Reconfigurable flight control surface actuation system and method

• US 20070108342A1
• Filed: 03/23/2006
• Published: 05/17/2007
• Est. Priority Date: 11/14/2005
• Status: Abandoned Application

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Hanlon, Casey, Wingett, Paul, Potter, Calvin
• Application Number:
  US11/387,583
• Publication Number:
  US 20070108342A1
• Time in Patent Office: Days
• US Class Current: 244/99.200
• CPC Class Codes: B64C 13/505 having duplication or stand-by provisions
• CPC Class Codes: B64C 13/506 overriding of personal controls; with automatic return to inoperative position

Abstract

A flight control surface actuation system, and the method implemented thereby, prevents an asymmetric secondary flight control surface deploy situation in the unlikely event one or more of the secondary flight control surfaces becomes inoperable. The system includes a control unit that receives one or more signals representative of operability of each of the secondary flight control surfaces. In response to these signal, the control unit determines the operability of each of the flight control surfaces and, upon determining that a flight control surface on one of the aircraft wings is inoperable, automatically moves, or inhibits movement of, one or more symmetric flight control surfaces on the other aircraft wing.

Claims

1. A flight control surface actuation system, comprising:

a plurality of flight control surface actuators, each flight control surface actuator configured to couple to a secondary flight control surface on either a first aircraft wing or a second aircraft wing, each flight control surface actuator coupled to receive power and operable, upon receipt thereof, to move its associated secondary flight control surface to a commanded position; and

a control unit configured to receive one or more signals representative of operability of each of the secondary flight control surfaces and operable, in response thereto;

(i) to determine the operability of each of the flight control surfaces and,

(ii) upon determining that a flight control surface on one of the first or second aircraft wings is inoperable, to automatically selectively supply or inhibit power to one or more of the flight control surface actuators that are adapted to be coupled to a secondary flight control surface on one of the second or first aircraft wings, respectively, to prevent an asymmetric flight control surface deploy condition.

2. The system of claim 1, further comprising:

a plurality of flight control surface position sensors, each flight control surface position sensor configured to couple to one of the secondary flight control surfaces and operable to (i) sense a position thereof and (ii) supply a flight control surface position signal representative thereof to the control unit,

wherein the flight control surface position signals are the one or more signals representative of the operability of each of the secondary flight control surfaces.

3. The system of claim 2, wherein:

each flight control surface position sensor comprises an actuator position sensor operable to sense a position of a flight control surface actuator and, in response, supply the flight control surface position signal representative thereof.

4. The system of claim 2, wherein:

the first aircraft wing includes a plurality of secondary flight control surfaces; and

the second aircraft wing includes a plurality of secondary flight control surfaces that are each symmetric to one of the plurality of secondary flight control surfaces on the first wing.

5. The system of claim 4, wherein the control unit, upon determining that a flight control surface on the first or second aircraft wing is inoperable, automatically selectively supplies or inhibits power to a flight control surface actuator that is adapted to be coupled to the symmetric secondary flight control surface on the second or first aircraft wing, respectively, to thereby prevent the asymmetric flight control surface deploy condition.

6. The system of claim 4, wherein the control unit is further operable, upon receipt of the flight control surface position signals, to:

(i) compare positions of the inoperable flight control surface and the symmetric flight control surface to determine a position difference magnitude;

(ii) if the determined position difference magnitude is at least a predetermined value, automatically supplying power to the flight control surface actuator configured to couple to the symmetric secondary flight control surface to move the symmetric secondary flight control surface to a position that is at least substantially equal to the position of the inoperable secondary flight control surface.

7. The system of claim 4, wherein the control unit is further operable, upon receipt of the flight control surface position signals, to:

(i) compare positions of the inoperable flight control surface and the symmetric flight control surface to determine a position difference magnitude;

(ii) if the determined position difference magnitude is less than a predetermined value, automatically inhibiting power to the flight control surface actuator configured to couple to the symmetric secondary flight control surface.

8. The system of claim 1, wherein the control unit is adapted to receive flight control surface position commands and is further operable, in response the received flight control surface position commands, to supply the power to the flight control surface actuators.

9. The system of claim 1, wherein:

selected ones of the plurality of flight control surface actuators are flap actuators that are each adapted to couple to a flap; and

selected ones of the plurality of flight control surface actuators are slat actuators that are each adapted to couple to a slat.

10. The system of claim 9, wherein:

at least some of the flap actuators are linear electromechanical actuators having an electric motor; and

at least some of the slat actuators are rotary electromechanical actuators having an electric motor.

11. The system of claim 10, further comprising:

a plurality of motor resolvers, each motor resolver coupled to one of the electric motors and operable to sense a rotational position thereof and supply a motor rotational position signal representative thereof,

wherein each of the electric motors is a brushless DC motor, and the control unit is coupled to receive the motor rotational position signals and is further operable, in response thereto, to supply the actuator position commands to the brushless DC motors in a manner that commutates the brushless DC motors.

