Prognostic and health management accuracy maintenance system and method

• US 8,185,260 B2
• Filed: 02/12/2009
• Issued: 05/22/2012
• Est. Priority Date: 02/12/2009
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Delaloye, James, Payne, David A.
• Primary Examiner(s): Badii, Behrang
• Application Number:
  US12/370,371
• Publication Number:
  US 20100204852A1
• Time in Patent Office: 1,195 Days
• Field of Search: 701/4, 417/110, 165/41, 62/7, 508/112, 72/42, 700/282, 184/6.24, 184/7.4
• US Class Current: 701/4
• CPC Class Codes: G05B 23/0243 model based detection method, e.g. first-principles knowledge model

Abstract

A prognostic and health accuracy maintenance system and method for a system following on-site replacement of a component in the system is provided. A system characterization model of at least portions of the system is generated and embedded within a controller in the system. The system characterization model is adapted to receive a plurality of signals that are each representative of an operational parameter within the system and is responsive to each of the signals to generate simulation response data and determine system health based, at least in part, on the simulation response data. When a component within the system is replaced, a determination is made as to whether the replacement component exhibits one or more operational performance characteristics that differ from the component it replaced. If so, the embedded system characterization model is updated in-situ.

Claims

1. An aircraft lubrication supply system, comprising:

a motor operable, upon being energized from a power source, to rotate and supply a drive force;

a pump coupled to receive the drive force from the motor and operable, upon receipt thereof, to supply lubricant; and

a controller including an updatable system characterization model, the controller coupled to receive a pressure signal representative of lubricant pressure, a temperature signal representative of lubricant temperature, a speed signal representative of motor rotational speed, a motor current signal representative of current being drawn by the motor, a motor voltage signal representative of motor supply voltage, and one or more aircraft condition signals representative of one or more aircraft operating conditions, the controller operable, in response to each of the received signals, to (i) at least selectively energize the motor from the power source, (ii) generate simulation response data using the updatable system characterization model, and (iii) determine lubrication supply system health based, at least in part, on the simulation response data,

wherein the controller is configured to allow the updatable system characterization model to be updated in-situ to reflect replacement of one or more aircraft lubrication supply system components.

2. The system of claims 1, wherein:

the controller is configured to selectively receive a performance map unique to a component that has been replaced in the aircraft lubrication supply system; and

the controller is operable, upon receipt of the performance map, to update the updatable system characterization model to include the performance map.

3. The system of claim 1, wherein:

the controller is configured, upon replacement of one or more aircraft lubrication supply system components, to selectively run one or more in-situ tests of the aircraft lubrication supply system to generate a performance map unique to the one or more aircraft lubrication supply system components that were replaced; and

automatically updating the embedded system characterization model in-situ to reflect the performance map.

4. The system of claim 1, wherein the controller is further operable, in response to each of the received signals, to at least selectively generate data representative of operator maintenance directions.

5. The system of claim 1, further comprising:

a lubricant filter having a filter inlet and a filter outlet, the filter inlet coupled to receive at least a portion of the lubricant supplied by the pump, the lubricant filter configured to filter the lubricant received thereby and discharge filtered lubricant via the filter outlet; and

a filter outlet pressure sensor disposed downstream of the filter outlet, the filter outlet pressure sensor configured to sense filter outlet pressure and supply a filter outlet pressure signal representative thereof to the controller,

wherein the pressure signal received by the controller is the filter outlet pressure signal.

6. The system of claim 5, further comprising:

a filter inlet pressure sensor disposed upstream of the filter inlet, the filter inlet pressure sensor configured to sense filter inlet pressure and supply a filter inlet pressure signal representative thereof to the controller,

wherein the controller is further responsive the filter inlet pressure signal to determine lubrication supply system health status.

7. The system of claim 1, further comprising:

a rotational speed sensor configured to sense motor rotational speed and supply the speed signal to the controller.

8. The system of claim 1, further comprising:

a temperature sensor configured to sense lubricant temperature and supply the temperature signal to the controller.

9. The system of claim 1, wherein the one or more aircraft condition signals representative of aircraft operating conditions include:

an altitude signal representative of aircraft altitude; and

an attitude signal representative of aircraft attitude.

10. The system of claim 1, further comprising:

an altitude sensor configured to sense aircraft altitude and supply the altitude signal representative thereof to the controller; and

an attitude sensor configured to sense aircraft attitude and supply the attitude signal representative thereof to the controller.

11. The system of claim 1, further comprising:

a bearing sump exit temperature sensor configured to sense bearing sump lubricant exit temperature and supply the temperature signal to the controller.