial position value, output-end initial position value, motor-end final position value, and output-end final position value; generating a signal based on comparing the backlash value to a predetermined threshold; and displaying a notification indicative of an operational condition of the actuator based on the signal.

A vertical takeoff and landing aircraft (101) for transporting persons or loads, including a plurality of preferably equivalent and redundant electric motors (3) and propellers (2), substantially arranged in one surface, wherein each propeller is assigned an individual electric motor to drive the propeller, the aircraft being characterized in that at least one attitude sensor is provided for attitude control of the aircraft (101) in an active signal connection to at least one signal processing unit which is designed or set up to automatically perform the attitude control based on measurement data from the attitude sensor by regulating the speed of at least some of the electric motors (3), preferably with signal actions of the speed controller assigned to each electric motor such that the aircraft (101) is positioned in space with the surface defined by the propeller (2) substantially horizontal at all times, without control input by a pilot or a remote control.

A system for providing regenerative power for an aircraft to sustain flight includes multiple energy cells disposed within the aircraft, the energy cells being configured to supply power to a propulsion motor and electronics of the aircraft, a fan generator harnessing propeller blast created by an aircraft propeller and converting kinetic energy of the propeller blast into electrical energy, a charger receiving the electrical energy generated by the fan generator and using the electrical energy to recharge one or more of the energy cells, and a power transfer switch selectively connecting one of the energy cells to the propulsion motor and electronics of the aircraft, such that the energy cells are rotated one at a time to power the propulsion motor and electronics. During recharging, the one or more of the energy cells are disconnected by the power transfer switch.