METHOD OF AIRCRAFT CONTROL DURING LANDING APPROACH Russian patent published in 2016 - IPC G05D1/08 B64D45/04 G08G5/02 G01S19/15 

FIELD: aircraft engineering.

SUBSTANCE: invention relates to a method of aircraft (AC) control during landing approach. For AC control during landing approach is measured by inertial navigation system (INS), air data systems (ADS), satellite navigation system (SNS) course, bank and tangage of an AC, angle rate, horizontal and vertical speed, positioning data and altitude of an AC, runway heading is formed based on specified positioning data of AC altitude and positioning data of runway altitude, AC pointing control signals are formed on the bank and the tangage, AC pointing is changed in automatic or manual mode in compliance with generated control signals, landing path is formed with a gradient specified by a crew team, coinciding with the direction of the runway heading by heading, glide-path and finding radio beacons (HB, GB and FRB). In case of absence of the signals “Heading readiness (glide-path or range)” on the AC board, the control signals are formed by the parameters of the virtual heading (glide-path or finding) beacons (VHB, VGB, VFRB) placed in a certain manner. Positioning data and altitude of VGB, omnibearings of VHB and elevation angle of VGB relative to the AC are determined. Desynchronization of the VHB omnibearing relative to the AC and runway heading, desynchronization of the VGB elevation angle relative to the AC and landing path inclination specified by the crew team are determined for correction of the control signals.

EFFECT: landing system reliability is provided.

1 cl, 5 dwg, 1 tbl