Aircraft Failure Diagnostic Method and System

• US 20080249678A1
• Filed: 09/19/2006
• Published: 10/09/2008
• Est. Priority Date: 09/23/2005
• Status: Abandoned Application

• Current Assignee: Thales SA
• Original Assignee: Thales SA
• Inventors: Bailly, Carine, Albouy, Christian
• Application Number:
  US12/066,529
• Publication Number:
  US 20080249678A1
• Time in Patent Office: Days
• US Class Current: 701/29
• CPC Class Codes: G05B 23/0281 Quantitative, e.g. mathematical distance; Clustering; Neural networks; Statistical analysis

Abstract

The present invention relates to an aircraft failure diagnostic method and system. The method includes one configuration phase defining the possible correlations between the detectable faults. Each of these correlations are associated with data pertinently describing the circumstances of the malfunction and appropriate failure-repair operations. A phase of correlating the detected fault is performed phase of recovering the data describing the circumstances of the malfunction and a phase of determining failure-repair operations is then performed.

Claims

1. An aircraft failure diagnostic method,

one configuration phase defining the possible correlations between the detectable faults, associating, with each of these correlations, data pertinently describing the circumstances of the malfunction and appropriate failure-repair operations, the relations thus defined being modeled in the form of a matrix with i rows and (m+n+p) columns, where i, m, n and p are nonzero integers, i being the number of distinct fault correlations, m being the maximum number of faults which can be correlated, n being the maximum number of data which pertinently describe the circumstances of a malfunction and which can be recovered and p being the maximum number of failure-repair operations which can be indicated;

one phase of correlating the detected faults;

one phase of recovering the data describing the circumstances of the malfunction; and

one phase of determining failure-repair operations.

2. The aircraft failure diagnostic method as claimed in claim 1, wherein the detectable faults include BITE maintenance messages issued by avionics equipment.

3. The aircraft failure diagnostic method as claimed in claim 1 wherein the detectable faults include alarm messages sent to the pilot.

4. An aircraft failure diagnostic system, comprising:

an apparatus for storing data defining the possible correlations between the detectable faults, associating, with each of these correlations, data pertinently describing the circumstances of the malfunction and appropriate failure-repair operations, in the form of a matrix with i rows and (m+n+p) columns, where i, m, n and p are nonzero integers, i being the number of distinct fault correlations, m being the maximum number of faults which can be correlated, n being the maximum number of data which pertinently describe the circumstances of a malfunction and which can be recovered and p being the maximum number of failure-repair operations which can be indicated;

a module for correlating the detected faults;

a module for recovering the data describing the circumstances of the malfunction;

a module for determining failure-repair operations.