Flight control system for aircraft and test for testing such a flight control system

• US 8,000,844 B2
• Filed: 06/27/2007
• Issued: 08/16/2011
• Est. Priority Date: 07/04/2006
• Status: Active Grant

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus France
• Inventors: Mottura, Alain
• Primary Examiner(s): Black; Thomas
• Assistant Examiner(s): LOUIE, WAE LENNY
• Application Number:
  US11/769,364
• Publication Number:
  US 20080009983A1
• Time in Patent Office: 1,511 Days
• Field of Search: 701/3, 701/33, 701/35, 701/36, 340/945, 455/66.1, 455/431, 455/98, 455/84
• 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

A test system for testing a flight control system of an aircraft includes a test device that: (1) accesses information available from the flight control system and (2) controls a computer of the flight control system.

Claims

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

said flight control system which comprises at least one flight control computer which comprises;

a first processor that implements a functional mode;

a second processor that implements a test mode, in which the flight control computer can be subjected to commands received from the exterior;

a switch that switches between said first and second processors; and

an interface that transmits, in the test mode, to the exterior information available in said flight control computer and receives commands from the exterior; and

a test device which comprises a connector that connects, in a detachable manner, to a communication bus of said flight control computer, and which cooperates with said second processor in a test phase, wherein;

said interface transmits, in the functional mode, to the exterior the information available in said flight control computer; and

said test device operates in one of the following two operational phases;

a test phase, in which said test device cooperates with said second processor of the flight control computer which is then in the test mode so as to allow the taking over of said flight control computer, said taking over comprising sending commands to the flight control computer and having access to information generated by such taking over; and

a data reception phase, in which said test device cooperates with said first processor of the flight control computer which is then in the functional mode so as to have access in real time to the information, including fault indications, which is available on said flight control computer, without affecting its behavior.

2. The test system as claimed in claim 1, further comprising:

a plurality of flight control computers, wherein

each of said flight control computers comprises first and second processors, a switch, and an interface.

3. The test system as claimed in claim 1, further comprising a securing section that secures the activation of the test mode.

4. The test system as claimed in claim 1, wherein:

said flight control system comprises a plurality of flight control computers, and

said test device connects, through the communication bus, to all of the flight control computers and cooperates with the flight control computers.

5. The test system as claimed in claim 4, wherein:

in the test phase, the flight control computers can be in the test mode independently from each other, and

when some of said flight control computers are in the functional mode and others in the test mode, the flight control computers which are in the test mode comply with all of the logics of the flight control system so as not to create functioning that leads to damage of the components of said flight control system.

6. The test system as claimed in claim 1, wherein said test device comprises at least one recorder that records, on at least one recording medium, information received from said flight control system.

7. The test system as claimed in claim 1, wherein said test device comprises at least one display that displays, on at least one display screen, information received from said flight control system.

8. The test system as claimed in claim 1, wherein said test device accesses, in the data reception phase, at least some of the following information:

characteristics of control surfaces of the aircraft;

characteristics of piloting devices of the aircraft;

information relating to faults in systems of the aircraft;

a status of computers of the aircraft; and

a status of a hydraulic system of the aircraft.

9. The test system as claimed in claim 1, wherein said test device, in the test phase:

displays in real time at least one input available on at least one flight control computer;

activates at least one output of at least one flight control computer; and

displays faults in real time.

10. The test system as claimed in claim 1, wherein said test device furthermore comprises an evolution tracing section that traces the evolution in real time of an item of information received from said flight control system.

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

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

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

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

15. A test system for an aircraft for testing a flight control system of the aircraft, said test system comprising:

said flight control system which comprises a plurality of flight control computers which each comprise;

a first processor that implements a functional mode;

a second processor that implements a test mode, in which the flight control computer can be subjected to commands received from the exterior;

a switch that switches between said first and second processors; and

an interface that transmits, in the test mode, to the exterior information available in said flight control computer and receives commands from the exterior; and

a test device which comprises a connector that connects, in a detachable manner, to said flight control computers, and which cooperates with said second processors in a test phase, wherein;

said interface transmits, in the functional mode, to the exterior the information available in said flight control computers; and

said test device operates in one of the following two operational phases;

a test phase, in which said test device cooperates with said second processors of the flight control computers which are then in the test mode so as to allow the taking over of said flight control computers, said taking over comprising sending commands to the flight control computers and having access to information generated by such taking over; and

a data reception phase, in which said test device cooperates with said first processors of the flight control computers which are then in the functional mode so as to have access in real time to the information, including fault indications, which is available on said flight control computers, without affecting their behavior.

16. The test system of claim 15, wherein:

in the test phase, the flight control computers can be in the test mode independently from each other, and

when some of said flight control computers are in the functional mode and others in the test mode, the flight control computers which are in the test mode comply with all of the logics of the flight control system so as not to create functioning that leads to damage of the components of said flight control system.

17. A test system for an aircraft for testing a flight control system of the aircraft, said test system comprising:

said flight control system which comprises at least one flight control computer which comprises;

a first processor that implements a functional mode;

a second processor that implements a test mode, in which the flight control computer can be subjected to commands received from the exterior;

a switch that switches between said first and second processors; and

an interface that transmits, in the test mode, to the exterior information available in said flight control computer and receives commands from the exterior; and

an automatic test station which comprises a connector that connects, in a detachable manner, to said flight control computer, and which cooperates with said second processor in a test phase, wherein;

said interface transmits, in the functional mode, to the exterior the information available in said flight control computer;

said automatic test station operates in one of the following two operational phases;

a test phase, in which said automatic test station cooperates with said second processor of the flight control computer which is then in the test mode so as to allow the taking over of said flight control computer, said taking over comprising sending commands to the flight control computer and having access to information generated by such taking over; and

a data reception phase, in which said automatic test station cooperates with said first processor of the flight control computer which is then in the functional mode so as to have access in real time to the information, including fault indications, which is available on said flight control computer, without affecting its behavior; and

said automatic test station comprises an evolution tracing section that traces the evolution in real time of information received from said flight control system.