FLIGHT CONTROL SYSTEM FOR AIRCRAFT AND TEST FOR TESTING SUCH A FLIGHT CONTROL SYSTEM

• US 20080009983A1
• Filed: 06/27/2007
• Published: 01/10/2008
• Est. Priority Date: 07/04/2006
• Status: Active Grant

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus France
• Inventors: MOTTURA, Alain
• Granted Patent: US 8,000,844 B2
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: G05D 1/0055 with safety arrangements
• CPC Class Codes: G06F 11/2236 to test CPU or processors

Abstract

• • Flight control system for aircraft and test system for testing such a flight control system.
  • The test system (1) comprises a test device (12) which makes it possible to have access to the information available on a flight control system (2) and to take over at least one computer (3) of that flight control system (2).

Claims

1. A test system for an aircraft for testing a flight control system (2) of the aircraft, said test system (1) comprising:

said flight control system (2) which comprises at least one flight control computer (3) which comprises;

a first processing means (4) able to implement a functional mode;

a second processing means (5) which is able to implement a test mode, in which the flight control computer (3) can be subjected to commands received from the exterior;

switching means (6) making it possible to carry out switching between said first and second processing means (4, 5); and

interface means (9) making it possible, in the test mode, to transmit to the exterior information available in said flight control computer (3) and to receive commands from the exterior; and

a test device (12) which comprises means of connection (13) making it possible to connect, in a detachable manner, to said flight control computer (3), and which is able to cooperate with said second processing means (5) in a test phase,

wherein;

said interface means (9) make it possible, in the functional mode, to transmit to the exterior information available in said flight control computer (3); and

said test device (12) is able to be put into one of the following two operational phases;

a test phase, in which it cooperates with said processing means (5) of the flight control computer (3) which is then in test mode in order to allow the taking over of said flight control computer (3) consisting at least in sending commands to the latter and having access to information generated by such a taking over; and

a data reception phase, in which it cooperates with said first processing means (4) of the flight control computer (3) which is then in functional mode in order to have access in real time to all of the information, including fault indications, which is available on said flight control computer (3), without affecting its behavior.

2. The test system as claimed in claim 1, wherein it comprises a plurality of flight control computers (3) and wherein each of said flight control computers (3) comprises first and second processing means (4, 5), switching means (6) and interface means (9).

3. The test system as claimed in claim 1, wherein it furthermore comprises securing means (21) for securing the activation of the test mode.

4. The test system as claimed in claim 1, wherein said flight control system (2) comprises a plurality of flight control computers (3) and wherein said test device (12) is able to be connected, by means of said connecting means (13) to all of these flight control computers (3) and is able to cooperate with the latter.

5. The test system as claimed in claim 4, wherein, in the test phase, the flight control computers (3) can be in test mode independently from each other, and wherein, in the case in which some of said flight control computers (3) are in functional mode and others in test mode, the flight control computers (3) which are in test mode comply with all of the logics of the flight control system (2) in order not to create functioning able to lead to damage of the components of said flight control system (2).

6. The test system as claimed in claim 1, wherein said test device (12) comprises at least one recording means (17) making it possible to record, on at least one recording medium (18), information received from said flight control system (2).

7. The test system as claimed in claim 1, wherein said test device (12) comprises at least one display means (15) making it possible to present, on at least one display screen (16) information received from said flight control system.

8. The test system as claimed in claim 1, wherein said test device (12) is formed in such a way as to have access, in the data reception phase, to at least some of the following information:

characteristics of the control surfaces of the aircraft;

characteristics of the piloting devices of the aircraft;

information relating to faults in the systems of the aircraft;

the status of the computers of the aircraft; and

the status of a hydraulic system of the aircraft.

9. The test system as claimed in claim 1, wherein said test device (12) is formed in such a way as to make it possible, in the test phase:

to display in real time at least one input available on at least one flight control computer (3);

to activate at least one output of at least one flight control computer (3); and

to display faults in real time.

10. The test system as claimed in claim 1, wherein said test device (12) furthermore comprises a means (20) making it possible to trace the evolution in real time of an item of information received from said flight control system (2).

11. The test system as claimed in claim 1, wherein it furthermore comprises a secure gateway (19), by the intermediary of which the test device (12) can be linked with at least one communication bus (14) of the aircraft, interconnecting at least the flight control computers (3) of the flight control system (2).

12. The test system as claimed in claim 1, wherein said test device (12) represents a man/machine interface tool which comprises at least a display screen (16) and at least a unit (22) allowing an operator to enter data.

13. The test system as claimed in claim 12, wherein said test device (12) is a portable computer.

14. The test system as claimed in claim 1, wherein said test device corresponds to an automatic test station.