FIELD: automatic control over flight of aircraft. SUBSTANCE: technical result of proposal lies in reduction of deviation from reference flight altitude and balanced value of pitch angle under effect of disturbance and in decrease of time of return of ground effect craft to reference flight altitude and to balanced value of pitch angle on completion of effect of disturbance. Method consists in measurement of pitch angle, angular velocity, in formation of control signals proportional to pitch angle and angular acceleration and in formation of non- linear control signal in which value of damping factor depends on sign and value of pitch angle, on sign and value of angular velocity. Control signals are summed up and fed to control unit directly acting on elevator. EFFECT: reduced deviation from reference flight altitude. 5 dwg
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Authors
Dates
2002-02-27—Published
2000-07-05—Filed