Distributed flight control system

• US 8,600,583 B2
• Filed: 02/04/2009
• Issued: 12/03/2013
• Est. Priority Date: 02/08/2008
• Status: Active Grant

• Current Assignee: Airbus Operations (European Aeronautic Defence and Space Company EADS NV)
• Original Assignee: Airbus Operations SAS (Airbus SE)
• Inventors: Fervel, Marc, Aubert, Jean-Jacques, Maussion, Antoine
• Primary Examiner(s): Mawari, Redhwan K
• Application Number:
  US12/865,949
• Publication Number:
  US 20110118906A1
• Time in Patent Office: 1,763 Days
• Field of Search: 701/3, 701/16, 701/20
• US Class Current: 701/3
• CPC Class Codes: B64C 13/503 Fly-by-Wire

Abstract

A flight control system for an aircraft, controlling a plurality of actuators adapted to actuate control surfaces of the aircraft, including: at least one communications bus; at least one computer situated in the avionics bay of the aircraft, and adapted to calculate flight commands and to transmit them over the bus in the form of command messages; and at least a first remote terminal connected to the bus, adapted to control a control surface actuator, and to acquire the state of the actuator from information provided by at least a first sensor, the first terminal receiving command messages from the computer and transmitting electrical orders to the actuator as a function of the command messages received in this way, and also transmitting messages to the computer, at its request, relating to the state of the actuator as a function of the information provided by the first sensor.

Claims

1. A flight control system for an aircraft for controlling a plurality of actuators configured to actuate corresponding control surfaces of the aircraft, the system comprising:

at least one communications bus;

at least one computer situated in an avionics bay of the aircraft, and configured to calculate flight commands and to transmit the calculated flight commands over said bus in the form of command messages;

at least a first remote terminal connected to said bus, configured to control a control surface actuator, to acquire a state of said control surface actuator from information provided by at least a first sensor coupled to the control surface actuator, to receive the command messages from the computer, to transmit electrical orders to said control surface actuator as a function of the received command messages, and to transmit messages to the computer, responsive to a first request of the computer, relating to the state of said control surface actuator as a function of the information provided by said first sensor; and

at least one second remote terminal connected to said bus, configured to acquire a state of a control surface from information provided by a second sensor coupled to the control surface, and to transmit messages to the computer, responsive to a second request of the computer, relating to the state of said control surface as a function of information provided by said second sensor,

wherein each said at least one computer includes a first channel and a second channel, said second channel being configured to monitor operation of said first channel.

2. An aircraft flight control system according to claim 1, wherein said bus is comprised of a differentially-powered twisted pair, and exchanges over said bus are performed in a half-duplex mode, using a master-slave protocol.

3. A flight control system according to claim 1, wherein

said first channel is configured to calculate flight commands, to send the calculated flight commands as command messages, to a plurality of said first remote terminals, to receive acknowledgments of receipt from said first remote terminals, and to send requests to said first remote terminals to obtain in return respective states of corresponding control surface actuators respectively controlled by said first remote terminals and of control surfaces moved by the corresponding control surface actuators, and

said second channel is configured to calculate flight commands, to transform the calculated flight commands into command messages, and to listen to and to record command messages passing over said bus, coming from and going to said first channel, and

the command messages of said first channel are compared to the command messages of said second channel.

4. A flight control system according to claim 1,

wherein the flight control system includes said bus as a single bus,

said first channel is configured to calculate flight commands, to send the calculated flight commands as command messages to a plurality of said first remote terminals, to receive acknowledgments of receipt from said first remote terminals, and to send requests to said first remote terminals to obtain in return respective states of corresponding control surface actuators respectively controlled by said first remote terminals and of control surfaces moved by the corresponding control surface actuators, said first channel being connected to said bus via a connection that is controlled by a bus controller,

said second channel is connected to said bus controller, and is configured to calculate flight commands and to transform the calculated flight commands into command messages, and to listen to and to record command messages transmitted and received from said bus controller, coming from and going to said first channel, and

the command messages of said first channel are compared to the command messages of said second channel.

5. A flight control system according to claim 1,

wherein the flight control system includes said bus as a single bus,

said first channel is configured to calculate flight commands, to send the calculated flight commands as command messages to a plurality of said first remote terminals, to receive acknowledgments of receipt from said first remote terminals, and to send requests to said first remote terminals to obtain in return respective states of corresponding control surface actuators respectively controlled by said first remote terminals and of control surfaces moved by the corresponding control surface actuators, said first channel being connected to said bus via a connection that is controlled by a bus controller,

said second channel is connected to said first channel and is configured to calculate flight commands and to transform the calculated flight commands into command messages, to receive messages from and to said first channel, relayed from said first channel to said second channel, and

the command messages of said first channel are compared to the command messages of said second channel.

