Method for guiding aircraft on taxiways

• US 6,411,890 B1
• Filed: 08/03/2000
• Issued: 06/25/2002
• Est. Priority Date: 11/27/1997
• Status: Expired due to Term

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Zimmerman, Rolf
• Primary Examiner(s): Nguyen, Tan
• Assistant Examiner(s): Tran, Dalena
• Application Number:
  US09/555,358
• Time in Patent Office: 691 Days
• Field of Search: 701/120, 701/117, 701/23, 701/28, 701/16, 701/17, 701/121, 701/122, 701/207, 701/225, 180/167, 180/168, 180/169, 348/117, 348/116, 348/144, 342/410, 340/947, 340/952, 340/953, 340/989, 702/94, 731/78.R, 731/78.T
• US Class Current: 701/120
• CPC Class Codes: B64F 1/002 Taxiing aids
• CPC Class Codes: G05D 1/0083 to help an aircraft pilot in the rolling phase
• CPC Class Codes: G08G 5/065 Navigation or guidance aids, e.g. for taxiing or rolling

Abstract

The invention refers to a method for the guidance of aircraft on the taxiways (R) of the airport apron with position lights (FE) located on the taxiways (R) and, possibly, other locations on the apron. It comprises the following steps:

determination of the current aircraft position with a defined precision by means of a navigation system (NAV);

position detection and measurement of the lights by means of a sensor (SEN) arranged on the aircraft,

provision of reference information (REF) including the positions of the individual lights (FE),

comparison of the path pursued by the navigation system (NAV) with the reference information (REF) and utilization of the detected lights (FE) as waypoints for the navigation system (NAV), and therefrom

determination of the current aircraft position with a higher precision than that of the original position determination by the navigation system (NAV);

generation of guidance information (FRG) based on the determined aircraft position.

Claims

1. A method for guiding an aircraft on a taxiway of an airport apron comprising:

a. providing a plurality of lights fixed along a taxiway path;

b. determining a first set of indices indicating a first position of a taxiing aircraft, the first set of indices being determined by an aircraft navigation system and exhibiting a first precision;

c. determining a second set of indices indicating a second position of the taxiing aircraft, the second position being detected by a sensor arranged on the taxiing aircraft and being relative to one of the lights, the second set of indices exhibiting a second precision that is more accurate than the first precision;

d. providing reference information comprising a definition of the taxiway path and a reference position for each of the lights relative to the taxiway path; and

e. generating guidance information based on the first set of indices, the second set of indices, and the reference information.

2. The method of claim 1 characterized in that the guidance information is transmitted to the pilot for manual aircraft control.

3. The method of claim 1 characterized in that the guidance information is used for automatic aircraft control without pilot intervention.

4. The method of claim 1 characterized in that the guidance information is used for semi-automatic aircraft control with longitudinal guidance controlled by a pilot and steering controlled automatically.

5. The method of any of claims 1 or 2 through 4 characterized in that the lights are fixed along the taxiway centerline.

6. The method of any of claims 1 or 2 through 5 characterized in that the reference information is stored in the form of a digital map.

7. The method of any of claims 1 or 2 through 6 characterized in that the sensor arranged on said taxiing aircraft is selected from the group consisting of a video camera and a scanner.

8. The method of any of claims 1 or 2 through 7 characterized in that the sensor is mounted on a landing gear of the taxiing, aircraft.

9. The method of any of claims 1 or 2 through 8 characterized in that the aircraft'"'"'s navigation system is an inertial navigation system.

10. The method of any of claims 1 or 2 through 8 characterized in that the navigation system is a satellite navigation system.