OPERATIONS SUPPORT SYSTEMS AND METHODS WITH POWER MANAGEMENT

• US 20100161154A1
• Filed: 12/23/2008
• Published: 06/24/2010
• Est. Priority Date: 12/23/2008
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Ling, Richard, Stramiello, Andy, Moeckly, Kevin, Goericke, Jan
• Granted Patent: US 8,417,410 B2
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F05D 2270/11 to prolong engine life
• CPC Class Codes: F05D 2270/44 active, predictive, or anticipative
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A power management system includes a data fusion unit configured to receive first health indicators from an engine diagnostics module and second health indicators from a power assurance module. The data fusion unit is configured to data fuse the first and second health indicators. A power assessment and decision support unit is coupled to the data fusion unit and configured to generate power available based on the fused first and second health indicators. A system diagnostic reasoner unit is coupled to the data fusion unit, and configured to provide a system level fault diagnosis based on the fused first and second health indicators. A graphical user interface is coupled to the power assessment and decision support unit and the system diagnostic reasoned unit. The graphical user interface is configured to display the system level fault diagnosis and the power available.

Claims

1. A power management system, comprising:

a data fusion unit configured to receive first health indicators from an engine diagnostics module and second health indicators from a power assurance module, the data fusion unit configured to data fuse the first and second health indicators;

a power assessment and decision support unit coupled to the data fusion unit and configured to generate power available based on the fused first and second health indicators;

a system diagnostic reasoner unit coupled to the data fusion unit, and configured to provide a system level fault diagnosis based on the fused first and second health indicators; and

a graphical user interface coupled to the power assessment and decision support unit and the system diagnostic reasoned unit, the graphical user interface configured to display the system level fault diagnosis and the power available.

2. The power management system of claim 1, wherein power assessment and decision support unit is configured to receive a mission profile, and to compare the power available to power necessary according the mission profile.

3. The power management system of claim 1, wherein the system fault diagnosis include a maintenance action plan.

4. The power management system of claim 1, wherein the data fusion unit is configured to receive third health indicators from a model-based torque module.

5. The power management system of claim 1, wherein the system level fault diagnosis further includes fault/failure mode ranking.

6. The power management system of claim 1, wherein the system level fault diagnosis further includes prognostic indicators.

7. The power management system of claim 1, wherein the graphical user interface is configured to display current engine and future engine health based on the system level fault diagnosis.

8. The power management system of claim 1, wherein the system level fault diagnosis further includes power assurance numbers.

9. The power management system of claim 1, wherein the graphical user interface is configured to display the power available relative to a mission profile.

10. The power management system of claim 1, wherein the system level fault diagnosis further includes component health of engine components.

11. The power management system of claim 1, wherein data fusion unit is configured to receive the first health indicators and the second health indicators from a plurality of aircraft, the graphical user interface being configured to display the fused health indicators for the plurality of aircraft.

12. The power management system of claim 11, wherein the graphical user interface is configured to display the fused health indicators for each of the plurality of aircraft.

13. The power management system of claim 1, wherein the system level fault diagnosis further includes engine hours remaining.

14. A method of managing power for an aircraft with an engine, comprising:

receiving first health indicators from an engine diagnostics module;

receiving second health indicators from a power assurance module;

fusing the first and second health indicators;

generating a system level fault diagnosis; and

displaying the system level fault diagnosis.

15. The method of claim 14, wherein the generating a system level fault diagnosis step includes generating power available.

16. The method of claim 15, further comprising receiving a mission profile and comparing the power available to power necessary according the mission profile.

17. The method of claim 14, further comprising generating a maintenance action plan.

18. The method of claim 14, wherein the generating a system level fault diagnosis step includes generating a fault/failure mode ranking.

19. The method of claim 14, further comprising generating prognostic indicators.

20. A method of managing power for an aircraft fleet, comprising:

receiving first health indicators from a first aircraft;

receiving second health indicators from a second aircraft;

fusing the first and second health indicators;

generating a fleet level fault diagnosis; and

displaying the fleet level fault diagnosis.