FIELD: aviation.
SUBSTANCE: invention relates to a method for controlling a yaw angle and a roll angle of a vertically launching aircraft. To control the yaw angle and the roll angle, power generated by drive units located in opposite lateral zones of the aircraft at a distance from its fuselage with the possibility of turning at a certain angle to perform horizontal or vertical flight is coordinated in a certain way.
EFFECT: improved control efficiency is provided during vertical and horizontal flight, as well as during transitions from one flight to another.
10 cl, 1 dwg
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