An aircraft includes a fuselage, a main wing, an electric field sensor, and a flight controller. The electric field sensor is configured to detect surface electric field intensities at four or more of mutually different positions on the aircraft. The flight controller includes a storage, a data extracting unit, an electric field intensity calculator, and an attitude control unit. The storage holds an electric field distribution table. The data extracting unit is configured to extract one of pieces of distribution data from the electric field distribution table. The electric field intensity calculator is configured to calculate surface electric field intensities at respective positions on the basis of the extracted piece of the distribution data. The attitude control unit is configured to perform prevention operation of the aircraft on the basis of the calculated surface electric field intensities at the respective positions.
AIRCRAFT AND FLIGHT CONTROLLER FOR AIRCRAFT
2021-09-02
Patent
Electronic Resource
English