FIELD: aircraft guidance systems.
SUBSTANCE: method comprises measuring transverse acceleration of the aircraft to be guided in the horizontal plane, measuring the angle between the vector of aircraft velocity and line of sighting on the ground object, distance between the aircraft and ground object, velocity of the aircraft, and generating the control signal in the horizontal plane as the difference between the required angular velocity of the conventional sighting point multiplied by the adaptive navigation parameter and transverse acceleration of the aircraft in the horizontal plane. The adaptive navigation parameter is generated depending on the difference between the current value of the angle between the vector of the aircraft velocity and line of sighting on the ground object in the horizontal plane and required angular shift of the conventional sighting point in the horizontal plane with respect to the line of sighting on the ground object.
EFFECT: improved stabilizing of linear resolution of the guidance.
1 dwg
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