DISTRIBUTED FLY-BY-WIRE SYSTEM

• US 20110251739A1
• Filed: 03/16/2011
• Published: 10/13/2011
• Est. Priority Date: 04/09/2010
• Status: Abandoned Application

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Zavisek, Michal, Hynek, Pavel, Tomas, Jan, Horniak, Frantisek, Prichystalova, Pavla
• Application Number:
  US13/049,718
• Publication Number:
  US 20110251739A1
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: B64C 13/505 having duplication or stand-by provisions
• CPC Class Codes: G05B 9/03 with multiple-channel loop, i.e. redundant control systems
• CPC Class Codes: G05D 1/0077 using redundant signals or controls
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A system includes a plurality of fly-by-wire control units to control flight control surfaces of an airplane, wherein each control unit is adapted to operate independently of other control units and directly control an actuator to control a control surface as a function of direct pilot control device input.

Claims

1. A system comprising:

a plurality of fly-by-wire control units to control flight control surfaces of an airplane, wherein each control unit is adapted to operate independently of other control units and directly control an actuator to control a control surface as a function of direct pilot control device input.

2. The system of claim 1 wherein each control unit is adapted to perform safety monitoring without input from other control units.

3. The system of claim 1 wherein each control unit is adapted to control its corresponding control surface with safety without input from other control units.

4. The system of claim 1 wherein each control unit is adapted to operate in a failure mode and process pilot control device input and perform safety monitoring without input from other control units.

5. The system of claim 1 wherein each control unit is directly coupled to the pilot control device.

6. The system of claim 1 wherein each control unit includes self monitoring functionality.

7. The system of claim 1 wherein each control unit includes digital closed loop functionality to control an actuator.

8. The system of claim 1 and further comprising a fly-by-wire bus coupled to each control unit to provide communications between the control units.

9. The system of claim 1 wherein the control units are adapted to reside separate from the actuators. H0026208

10. The system of claim 1 wherein the control units are adapted to be directly coupled to the actuators.

11. A control unit comprising:

an input to couple directly to pilot control device input;

an output to couple directly to an actuator to control a flight control surface; and

a processor coupled to the input and to the output to directly control the flight control surface via the actuator, while complying with predetermined control laws and safety monitoring independently performed by the processor, as a direct function of pilot control device input.

12. The control unit of claim 11 wherein the control unit is adapted to perform safety monitoring without input from other control units.

13. The control unit of claim 11 wherein the control unit is adapted to control its corresponding control surface with safety without input from other control units.

14. The control unit of claim 11 wherein the control unit is adapted to operate in a failure mode and process pilot control device input and perform safety monitoring without input from other control units.

15. The control unit of claim 11 wherein the control unit is directly coupled to the pilot control device.

16. The control unit of claim 11 wherein the control unit includes self monitoring functionality.

17. The control unit of claim 11 wherein the control unit includes digital closed loop control via a digital signal processor or field programmable gate array to control an actuator.

18. The control unit of claim 11 and further comprising a fly-by-wire bus coupled to each control unit to provide communications between the control units.

19. A computer implemented method comprising:

while operating in a normal mode;

receiving input from multiple control units and external systems via a fly-by-wire bus;

receiving input from a pilot control device;

executing control laws;

executing safety monitoring; and

controlling a flight surface via a directly coupled actuator; and

while operating in a failure mode;

exclusively receiving input from a directly coupled pilot control device;

executing control laws independent from other control units and external systems;

executing safety monitoring independent from other control units; and

controlling a flight surface via a directly coupled actuator.

20. The method of claim 19 wherein the method is implemented by a plurality of independently operable control units directly coupled to pilot input and actuators.