Fault detection and isolation with analysis of built-in-test results

• US 20060120181A1
• Filed: 10/04/2005
• Published: 06/08/2006
• Est. Priority Date: 10/05/2004
• Status: Abandoned Application

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Bestle, Edward R., Berbaum, Richard
• Application Number:
  US11/241,937
• Publication Number:
  US 20060120181A1
• Time in Patent Office: Days
• US Class Current: 365/191
• CPC Class Codes: G06F 11/273 Tester hardware, i.e. output processing circuits G06F11/263 takes precedence

Abstract

A method for detecting and isolating faults in a complex system using a meta-analysis of subsystem built-in-test (BIT) results is disclosed. Subsystem BIT results may be combined with each other and with a representation of the complex system architecture and operational characteristics. A meta-analysis of the BIT results of individual modules, for example, commercial-off-the-shelf modules, may provide a diagnostic capability of a higher scope than individual subsystem BIT.

Claims

1. A computer system for detecting and isolating a fault in a helicopter using an analysis of subsystem test results, said computer system comprising:

a processor; and

a memory including software instructions adapted to cause the computer system to perform the steps of;

receiving a helicopter test result including a first subsystem test result from a first built-in-test in a first weapons replaceable assembly and a second subsystem test result from a-second built-in-test in a second weapons replaceable assembly, wherein the first weapons replaceable assembly is different from the second weapons replaceable assembly;

detecting the fault in the helicopter based on the helicopter test result;

selecting a group of fault combinations based on a system architecture of the helicopter and a representation of an operational characteristic of the helicopter;

evaluating the first subsystem test result and the second subsystem test result at a system level based on the group of fault combinations to determine candidate faults; and

isolating a root cause of the fault from among the candidate faults by performing a reasonableness analysis of the helicopter test result including cross referencing related tests and comparing the first subsystem test result and the second subsystem test result, wherein related tests are predetermined based on the system architecture of the helicopter and the operational characteristic of the helicopter, and

wherein the computer system forms a portion of an integrated electronic technical manual.

2. The computer system of claim 1, wherein the first and second subsystem test results are compared in order to validate interface operation and check data transfer status.

3. The computer system of claim 1, wherein the processor and memory are distributed between the integrated electronic technical manual and the helicopter such that the integrated electronic technical manual and the helicopter each execute a portion of the software instructions.

4. A computer program product for enabling a computer to detect and isolate a fault in an aircraft using a meta-analysis of built-in-test results, said computer program product comprising:

software instructions for enabling the computer to perform predetermined operations; and

a computer readable medium bearing the software instructions;

the predetermined operations including the steps of;

receiving an aircraft test result including a first subsystem test result and a second subsystem test result;

detecting the fault in the aircraft based on the aircraft test result;

selecting a group of fault combinations based on an architecture of the aircraft subsystems and a representation of an operational characteristic of the aircraft;

evaluating the first subsystem test result and the second subsystem test result at a system level based on the group of fault combinations to determine candidate faults; and

isolating a root cause of the fault in the aircraft at a system level.

5. The computer program product of claim 4, wherein the step of isolating a root cause of the fault in the aircraft at a system level comprises performing a meta-analysis of the aircraft test result.

6. The computer program product of claim 5, wherein the meta-analysis of the aircraft test result includes cross-referencing selected subsystem tests.

7. The computer program product of claim 6, wherein the meta-analysis of the aircraft test result includes comparing the first subsystem test result and the second subsystem test result.

8. The computer program product of claim 5, wherein the selected subsystem tests are determined based on the system architecture of the aircraft and the operational characteristic of the aircraft.

9. The computer program product of claim 4, wherein the aircraft is a helicopter.

10. The computer program product of claim 4, wherein the computer is included in an integrated electronic technical manual.

11. A method for detecting and isolating a fault in a complex system, said method comprising:

providing a complex system test result including a first subsystem test result and a second subsystem test result;

detecting the fault in the complex system based on the complex system test result; and

isolating a root cause of the fault through a meta-analysis of the first subsystem test results and the second subsystem test result;

wherein the first subsystem test result is from a first built-in-test and the second subsystem test result is from a second built-in-test different from the first built-in-test, and wherein the first subsystem test result is communicated in a first protocol and the second subsystem test result is communicated in a second protocol not designed for compatibility with the first protocol.

12. The method of claim 11, wherein the meta-analysis includes cross referencing related tests.

13. The method of claim 11, wherein the meta-analysis includes comparing the first subsystem test result and the second subsystem test result.

14. The method of claim 11, wherein the meta-analysis includes validating interface operation and checking data transfer status.

16. The method of claim 11, wherein the meta-analysis includes combining the first subsystem test result and the second subsystem test result.

17. The method of claim 11, wherein the meta-analysis includes combining the complex system test result with a representation of the complex system architecture.

18. The method of claim 11, wherein the meta-analysis includes combining the complex system test result with an operational characteristic of the complex system.

19. The method of claim 11, wherein the complex system is an aircraft.

20. The method of claim 11, wherein the complex system is a helicopter.

15. The method of 12, wherein related tests are selected based on a system architecture of the complex system and operational characteristics of the complex system.