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.