An electrical power supply device for electric propulsion aircraft includes first and second electric motors configured to ensure the propulsion of the aircraft. First and second high-voltage electrical circuits are connected respectively to the two electric motors. A low-voltage electrical circuit is connected to at least one control and/or command facility of the aircraft. First and second pack of batteries are connected respectively to the two high-voltage electrical circuits. First and second battery management systems are connected to the low voltage circuit. Two battery management systems are linked respectively to the two packs of batteries. An electrical converter is connected to the first high-voltage electrical circuit and to the low-voltage electrical circuit.

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.

Examples relate to a battery management system with an enhanced equivalent circuit model (ECM) for electric vehicles, including electric vertical takeoff and landing (eVTOL) aircraft. The system includes a memory to store an equivalent circuit model (ECM) configured to dynamically adjust a series resistance component in real-time based on operational data from a lithium-ion battery. This adjustment models lithium depletion effects under high discharge conditions. At least one processor is configured to continuously refine parameters of the ECM by analyzing discrepancies between predicted and actual battery performance, where the adjustments are based on real-time changes in state of charge, temperature, and current.

Examples relate to a battery management system with an enhanced equivalent circuit model (ECM) for electric vehicles, including electric vertical takeoff and landing (eVTOL) aircraft. The system includes a memory to store an equivalent circuit model (ECM) configured to dynamically adjust a series resistance component in real-time based on operational data from a lithium-ion battery. This adjustment models lithium depletion effects under high discharge conditions. At least one processor is configured to continuously refine parameters of the ECM by analyzing discrepancies between predicted and actual battery performance, where the adjustments are based on real-time changes in state of charge, temperature, and current.

A propulsor brake lock system includes an aircraft propulsor, a reduction gear assembly, a brake shaft, and a brake assembly. The aircraft propulsor includes a propeller having a propeller input shaft coupled thereto. The reduction gear assembly includes at least an input gear and an output gear. The input gear and output gear are both rotatable with the propeller input shaft. The brake shaft is coupled to, and is rotatable with, the output gear. The brake assembly is coupled to the brake shaft and is moveable between a disengaged position, in which the brake shaft may rotate whenever the output gear rotates, and an engaged position, in which the brake shaft is prevented from rotating, thereby preventing rotation of the output gear, the input gear, and the propeller input shaft.

A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotor assemblies, tandem wings, and forward thrust propellers. The vertical lift rotor assemblies, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotor assemblies and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotor assemblies provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.

A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotor assemblies, tandem wings, and forward thrust propellers. The vertical lift rotor assemblies, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotor assemblies and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotor assemblies provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.

Provided in this disclosure is a high voltage distribution system of an electric aircraft. The system includes a power source mechanically connected to an electric aircraft, where the power source is configured to supply power to the electric aircraft. The system also includes a flight component mechanically connected to the electric aircraft. The system also includes a distribution component configured to control the providing of power to and from the power source and the flight component as needed during recharging and/or operation of the electric aircraft.

A system for fault detection and control in an electric aircraft including an inertial measurement unit, the inertial measurement unit including at least a sensor configured to detect a torque datum associated with at least a propulsor. The system includes an observer, the observer configured to generate a torque prediction datum associated with the at least a propulsor, compare the torque prediction datum with the torque datum, and generate a residual datum as a function of the comparison. The system includes a mixer, the mixer comprising circuitry configured to generate, as a function of the residual datum, a torque priority command datum and transmit, to the at least a propulsor, the torque priority command datum.

A power feeding device that is connected to a Faraday cage containing a flight vehicle via a conductor and supplies lightning power generated from a lightning surge that has struck to a battery of the flight vehicle, and a ground line that connects the power feeding device and a ground surface are provided, the power feeding device includes a capacitor connected in series between the Faraday cage and the ground line, a lightning arrester connected in parallel to the capacitor, and a step-down converter that steps down a terminal voltage of the capacitor charged by the lightning surge to generate lightning power and supplies the generated lightning power to the battery.