12. A flight control surface actuation system, comprising:

a plurality of first flight control surface actuators, each first flight control surface actuator adapted to be coupled to a secondary flight control surface on a first aircraft wing, each first flight control actuator coupled to receive power and operable, upon receipt thereof, to move its associated secondary flight control surface to a commanded position;

a plurality of second flight control surface actuators, each second flight control surface actuator adapted to be coupled to a secondary flight control surface on a second aircraft wing having a plurality of secondary flight control surfaces that are each symmetric to one of the plurality of secondary flight control surfaces on the first wing, each second flight control surface actuator further coupled to receive power and operable, upon receipt thereof, to move its associated secondary flight control surface to a commanded position;

a plurality of first flight control surface position sensors, each first flight control surface position sensor associated with one of the first aircraft wing secondary flight control surface and operable to sense a position thereof and supply a first aircraft wing flight control surface position signal representative thereof;

a plurality of second flight control surface position sensors, each second flight control surface position sensor associated with one of the second aircraft wing secondary flight control surfaces and operable to sense a position thereof and supply a second aircraft wing flight control surface position signal representative thereof; and

a control unit coupled to receive the first and second aircraft wing flight control surface position signals and operable, in response thereto;

(i) to determine operability of each of the first and second flight control surface actuators and,

(ii) upon determining that a first or a second flight control surface actuator is inoperable, to automatically selectively supply or inhibit power to the second or first flight control surface actuators, respectively, that are adapted to be coupled to the symmetric flight control surface.

13. The system of claim 12, wherein the control unit is adapted to receive flight control surface position commands and is further operable, in response the received flight control surface position commands, to supply the power to the flight control surface actuators.

14. The system of claim 12, wherein:

the first flight control surface position sensors each comprise an actuator position sensor operable to sense a position of a first flight control surface actuator and, in response, supply the first aircraft wing flight control surface position signal representative thereof; and

the second flight control surface position sensors each comprise an actuator position sensor operable to sense a position of a second flight control surface actuator and, in response, supply the second aircraft wing flight control surface position signal representative thereof.

15. The system of claim 12, wherein:

the first flight control surface position sensors are each coupled to a first aircraft wing flight control surface and are each operable to sense the position thereof and supply the first aircraft wing flight control surface position signal; and

the second flight control surface position sensors are each coupled to a second aircraft wing flight control surface and are each operable to sense the position thereof and supply the second aircraft wing flight control surface position signal.

16. The system of claim 12, wherein the control unit is further operable, upon receipt of the flight control surface position signals, to:

(i) compare positions of the inoperable flight control surface and the symmetric flight control surface to determine a position difference magnitude; and

(ii) if the determined position difference magnitude is at least a predetermined value, automatically supplying power to the flight control surface actuator configured to couple to the symmetric secondary flight control surface to move the symmetric secondary flight control surface to a position that is at least substantially equal to the position of the inoperable secondary flight control surface.

17. The system of claim 12, wherein the control unit is further operable, upon receipt of the flight control surface position signals, to:

(i) compare positions of the inoperable flight control surface and the symmetric flight control surface to determine a position difference magnitude;

(ii) if the determined position difference magnitude is less than a predetermined value, automatically inhibit power to the flight control surface actuator configured to couple to the symmetric secondary flight control surface.

18. In an aircraft having at least first and second aircraft wings, the first aircraft wing having a plurality of secondary flight control surfaces that are each symmetric to a secondary flight control surface on the second wing, and each flight control surface on the first and second aircraft wings having one or more flight control surface actuators coupled thereto, a method of preventing an asymmetric flight control surface deploy condition, comprising the steps of:

determining operability of each of the plurality of secondary flight control surfaces; and

if it is determined that a secondary flight control surface on one of the first or second aircraft wings is inoperable, selectively moving, or inhibiting movement of, the symmetric secondary flight control surface on one of the second or first aircraft wings, respectively, to thereby prevent the asymmetric flight control surface deploy condition.

19. The method of claim 18, further comprising:

determining a position of the inoperable secondary flight control surface;

determining a position of the symmetric secondary flight control surface;

comparing the determined positions to determine a position difference magnitude; and

if the determined position difference magnitude is at least a predetermined value, automatically moving the symmetric secondary flight control surface to a position that is at least substantially equal to the position of the inoperable flight control surface.

20. The method of claim 18, further comprising:

determining a position of the inoperable secondary flight control surface;

determining a position of the symmetric secondary flight control surface;

comparing the determined positions to determine a position difference magnitude; and

if the determined position difference magnitude is less than a predetermined value, automatically inhibiting the movement the symmetric secondary flight control surface.