Systems and methods for monitoring an altitude in a flight vehicle

• US 20070239326A1
• Filed: 04/05/2006
• Published: 10/11/2007
• Est. Priority Date: 04/05/2006
• Status: Abandoned Application

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Ishihara, Yasuo, Johnson, Steve, Bateman, Charles
• Application Number:
  US11/398,955
• Publication Number:
  US 20070239326A1
• Time in Patent Office: Days
• US Class Current: 701/9
• CPC Class Codes: G01C 5/06 by using barometric means
• CPC Class Codes: G08G 5/0021 located in the aircraft
• CPC Class Codes: G08G 5/0052 for cruising combined instruments indicating more than one navigational value G01C23/00
• CPC Class Codes: G08G 5/0086 for monitoring terrain radar or analogous systems specially adapted for terrain avoidance G01S13/935

Abstract

Systems and methods for monitoring an altitude in a flight vehicle are disclosed. In an embodiment, a system includes a barometric altimeter system operable to determine an altitude of the flight vehicle relative to a pressure datum that is adjustably selectable, and at least one altitude determination system that is operable to determine an altitude of the flight vehicle without reference to the selected pressure datum. A processor is coupled to the barometric altimeter system and to the at least one altitude determination system that is operable to receive altitude information from the barometric altimeter system and the at least one altitude determination system to compare the respective altitude information and determine if an altitude discrepancy exists.

Claims

1. A system for monitoring an altitude in a flight vehicle, comprising:

a barometric altimeter system operable to determine an altitude of the flight vehicle relative to a pressure datum that is adjustably selectable;

at least one altitude determination system that is operable to determine an altitude of the flight vehicle without reference to the selected pressure datum; and

a processor coupled to the barometric altimeter system and to the at least one altitude determination system that is operable to receive altitude information from the barometric altimeter system and the at least one altitude determination system and compare the respective altitude information to determine if an altitude discrepancy exists.

2. The system for monitoring an altitude in a flight vehicle of claim 1, wherein the at least one altitude determination system further comprises a radio altimeter system.

3. The system for monitoring an altitude in a flight vehicle of claim 1, wherein the at least one altitude determination system further comprises a global positioning system (GPS) receiving device.

4. The system for monitoring an altitude in a flight vehicle of claim 2, wherein the at least one altitude determination system further comprises a Terrain Awareness and Warning System (TAWS) that is configured to provide information for terrain in proximity to the flight vehicle.

5. The system for monitoring an altitude in a flight vehicle of claim 1, wherein the barometric altimeter system further comprises at least a static pressure sensor and a velocity sensor operably coupled to the flight vehicle.

6. The system for monitoring an altitude in a flight vehicle of claim 5, wherein the barometric altimeter system further comprises at least one air data computer coupled to the static pressure sensor and the velocity sensor that is configured to generate at least a corrected barometric altitude.

7. The system for monitoring an altitude in a flight vehicle of claim 1, further comprising an alarm module coupled to the processor that is configured to generate at least one of an audible alarm and a visual alarm upon detection of the altitude discrepancy.

8. A system for monitoring an altitude in a flight vehicle, comprising:

a selectively adjustable barometric altimeter system configured to display an altitude of the flight vehicle in response to a selected reference altitude and a sensed static pressure proximate to the flight vehicle;

at least one alternate altitude determination system that is operable to determine an altitude of the flight vehicle that is independent of the sensed static pressure; and

a processor coupled to the barometric altimeter system and to the at least one alternate altitude determination system that is configured to receive an altitude value from the barometric altimeter system and a corresponding altitude value from the at least one alternate altitude determination system and to compare the respective altitude values to determine if a statistically significant difference exists.

9. The system for monitoring an altitude in a flight vehicle of claim 8, wherein the at least one alternate altitude determination system further comprises a radio altimeter system.

10. The system for monitoring an altitude in a flight vehicle of claim 8, wherein the at least one alternate altitude determination system further comprises a global positioning system (GPS) receiving device.

11. The system for monitoring an altitude in a flight vehicle of claim 9, wherein the at least one alternate altitude determination system further comprises a Terrain Awareness and Warning System (TAWS) operable to provide information for terrain in proximity to the flight vehicle.

12. The system for monitoring an altitude in a flight vehicle of claim 8, wherein the barometric altimeter system further comprises at least a static pressure sensor and a velocity sensor operably coupled to the flight vehicle.

13. The system for monitoring an altitude in a flight vehicle of claim 12, wherein the barometric altimeter system further comprises at least one air data computer coupled to the static pressure sensor and the velocity sensor that is configured to generate at least a corrected barometric altitude.

14. The system for monitoring an altitude in a flight vehicle of claim 8, further comprising an alarm module coupled to the processor that is configured to generate at least one of an audible alarm and a visual alarm when the statistically significant difference exists.

15. A method of monitoring an altitude of a flight vehicle, comprising:

selectively adjusting a barometric altimeter system to define an altimeter setting that relates an altitude of the flight vehicle to a selected pressure datum;

acquiring altitude information from at least one alternate altitude determination system that is operable to determine an altitude of the flight vehicle that is independent of the altimeter setting;

assessing a difference between an altitude for the flight vehicle determined by the barometric altimeter system and an altitude determined by the at least one alternate altitude determination system; and

if the difference is greater than a predetermined value, generating a suitable alarm signal.

16. The method of monitoring an altitude of a flight vehicle of claim 15, wherein acquiring altitude information from at least one alternate altitude determination system comprises determining an altitude from at least one of a GPS system, a radio altimeter system and a TAWS system.

17. The method of monitoring an altitude of a flight vehicle of claim 15, wherein assessing a difference between an altitude for the flight vehicle determined by the barometric altimeter system and an altitude determined by the at least one alternate altitude determination system further comprises calculating a selected measure of statistical significance and comparing the selected measure to the predetermined value.

18. The method of monitoring an altitude of a flight vehicle of claim 17, wherein calculating a selected measure of statistical significance and comparing the selected measure to the predetermined value further comprises assuming that the predetermined value conforms to a chi-square distribution with a predetermined probability and a predetermined number of degrees of freedom.

19. The method of monitoring an altitude of a flight vehicle of claim 16, wherein assuming that the predetermined value conforms to a chi-square distribution with a predetermined probability and a predetermined number of degrees of freedom further comprises adopting a probability of approximately about 0.00010 and adopting a number of degrees of freedom of approximately about 25.

20. The method of monitoring an altitude of a flight vehicle of claim 15, wherein generating a suitable alarm message further comprises generating at least one of an audible alarm and a visual alarm.