Operations support systems and methods with power management

• US 8,417,410 B2
• Filed: 12/23/2008
• Issued: 04/09/2013
• Est. Priority Date: 12/23/2008
• Status: Expired due to Fees

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Moeckly, Kevin, Goericke, Jan, Stramiello, Andy, Ling, Richard
• Primary Examiner(s): Black, Thomas
• Assistant Examiner(s): LI, CE LI
• Application Number:
  US12/342,581
• Publication Number:
  US 20100161154A1
• Time in Patent Office: 1,568 Days
• Field of Search: 701/3, 701/14, 701 29- 30, 701/34.4, 701/99, 702182-184, 340/945, 340/963
• US Class Current: 701/29.1
• 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:

an engine diagnostics module configured to receive engine data from an engine and to generate first health indicators based on the engine data using a thermodynamic model, the thermodynamic model being based on component maps associated with the engine, wherein the engine diagnostics module is further configured to generate scalars based on the thermodynamic model and wherein the engine diagnostics module is further configured to adjust thermodynamic equations of the thermodynamic model based on the scalars;

a data fusion unit coupled to the engine diagnostics module and configured to receive the first health indicators from the 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 calculate 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, wherein the system level fault diagnosis further includes power assurance numbers; 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 4, wherein the system diagnostic reasoner unit is configured to project a failure time of a torque sensor based on the third health indicators from the model-based torque module.

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

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

8. 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.

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. The power management system of claim 1, wherein the engine diagnostics module is further configured to adjust thermodynamic equations of the thermodynamic model based on the scalars by scaling engine component airflows and efficiencies to match measured data.

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

collecting engine data;

generating condition indicators from the engine data using a thermodynamic model based on component maps associated with the engine;

generating scalars from the engine data using the thermodynamic model;

generating first health indicators from the condition indicators with an engine diagnostics module;

modifying the thermodynamic model based on the scalars;

receiving the first health indicators from the 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 based on the fused first and second health indicators; and

displaying the system level fault diagnosis,

wherein the generating a system level fault diagnosis step includes generating power available, and

further comprising receiving a mission profile and comparing the power available to power necessary according the mission profile.

16. The method of claim 15, further comprising generating a maintenance action plan.

17. The method of claim 15, wherein the generating a system level fault diagnosis step includes generating a fault/failure mode ranking.

18. The method of claim 15, further comprising generating prognostic indicators.

19. 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, each of the first and second health indicators being generating from engine data using at least one thermodynamic model based on component maps associated with an engine of the respective first and second aircraft;

generating scalars from the engine data of the respective first and second aircraft using the at least one thermodynamic model;

modifying the at least one thermodynamic model based on the scalars;

fusing the first and second health indicators;

generating a fleet level fault diagnosis, wherein the generating the fleet level fault diagnosis includes generating power available for each of the first aircraft and the second aircraft; and

receiving a mission profile and comparing the power available for each of the first aircraft and the second aircraft to power necessary according the mission profile; and

displaying the fleet level fault diagnosis.