Apparatus and method for backup control in a distributed flight control system

• US 8,235,328 B2
• Filed: 06/23/2011
• Issued: 08/07/2012
• Est. Priority Date: 01/17/2006
• Status: Active Grant

• Current Assignee: Gulfstream Aerospace Corporation (General Dynamics Corporation)
• Original Assignee: Gulfstream Aerospace Corporation (General Dynamics Corporation)
• Inventors: Hirvonen, Jukka Matti
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): BENEDIK, JUSTIN M
• Application Number:
  US13/167,447
• Publication Number:
  US 20110248121A1
• Time in Patent Office: 411 Days
• Field of Search: 244/194, 244/195, 244/196
• US Class Current: 244/194
• CPC Class Codes: B64C 13/504 using electro-hydrostatic actuators [EHA's]
• CPC Class Codes: B64C 13/505 having duplication or stand-by provisions
• CPC Class Codes: G05D 1/0077 using redundant signals or controls
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

Embodiments of the invention relate to a flight control system for controlling an aircraft during flight. The flight control system may include a primary controller configured to receive an input from a pilot and to output a primary control signal and a primary transmission path connected to the primary controller and configured to relay the primary control signal. The flight control system may also include a backup controller configured to receive the input from the pilot and to output a backup control signal and a backup transmission path connected to the backup controller and configured to relay the backup control signal. Additionally, the flight control system may include an actuator having a remote electronics unit configured to receive the primary control signal and the backup control signal and to determine if the primary control signal is available and valid. The remote electronics unit may be configured to output an actuator command based on the primary control signal if the primary control signal is available and valid and to output the actuator command based on the backup control signal if the primary control signal is unavailable or invalid.

Claims

1. A flight control system for controlling an aircraft, the flight control system comprising:

a first controller configured to receive a first input and to output a primary control signal;

a first transmission path coupled to the first controller and configured to relay the primary control signal;

a second controller configured to receive a second input and to output a backup control signal;

a second transmission path coupled to the second controller and configured to relay the backup control signal; and

an actuator having actuator electronics configured to receive the primary control signal along the first transmission path and the backup control signal along the second transmission path and configured to determine if the primary control signal is valid;

the actuator electronics located remotely from the primary controller and adjacent to the actuator and configured to output an actuator command based, at least in part, on the primary control signal if the primary control signal is valid and to output the actuator command based, at least in part, on the backup control signal if the primary control signal is not valid;

wherein the first transmission path is bi-directional; and

wherein the second transmission path is unidirectional.

2. The flight control system of claim 1, wherein:

the actuator electronics are further configured to transmit the backup control signal to the first controller via the first transmission path; and

the first controller is further configured to monitor the backup control signal and generate a backup control system status signal.

3. The flight control system of claim 1, further comprising:

a first data link between the first controller and the second controller;

a validation data generator in the first controller; and

validation data generated by the validation data generator and transmitted to the second controller via the data link, the validation data being included in the backup control signal.

4. The flight control system of claim 3, wherein:

the actuator electronics are further configured to transmit the validation data in the backup control signal to the first controller via the first transmission path; and

the first controller is further configured to generate a backup control system status signal based, at least in part, on a comparison of the validation data transmitted to the second controller and the validation data received from the actuator electronics.

5. The flight control system of claim 4, wherein the actuator electronics further comprises:

a first input/output module coupled to the first transmission path;

a second input/output module coupled to the second transmission path, the second input/output module being separate and independent from the first input/output module; and

a second data link between the second input/output module and the first input/output module;

wherein the validation data is transmitted from the second input/output module to the first input/output module and the first input/output module transmits the validation data to the first controller.

6. The flight control system of claim 5, wherein the first data link and second data link are optical links.

7. A flight control system for controlling an aircraft, the flight control system comprising:

a first controller configured to receive a first input and to output a primary control signal;

a bi-directional transmission path coupled to the first controller and configured to relay the primary control signal;

a second controller configured to receive a second input and to output a backup control signal;

a unidirectional second transmission path coupled to the second controller and configured to relay the backup control signal; and

an actuator having actuator electronics located remotely from the primary controller and adjacent to the actuator and configured to receive the primary control signal along the bi-directional transmission path and the backup control signal along the unidirectional transmission path and configured to determine if the primary control signal is valid;

wherein the actuator electronics is configured to output an actuator command based, at least in part, on the primary control signal if the primary control signal is valid and to output the actuator command based, at least in part, on the backup control signal if the primary control signal is not valid.

8. The flight control system of claim 7, wherein:

the actuator electronics are further configured to transmit the backup control signal to the first controller via the bi-directional transmission path; and

the first controller is further configured to monitor the backup control signal and generate a backup control system status signal.

9. The flight control system of claim 7, further comprising:

a first data link between the first controller and the second controller;

a validation data generator in the first controller; and

validation data generated by the validation data generator and transmitted to the second controller via the data link, the validation data being included in the backup control signal.

10. The flight control system of claim 9, wherein:

the actuator electronics are further configured to transmit the validation data in the backup control signal to the first controller via the bi-directional transmission path; and

the first controller is further configured to generate a backup control system status signal based, at least in part, on a comparison of the validation data transmitted to the second controller and the validation data received from the actuator electronics.

11. The flight control system of claim 10, wherein the actuator electronics further comprises:

a first input/output module coupled to the bi-directional transmission path;

a second input/output module coupled to the unidirectional transmission path, the second input/output module being separate and independent from the first input/output module; and

a second data link between the second input/output module and the first input/output module;

wherein the validation data is transmitted from the second input/output module to the first input/output module and the first input/output module transmits the validation data to the first controller.

12. A flight control system for controlling an aircraft, the flight control system comprising:

a first controller configured to receive an input and to output a primary control signal;

a bi-directional transmission path coupled to the first controller and configured to relay the primary control signal;

a second controller configured to receive the input and to output a redundant control signal;

a unidirectional transmission path coupled to the second controller and configured to relay the redundant control signal; and

an actuator having actuator electronics located remotely from the primary controller and adjacent to the actuator and configured to receive the primary control signal along the bi-directional transmission path and the redundant control signal along the unidirectional transmission path and configured to determine if the primary control signal is valid;

wherein the actuator electronics is configured to output an actuator command based, at least in part, on the primary control signal if the primary control signal is valid and to output the actuator command based, at least in part, on the backup control signal if the primary control signal is not valid.

13. The flight control system of claim 12, wherein:

the actuator electronics are further configured to transmit the backup control signal to the first controller via the bi-directional transmission path; and

the first controller is further configured to monitor the backup control signal and generate a backup control system status signal.

14. The flight control system of claim 12, further comprising:

a first data link between the first controller and the second controller;

a validation data generator in the first controller; and

validation data generated by the validation data generator and transmitted to the second controller via the data link, the validation data being included in the redundant control signal.

15. The flight control system of claim 14, wherein:

the actuator electronics are further configured to transmit the validation data in the redundant control signal to the first controller via the bi-directional transmission path; and

the first controller is further configured to generate a redundant control system status signal based, at least in part, on a comparison of the validation data transmitted to the second controller and the validation data received from the actuator electronics.

16. The flight control system of claim 15, wherein the actuator electronics further comprises:

a first input/output module coupled to the bi-directional transmission path;

a second input/output module coupled to the unidirectional transmission path, the second input/output module being separate and independent from the first input/output module; and

a second data link between the second input/output module and the first input/output module;

wherein the validation data is transmitted from the second input/output module to the first input/output module and the first input/output module transmits the validation data to the first controller.