Vertical path control for aircraft area navigation system

Aeronautics and astronautics – Aircraft control – Automatic

Patent

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Details

23515022, 244183, 244186, G05D 108

Patent

active

040210090

ABSTRACT:
In the vertical path control of an area navigation system when the aircraft ascends or descends to a waypoint with an "at-or-above" or "at-or-below" altitude requirement, vertical steering is effected at a constant airspeed with regard to a reference airspeed. An alert device is included to provide a warning to the pilot when the aircraft flight path angle is less than the straight line flight path angle to the waypoint for "at-or-above" waypoints or when the flight path angle of the aircraft is greater than the straight line flight path angle to the waypoint for waypoints with an "at-or-below" altitude requirement. Altitude error is displayed on a vertical deviation indicator of an aircraft flight instrument in accordance with the difference between the actual aircraft altitude and the altitude of the next waypoint having a firm altitude requirement. When the aircraft ascends or descends to a waypoint through the pressure-barometric altitude transition, flight path angles are computed and utilized as the vertical steering reference to avoid a steering discontinuity at the transition altitude. When the aircraft is on a descent path to a waypoint and an airspeed reduction is required, vertical angles are computed and utilized for generating the vertical steering signal whereby a speed reduction transition zone is included in the flight path to effect the speed reduction and make good the desired waypoint altitude.

REFERENCES:
patent: 3691361 (1972-09-01), Perkins
patent: 3705306 (1972-12-01), Lydon
patent: 3786505 (1974-01-01), Rennie
patent: 3848114 (1974-11-01), Campbell

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