FIELD: aviation.
SUBSTANCE: invention relates to a method for aircraft control in longitudinal channel during landing. For landing aircraft is informed on target velocity and elevator is turned by target turning angle, engine thrust is released down at reduction of aircraft vertical speed to preset magnitude. Target velocity is calculated as sum of preset air speed and taken with opposite sign value proportional to wind velocity. Target turning angle is calculated as sum of specified rotation angle and taken with opposite sign angles, proportional to wind speed and derivative of wind speed. Wind speed is calculated as difference between values of track and aircraft air speed.
EFFECT: aircraft landing on specified section of runway in conditions of varying longitudinal wind due to minimum vertical speed.
2 cl, 2 dwg
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