Aircraft systems and methods for providing landing approach alerts

Patent metadata

Field	Value
Publication number	US-9916765-B2
Application number	US-201514932492-A
Country	US
Kind code	B2
Filing date	Nov 4, 2015
Priority date	Nov 4, 2015
Publication date	Mar 13, 2018
Grant date	Mar 13, 2018

Abstract

A method is provided for monitoring a landing approach of an aircraft. The method includes receiving instrument landing system (ILS) signals; determining a glideslope deviation from the ILS signals; disabling, when the glideslope deviation is less than a first predetermined threshold, at least one glideslope alert function; evaluating a current glideslope condition by comparing a designated glideslope angle to a glideslope check value; and re-enabling the at least one glideslope alert function when the glideslope check value differs from the designated glideslope angle by more than a second predetermined threshold.

First claim

What is claimed is:

1. A method for monitoring a landing approach of an aircraft, the method comprising:
receiving instrument landing system (ILS) signals;
determining a glideslope deviation from the ILS signals;
disabling, with a processor controlling a glideslope warning unit and when the glideslope deviation is less than a first predetermined threshold, at least one glideslope alert function of the glideslope warning unit;
evaluating, with the processor, a current glideslope condition by comparing a designated glideslope angle to a glideslope check value; and
re-enabling, with the processor controlling the glideslope warning unit, the at least one glideslope alert function of the glideslope warning unit when the glideslope check value differs from the designated glideslope angle by more than a second predetermined threshold.

2. The method of claim 1 , wherein the at least one glideslope alert function is an excess height alert function.

3. The method of claim 1 , wherein the step of evaluating the current glideslope condition includes calculating the glideslope check value with the following equation:

GlideslopeCheckValue
=

Arc
⁢

⁢

Tan
⁡

(

HeightAboveRunway

(
DistRunwayThreshold
)

*
6076.11
⁢

⁢

ft
/
nm

)

,

wherein
HeightAboveRunway is a current height of the aircraft above a respective runway in feet, and
DistRunwayThreshold is a current lateral distance of the aircraft from the respective runway in nautical miles.

4. The method of claim 1 , wherein the step of evaluating the current glideslope condition includes determining a current flight path angle and using the current flight path angle as the glideslope check value.

5. The method of claim 1 , wherein the step of evaluating the current glideslope condition includes retrieving the designated glideslope angle from a runway database.

6. The method of claim 1 , wherein the step of evaluating the current glideslope condition includes setting the designated glideslope angle within a range of approximately 2.5° to 3.5°.

7. The method of claim 1 , wherein the second predetermined threshold is approximately 2°.

8. The method of claim 1 , wherein the second predetermined threshold is approximately 1°.

9. The method of claim 1 , wherein the evaluating step includes identifying a false glideslope capture event when the glideslope check value differs from the designated glideslope angle by more than the second predetermined threshold.

10. A system for monitoring a landing approach of an aircraft, comprising:
an aircraft instrument landing system (ILS) configured to receive ILS signals and to calculate a glideslope deviation based on the ILS signals;
a glideslope warning unit coupled to the aircraft ILS and comprising a computer having a processor and a computer readable storage medium storing computer readable instructions capable of, upon execution by the processor, to selectively operate in at least one of
a default mode with at least one glideslope alert function,
a first mode in which the at least one glideslope alert function is disabled, or
a second mode in which the at least one glideslope alert function is re-enabled; and

a glideslope monitor coupled to the glideslope warning unit and configured to evaluate a current glideslope condition by comparing a designated glideslope angle to a glideslope check value,
wherein the glideslope warning unit is configured to operate in the first mode when the glideslope deviation is less than a first predetermined threshold and when a difference between the glideslope check value and the designated glideslope angle is within a second predetermined threshold, and
wherein the glideslope warning unit is configured to operate in the second mode when the glideslope deviation is less than the first predetermined threshold and when the difference between the glideslope check value and the designated glideslope angle exceeds the second predetermined threshold.

11. The system of claim 10 , wherein the at least one glideslope alert function is an excess height alert function.

12. The system of claim 10 , wherein the glideslope monitor is configured to calculate the glideslope check value with the following equation:

GlideslopeCheckValue
=

Arc
⁢

⁢

Tan
⁡

(

HeightAboveRunway

(
DistRunwayThreshold
)

*
6076.11
⁢

⁢

ft
/
nm

)

,

wherein
HeightAboveRunway is a current height of the aircraft above a respective runway in feet, and
DistRunwayThreshold is a current lateral distance of the aircraft from the respective runway in nautical miles.

13. The system of claim 10 , wherein the glideslope monitor is configured to determine a current flight path angle and use the current flight path angle as the glideslope check value.

14. The system of claim 10 , further comprising a runway database coupled to the glideslope monitor, wherein the glideslope monitor is configured to retrieve the designated glideslope angle from a runway database.

15. The system of claim 10 , wherein the glideslope monitor is configured to set the designated glideslope angle within a range of approximately 2.5° to 3.5°.

16. The system of claim 10 , wherein the second predetermined threshold is approximately 2°.

17. The system of claim 10 , wherein the second predetermined threshold is approximately 1°.

18. The system of claim 10 , wherein the glideslope mo

Assignees

• Honeywell Int Inc

Inventors

• Ishihara Yasuo
• Johnson Steve

Classifications

• G01S1/08

  Systems for determining direction or position line · CPC title

• G08G5/0026

  Physics · mapped topic

• G01S1/022

  Means for monitoring or calibrating · CPC title

• G01S1/02

  using radio waves (G01S19/00 takes precedence) · CPC title

• G08G5/0021

  Physics · mapped topic