Method of fast reinitialization for instrument panel viewing device

• US 8,943,363 B2
• Filed: 10/12/2012
• Issued: 01/27/2015
• Est. Priority Date: 10/14/2011
• Status: Active Grant

• Current Assignee: Thales SA
• Original Assignee: Thales SA
• Inventors: Chabot, Philippe, Durieux, Florence, Lefort, Marc, Sanderson, Gordon
• Primary Examiner(s): Butler, Sarai
• Application Number:
  US13/651,335
• Publication Number:
  US 20130097461A1
• Time in Patent Office: 837 Days
• Field of Search: 714/25, 714/48
• US Class Current: 714/25
• CPC Class Codes: G01C 23/00 Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
• CPC Class Codes: G06F 11/3688 for test execution, e.g. scheduling of test suites
• CPC Class Codes: G06F 3/14 Digital output to display device ; Cooperation and interconnection of the display device with other functional units
• CPC Class Codes: G09G 2380/12 Avionics applications

Abstract

The general field of the invention is that of the management of the faults of the viewing devices used on aircraft. An aircraft instrument panel viewing device comprises an electronic assembly, embedded software and a viewing screen. When the viewing device detects a fault arising after a predetermined time of proper operation, the reinitialization method according to the invention executes just the software verification tests without executing the electronic assembly verification tests termed “safety tests”, no specific presentation of fault being displayed on the viewing screen. The duration for which the pilot is deprived of information is thus considerably reduced.

Claims

1. A method for reinitializing an aircraft instrument panel viewing device comprising an electronic assembly, embedded software and a viewing screen, the method comprising:

detecting a fault associated with the aircraft instrument panel viewing device during an operation mode of the aircraft instrument panel viewing device, wherein the fault is determined to arise after a predetermined time of proper operation in the operation mode of the aircraft instrument panel viewing device; and

executing a verification test that resets and tests the embedded software that controls the aircraft instrument panel before execution of a different verification safety test that resets and tests the embedded software and the electronic assembly and clears a display of the viewing screen during the safety test, wherein no specific presentation of fault is displayed on the viewing screen during execution of the verification test.

2. The method for reinitializing the aircraft instrument panel viewing device according to claim 1, wherein the origin of the fault is recorded in the means of storage of the viewing device.

3. The method for reinitializing the aircraft instrument panel viewing device according to claim 1, wherein when a second fault arises after a first fault before a predetermined time of proper operation of the viewing device, the viewing device executes the entirety of the software and electronic assembly verification tests, a specific presentation of fault being displayed during this verification.

4. The method for reinitializing the aircraft instrument panel viewing device according to claim 1, wherein

if, the safety tests having been run a first time after failure of the verification test of the embedded software that controls the aircraft instrument panel, the result of the safety tests is not correct, the viewing device executes the safety tests a second time,

if, on completion of this second execution, the result of the safety tests is not correct, the viewing device executes the safety tests a third time,

if, on completion of this third execution, the result of the safety tests is not correct, the viewing device is declared faulty, a specific presentation of fault being displayed on the viewing screen.

5. The method for reinitializing the aircraft instrument panel viewing device according to claim 1, wherein the software is produced according to the ARINC 653 standard.

6. A system, comprising:

an aircraft instrument panel viewing device that comprises an electronic assembly, embedded software, and a viewing screen;

a processor coupled with the aircraft instrument panel viewing device to

detect a fault associated with the aircraft instrument panel viewing device during an operation mode of the aircraft instrument panel viewing device, wherein the fault is determined to arise after a predetermined time of proper operation in the operation mode of the aircraft instrument panel viewing device, and

execute a verification test that resets and tests the embedded software that controls the aircraft instrument panel before execution of a different verification safety test that resets and tests the embedded software and the electronic assembly and clears a display of the viewing screen during the safety test, wherein no specific presentation of fault is displayed on the viewing screen during execution of the verification test.