Interactive diagnostic display system and method for an aircraft

Patent metadata

Field	Value
Publication number	US-9309009-B1
Application number	US-201414575047-A
Country	US
Kind code	B1
Filing date	Dec 18, 2014
Priority date	Dec 18, 2014
Publication date	Apr 12, 2016
Grant date	Apr 12, 2016

Abstract

A diagnostic display system is provided for diagnosing avionics components of an aircraft using an interactive display accessible to a user in real time. A central diagnostic module receives at least one signal from a plurality of sensors for the aircraft, and at least one parameter from a related avionics system associated with the aircraft. A component information module provides operational status information about at least one of the avionics components of the aircraft, and provides a detailed operational status configuration of each avionics component using a plurality of status messages stored in a database via a network. The central diagnostic module assesses a current operational status of the aircraft by evaluating the operational status configuration illustrated in the display for establishing a visual link between the status messages associated with the avionics components of the aircraft.

First claim

What is claimed is:

1. A diagnostic display system for diagnosing avionics components of an aircraft using an interactive display accessible to a user in real time, the system comprising:
a central diagnostic module configured for receiving at least one signal from a plurality of sensors for the aircraft, and at least one parameter from a related avionics system associated with the aircraft; and
a component information module configured for providing operational status information about at least one of the avionics components of the aircraft, and providing a detailed operational status configuration of each avionics component using a plurality of status messages stored in a database via a network;
wherein the central diagnostic module assesses a current operational status of the aircraft by evaluating the operational status configuration illustrated in the display for establishing a visual link between the plurality of status messages associated with the avionics components of the aircraft.

2. The system of claim 1 , further comprising an interface module configured for controlling operation of the plurality of sensors, the at least one parameter, the network, and other related system devices, services, and applications associated with the diagnostic display system.

3. The system of claim 1 , further comprising a detection module configured for examining the at least one signal and parameter for detecting a fault of the avionics component based on a predetermined set of rules.

4. The system of claim 3 , wherein the detection module monitors the operational status of the aircraft for a predetermined time period, and identifies the fault of the avionics component based on an anomaly analysis in communication with the database.

5. The system of claim 3 , wherein the detection module retrieves at least a portion of diagnostic service data associated with the aircraft from the database for assisting in identifying the fault of a current operational status of the aircraft.

6. The system of claim 1 , further comprising a diagnostics module configured for analyzing a detected fault of the avionics component of the aircraft based on a set of predetermined thresholds.

7. The system of claim 6 , wherein the diagnostics module evaluates the detected fault by applying a set of predetermined queries in response to erroneous operation of at least one of the avionics components as represented by the at least one signal and parameter.

8. The system of claim 6 , wherein when the diagnostics module determines that the detected fault is out of an acceptable range based on the predetermined thresholds, the plurality of status messages associated with the avionics components are selected for illustration on the interactive display.

9. The system of claim 1 , further comprising a categorization module configured for categorizing the plurality of status messages based on a hierarchical level assigned to each status message.

10. The system of claim 9 , wherein the categorization module divides the plurality of status messages into an operational level and a functional level.

11. The system of claim 10 , wherein the categorization module further divides at least one of the operational and functional levels into one or more subcategories based on an operational connection of the avionics components.

12. The system of claim 10 , wherein the operational level includes the plurality of status messages associated with at least one of a flight section, a navigation section, and a communication section.

13. The system of claim 10 , wherein the functional level includes the plurality of status messages that are subordinate to the plurality of status messages of the corresponding operational level.

14. The system of claim 1 , further comprising a display module configured for illustrating the plurality of status messages based on at least one of a hierarchical level assigned to each status message and an operational relationship between the avionics components of the aircraft.

15. The system of claim 1 , further comprising a tile display system for illustrating the plurality of status messages, the tile display system including a toggle button for selectively displaying a message time associated with the toggle button.

16. A computer-implemented method for diagnosing avionics components of an aircraft using an interactive display accessible to a user in real time, the method comprising:
receiving at least one signal from a plurality of sensors for the aircraft, and at least one parameter from a related avionics system associated with the aircraft;
providing operational status information about at least one of the avionics components of the aircraft;
providing a detailed operational status configuration of each avionics component using a plurality of status messages stored in a database via a network;
assessing a current operational status of the aircraft by evaluating the operational status configuration illustrated in the display; and
establishing a visual link between the plurality of status messages associated with the avionics components of the aircraft.

17. The method of claim 16 , further comprising examining the at least one signal and parameter for detecting a fault of the avionics component based on a predetermined set of rules.

18. The method of claim 16 , further comprising analyzing a detected fault of the avionics component of the aircraft based on a set of predetermined thresholds.

19. The method of claim 16 , further comprising categorizing the plurality of status messages based on a hierarchical level assigned to each status message.

20. The method of claim 16 , further comprising illustrating the plurality of status messages based on at least one of a hierarchical level assigned to each status message and an operational relationship between the avionics components of the aircraft.

Assignees

• Airbus Operations Sas

Inventors

• Poux Thibaut T
• Giuliano Sebastien S
• Larrieu Clement

Classifications

• G07C5/0808

  Diagnosing performance data (testing of vehicles G01M17/00; testing of electrical installation on vehicles G01R31/005) · CPC title

• G07C5/008

  communicating information to a remotely located station (transmission systems for measured values G08C) · CPC title

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title

• G07C5/0825 Primary

  using optical means · CPC title

• G05B23/0272

  Presentation of monitored results, e.g. selection of status reports to be displayed; Filtering information to the user · CPC title