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.

A permanent-magnet synchronous three-phase rotating machine equipped with a control device having a command processor for an inverter driving phases of said machine, an angular speed and position estimator module for the rotor of the machine equipped at the input thereof with an input selector module, receiving digital voltage data, where said input selector module is driven by an operating mode command for said machine to select input data for the angular speed and position estimator module of the machine.

A permanent-magnet synchronous three-phase rotating machine equipped with a control device having a command processor for an inverter driving phases of said machine, an angular speed and position estimator module for the rotor of the machine equipped at the input thereof with an input selector module, receiving digital voltage data, where said input selector module is driven by an operating mode command for said machine to select input data for the angular speed and position estimator module of the machine.

A turbomachine monitoring and control system includes a temperature sensor configured to measure temperature of a turbomachine disposed onboard a vehicle, a vibration sensor configured to measure vibration of the turbomachine, and a controller including one or more processors. The controller is configured to receive and analyze temperature data generated by the temperature sensor and vibration data generated by the vibration sensor. The controller is further configured to determine a health condition of the turbomachine based on the analysis.

A turbomachine monitoring and control system includes a temperature sensor configured to measure temperature of a turbomachine disposed onboard a vehicle, a vibration sensor configured to measure vibration of the turbomachine, and a controller including one or more processors. The controller is configured to receive and analyze temperature data generated by the temperature sensor and vibration data generated by the vibration sensor. The controller is further configured to determine a health condition of the turbomachine based on the analysis.

The present disclosure relates generally to high voltage systems. In one embodiment, a balancing and measuring circuit is disclosed, comprising: a first capacitor electrically coupled between a first voltage and a chassis voltage, wherein the first voltage is greater than the chassis voltage; a second capacitor electrically coupled between a second voltage and the chassis voltage, wherein the second voltage is less than the chassis voltage; a first circuit associated with the first capacitor; and a second circuit associated with the second capacitor, wherein the first circuit and the second circuit each comprise: a resistive element; a switching element; a voltage circuit configured to generate a reference voltage; and a controller configured to monitor a voltage of a reference capacitor and to control the switching element based on the monitored voltage, wherein the resistive element and the switching element are connected in series.

The present disclosure relates generally to high voltage systems. In one embodiment, a balancing and measuring circuit is disclosed, comprising: a first capacitor electrically coupled between a first voltage and a chassis voltage, wherein the first voltage is greater than the chassis voltage; a second capacitor electrically coupled between a second voltage and the chassis voltage, wherein the second voltage is less than the chassis voltage; a first circuit associated with the first capacitor; and a second circuit associated with the second capacitor, wherein the first circuit and the second circuit each comprise: a resistive element; a switching element; a voltage circuit configured to generate a reference voltage; and a controller configured to monitor a voltage of a reference capacitor and to control the switching element based on the monitored voltage, wherein the resistive element and the switching element are connected in series.

Embodiments are provided for charging system for an aircraft. The charging system may comprise a plurality of electric propeller units (EPUs), a plurality of battery packs configured to power the plurality of EPUs, a charge port configured to accept high voltage power to charge the plurality of battery packs, a common high voltage charging bus connected to the charge port, and a charge control unit configured to determine battery pack charge contactor commands based on flight information for an aircraft and a current state of each battery pack of the plurality of battery packs. The plurality of battery packs may be chargeable through the common high voltage charging bus and each of the plurality of battery packs may include a disconnection device configured to disconnect the battery pack from charging.

Embodiments are provided for charging system for an aircraft. The charging system may comprise a plurality of electric propeller units (EPUs), a plurality of battery packs configured to power the plurality of EPUs, a charge port configured to accept high voltage power to charge the plurality of battery packs, a common high voltage charging bus connected to the charge port, and a charge control unit configured to determine battery pack charge contactor commands based on flight information for an aircraft and a current state of each battery pack of the plurality of battery packs. The plurality of battery packs may be chargeable through the common high voltage charging bus and each of the plurality of battery packs may include a disconnection device configured to disconnect the battery pack from charging.

A system and method for detecting and mitigating aircraft propulsor faults uses deliberate speed perturbations of individual propulsors and analysis of resulting vibration spectra to identify problematic units. Distributed sensors monitor vibration across multiple propulsors. A propulsor operates at an adjusted speed different from the ensemble. Resulting vibration characteristics reveal if the adjusted propulsor is an anomaly source. Its unique signature emerges in the vibration frequency data. The system cycles propulsors through adjusted speeds, detects correlated frequency shifts, and isolates faulty units. Targeted mitigation then acts only on identified bad propulsors while others remain operational. This enables automated in-flight troubleshooting of vibration issues and pinpointed mitigation.