6. A flight control system according to claim 3, wherein said first remote terminal includes:

a first channel configured to receive command messages from the computer, to acknowledge receipt of the received command messages, and to transmit electrical orders to said control surface actuator controlled by said first remote terminal; and

a second channel configured to receive requests from the computer and to return messages relating to at least one of the state of said control surface actuator and the state of said corresponding control surface movable by said control surface actuator.

7. A flight control system according to claim 6, wherein said first and second channels of the computer and said first and second channels of said first remote terminal are connected to said bus as a single bus.

8. A flight control system according to claim 7,

wherein said first channel of the computer includes a bus controller in series with a first transceiver and a first transformer providing coupling to said bus,

said second channel of the computer includes a bus monitor module in series with a second transceiver and a second transformer providing coupling to said bus, and

each of said first and second channels of said first remote terminal includes a control module in series with a third transceiver and a third transformer providing coupling to said bus.

9. A flight control system according to claim 6,

wherein said at least one communications bus includes a first bus and a second bus,

said first channel of the computer and said first channel of said first remote terminal are connected to said first bus, and

said second channel of the computer and said second channel of said first remote terminal are connected to said second bus.

10. A flight control system according to claim 9,

wherein each of said first and second channels of the computer includes a bus controller in series with a first transceiver and a first transformer providing coupling to said first and second buses, respectively, and

each of said first and second channels of said first remote terminal includes a control module in series with a second transceiver and a second transformer providing coupling to said first and second buses, respectively.

11. A flight control system according to claim 6,

wherein said at least one communications bus includes a first bus and a second bus,

said first channel of said computer includes a bus controller in series with two first branches in parallel, each said first branch having a first transceiver in series with a first transformer for coupling said first bus to said second bus,

said second channel of said computer includes a monitor module in series with two second branches in parallel, each said second branch having a second receiver in series with a second transformer for providing coupling to said first and second buses, respectively, and

each of said first and second channels of said first remote terminal includes a control module in series with two third branches in parallel, each said third branch having a third transceiver in series with a third transformer for providing coupling to said first and second buses, respectively.

12. An aircraft having a plurality of said control surfaces configured to be operated by corresponding ones of said control surface actuators, the aircraft comprising the flight control system according to claim 1.

13. A flight control system according to claim 1,

wherein said at least one computer includes said computer and another identical computer, said computer being a primary flight control computer and said another computer being a secondary flight control computer, and

wherein, in a normal operation mode said first channel of said another computer is inhibited from outputting the command messages to said bus.

14. A flight control system according to claim 13,

wherein, when a malfunction affects said first channel of said computer, the malfunction is detected by said second channel of said computer, and said computer is deactivated by said second channel of said computer, and

responsive to the deactivation of said computer, said another computer is activated as the primary flight control computer.

15. A flight control system for an aircraft for controlling a plurality of actuators configured to actuate corresponding control surfaces of the aircraft, the system comprising:

at least one communications bus;

at least one computer situated in an avionics bay of the aircraft, and configured to calculate flight commands and to transmit the calculated flight commands over said bus in the form of command messages; and

at least a first remote terminal connected to said bus, configured to control a control surface actuator, to acquire a state of said control surface actuator from information provided by at least a first sensor coupled to the control surface actuator, to transmit electrical orders to said control surface actuator as a function of the received command messages, to transmit messages to the computer, responsive to a first request of the computer, relating to the state of the control surface actuator as a function of the information provided by said first sensor,

wherein the first remote terminal is also configured to acquire a state of a control surface moved by said actuator from information provided by at least one second sensor coupled to the control surface, and to transmit messages to the computer, responsive to a second request of the computer, relating to the state of said control surface as a function of information provided by said second sensor, and

each said at least one computer includes a first channel and a second channel, said second channel being configured to monitor operation of said first channel.

16. A flight control system according to claim 15,

wherein said at least one computer includes said computer and another identical computer, said computer being a primary flight control computer and said another computer being a secondary flight control computer, and

wherein, in a normal operation mode said first channel of said another computer is inhibited from outputting the command messages to said bus.

17. A flight control system according to claim 16,

wherein, when a malfunction affects said first channel of said computer, the malfunction is detected by said second channel of said computer, and said computer is deactivated by said second channel of said computer, and

responsive to the deactivation of said computer, said another computer is activated as the primary flight control computer.