Provided is a vertical take-off/landing aircraft controlling a tilt angle of a main rotor, based on a vertical posture control signal during low-speed flight, wherein, when an aircraft steering signal including a vertical posture control signal for changing the pitch posture angle of the vertical take-off/landing aircraft by a first pitch posture angle is obtained, a flight controller determines a tilt angle of the main rotor with reference to the first pitch posture angle and generates a tilt angle control signal for the main rotor based on the determined tilt angle.
Method and computer program for controlling tilt angle of main rotor on basis of pitch attitude control signal low-speed flight state, and vertical take-off and landing aircraft
2023-11-07
Patent
Elektronische Ressource
Englisch
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