Airplane position assurance monitor

• US 9,257,050 B2
• Filed: 12/09/2013
• Issued: 02/09/2016
• Est. Priority Date: 04/12/2011
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Fleiger-Holmes, Steven L., Murphy, Timothy Allen, Crane, Jean Marie
• Primary Examiner(s): Do, Truc M
• Application Number:
  US14/100,245
• Publication Number:
  US 20140100720A1
• Time in Patent Office: 792 Days
• Field of Search: 701/16, 701/301, 701/120, 701/117, 701/14, 701/18, 340/969, 340/965, 340/975, 340/977, 340/981
• US Class Current: 1/1
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C
• CPC Class Codes: B64D 45/04 Landing aids; Safety measures to prevent collision with earth's surface
• CPC Class Codes: G01C 5/005 altimeters for aircraft G01C5/02, G01C5/06 take precedence
• CPC Class Codes: G01S 1/18 Elevational guidance systems, e.g. system for defining aircraft glide path
• CPC Class Codes: G01S 19/15 Aircraft landing systems
• CPC Class Codes: G01S 19/20 Integrity monitoring, fault detection or fault isolation of space segment
• CPC Class Codes: G05D 1/0676 specially adapted for landing
• CPC Class Codes: G08G 5/0021 located in the aircraft
• CPC Class Codes: G08G 5/0026 located on the ground
• CPC Class Codes: G08G 5/02 Automatic approach or landing aids, i.e. systems in which flight data of incoming planes are processed to provide landing data landing aids fitted in or to aircraft B64D45/04; visual or acoustic landing aids B64F1/18
• CPC Class Codes: G08G 5/025 Navigation or guidance aids radar or analogous systems specially adapted for landing purposes G01S13/913

Abstract

An onboard monitor that ensures the accuracy of data representing the calculated position of an airplane during final approach to a runway. This airplane position assurance monitor is a software function that uses dissimilar sources of airplane position and runway data to ensure the accuracy of the respective data from those dissimilar sources. ILS data and GPS or GPS/Baro data are the dissimilar sources of airplane position data used by this function. This function will calculate the airplane'"'"'s angular deviations from the runway centerline and from the glide slope with onboard equipment and then compare those angular deviations to the ILS angular deviation information.

Claims

1. A method for monitoring positional accuracy of an airplane approaching a runway, comprising the following steps performed by a computer system during the approach:

(a) determining a ground distance between a location of the airplane and a touchdown aim point on the runway based on respective coordinates thereof;

(b) determining a height of the airplane above a threshold of the runway based on an altitude of the airplane and an elevation of a threshold of the runway;

(c) determining an angle between a hypothetical line extending from the airplane to the touchdown aim point and a perpendicular projection of that line onto a locally level plane that passes through a runway threshold reference point based on the ground distance and the height;

(d) determining a first vertical angular deviation of the airplane from a glideslope based on a difference of the determined angle and a glide path angle;

(e) receiving a second vertical angular deviation of the airplane from the glideslope based on measurements of a difference in a depth of modulation of first and second modulated signals transmitted from a ground-based antenna and received by an antenna onboard the airplane;

(f) comparing the first and second vertical angular deviations; and

(g) generating an alert signal when the first and second vertical angular deviations differ by an amount greater than a threshold value.

2. The method as recited in claim 1, wherein the airplane location is a location of a control guidance point.

3. The method as recited in claim 1, further comprising determining the coordinates of the airplane location using GPS signals.

4. The method as recited in claim 1, further comprising:

measuring a barometric pressure onboard the airplane; and

determining the airplane altitude based in part on the measured barometric pressure.

5. The method as recited in claim 1, further comprising determining the altitude of the airplane using GPS signals.

6. The method as recited in claim 1, further comprising:

retrieving the glide path angle and a threshold crossing height from a database; and

determining the touchdown aim point based on the glide path angle and the threshold crossing height.

7. A system for monitoring positional accuracy of an airplane approaching a runway, comprising:

a glideslope receiver for determining a first vertical angular deviation of the airplane from the glide slope based on measurements of a difference in a depth of modulation of first and second modulated signals transmitted by a ground-based glide slope transmitter; and

a computer system that is programmed to perform the following operations during the approach;

(a) determining a ground distance between a location of the airplane and a touchdown aim point on the runway based on respective coordinates thereof;

(b) determining a height of the airplane above a threshold of the runway based on an altitude of the airplane and an elevation of a threshold of the runway;

(c) determining an angle between a hypothetical line extending from the airplane to the touchdown aim point and a perpendicular projection of that line onto a locally level plane that passes through a runway threshold reference point based on the ground distance and the height;

(d) determining a second vertical angular deviation of the airplane from a glideslope based on the computed angle and a glide path angle;

(e) comparing the first and second vertical angular deviations; and

(f) generating an alert signal when the first and second vertical angular deviations differ by an amount greater than a threshold value.

8. The system as recited in claim 7, further comprising a device that produces an audible or visible warning in response to generation of said alert signal.

9. The system as recited in claim 7, further comprising a pressure altimeter for determining the airplane altitude based on the measured barometric pressure and a navigation database, wherein said computer system is further programmed to retrieve the runway threshold elevation from said navigation database and receive the airplane altitude form said pressure altimeter.

10. The system as recited in claim 7, further comprising a navigation database, wherein said computer system is further programmed to perform the following operations:

retrieving the glide path angle and a threshold crossing height from said navigation database; and

determining the touchdown aim point based on the glide path angle and the threshold crossing height.

11. The system as recited in claim 7, wherein said computer system is further programmed to determine the altitude of the airplane using GPS signals.

12. A method for monitoring positional accuracy of an airplane approaching a runway, comprising the following steps performed by a computer system during the approach:

(a) calculating a ground distance between a location of the airplane and a touchdown aim point on the runway based on respective coordinates thereof and not using vertical angular deviation;

(b) calculating a height of the airplane above a threshold of the runway based on an altitude of the airplane and an elevation of a threshold of the runway and not using vertical angular deviation;

(c) calculating an angle between a hypothetical line extending from the airplane to the touchdown aim point and a perpendicular projection of that line onto a locally level plane that passes through a runway threshold reference point based on the ground distance and the height and not using vertical angular deviation;

(d) calculating a first vertical angular deviation of the airplane from a glideslope based on a difference of the calculated angle and a glide path angle;

(e) calculating a second vertical angular deviation of the airplane from the glideslope based on measurements of a difference in a depth of modulation of first and second modulated signals transmitted from a ground-based antenna and received by an antenna onboard the airplane;

(f) comparing the first and second vertical angular deviations; and

(g) generating an alert signal when the first and second vertical angular deviations differ by an amount greater than a threshold value.

13. The method as recited in claim 12, further comprising calculating the coordinates of the airplane location using GPS signals.

14. The method as recited in claim 12, further comprising:

measuring a barometric pressure onboard the airplane; and

calculating the airplane altitude based in part on the measured barometric pressure.

15. The method as recited in claim 12, further comprising calculating the altitude of the airplane using GPS signals.

16. The method as recited in claim 12, further comprising:

retrieving the glide path angle and a threshold crossing height from a database; and

calculating the coordinates of the touchdown aim point based on the glide path angle and the threshold crossing height.