FIELD: aircraft engineering.
SUBSTANCE: invention relates to a method for generating an adaptive lateral-directional input of an aircraft. To implement the method, yaw and roll angles, angles of deviation of flight control surfaces, yaw rate, roll rate, transverse acceleration are measured, the identification of aerodynamic performance of the aircraft based on the recovery of the angle of sideslip, produced with the use of a linear continuous Kalman-Bucy filter and transverse acceleration measurement errors, yaw and roll rates, the lateral-directional motion control gains are corrected, on the basis of which the adaptive lateral-directional input of the aircraft is formed.
EFFECT: stabilization quality of an attitude motion of the aircraft in a wide speed and altitude envelope under the action of perturbations is ensured.
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