FLIGHT CONTROL ACTUATION SYSTEM

• US 20040195441A1
• Filed: 04/07/2003
• Published: 10/07/2004
• Est. Priority Date: 04/07/2003
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Kern, James I., Gaines, Louie T., Wingett, Paul T., Evans, Paul S.
• Granted Patent: US 6,827,311 B2
• Time in Patent Office: Days
• US Class Current: 244/99.5
• CPC Class Codes: B64C 13/50 using electrical energy

Abstract

A flight control actuation system comprises a controller, electromechanical actuator and a pneumatic actuator. During normal operation, only the electromechanical actuator is needed to operate a flight control surface. When the electromechanical actuator load level exceeds 40 amps positive, the controller activates the pneumatic actuator to offset electromechanical actuator loads to assist the manipulation of flight control surfaces. The assistance from the pneumatic load assist actuator enables the use of an electromechanical actuator that is smaller in size and mass, requires less power, needs less cooling processes, achieves high output forces and adapts to electrical current variations. The flight control actuation system is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially flight vehicles that are large in size and travel at high velocities.

Claims

1. A flight control actuation system for use in a flight control system comprising:

a controller operable in response to an input for generating a control signal;

an electromechanical actuator responsive to the control signal, for operating a flight control surface; and

a pneumatic actuator for assisting the electromechanical actuator by reducing the load on the electromechanical actuator.

2. The flight control actuation system of claim 1, wherein the electromechanical actuator and the pneumatic actuator are attached to the same flight control surface.

3. The flight control actuation system of claim 2, wherein the flight control surface comprises at least one aileron.

4. The flight control actuation system of claim 2, wherein the flight control surface comprises at least one flaperon.

5. The flight control actuation system of claim 2, wherein the flight control surface comprises at least one elevator.

6. The flight control actuation system of claim 2, wherein the flight control surface comprises at least one spoiler.

7. The flight control actuation system of claim 2, wherein the flight control surface comprises at least one rudder.

8. The flight control actuation system of claim 1, comprising at least one pressure vessel for supplying gas to the pneumatic actuator.

9. The flight control actuation system of claim 1, comprising at least one vent solenoid valve connected to the pneumatic actuator.

10. The flight control actuation system of claim 1, comprising at least one pressurization solenoid valve connected to the pneumatic actuator.

11. The flight control actuation system of claim 9, comprising at least one pressurization solenoid valve connected to the pneumatic actuator and connected to the vent solenoid valve.

12. A flight control actuation system for use in a flight control system comprising:

a controller operable in response to an input for generating a control signal;

an electromechanical actuator responsive to the control signal, for operating a flight control surface;

a pneumatic actuator for assisting the electromechanical actuator by reducing the load on the electromechanical actuator;

wherein the pneumatic actuator initializes when the electrical current in the electromechanical actuator exceeds a predetermined amperage.

13. The flight control actuation system of claim 12, comprising at least one vent solenoid valve and at least one pressurization solenoid valve connected to the pneumatic actuator.

14. The flight control actuation system of claim 13, wherein the controller closes the pressurization solenoid valve when the electrical current decreases below the predetermined amperage.

15. The flight control actuation system of claim 12, wherein the predetermined amperage in the electromechanical actuator is 40 amps positive.

16. The flight control actuation system of claim 13, wherein the predetermined amperage in the electromechanical actuator is 40 amps positive.

17. The flight control actuation system of claim 13, wherein the controller opens the vent solenoid valve when the electrical current decreases below 10 amps negative.

18. A flight control actuation system for use in a flight control system comprising:

at least one aerodynamic flight control surface;

an electromechanical actuator system adapted to act on each aerodynamic flight control surface;

a pneumatic actuator system adapted to produce a force to act on at least one of the aerodynamic flight control surfaces;

at least one electromechanical actuator associated with a distinct one of the at least one aerodynamic flight control surfaces;

a controller adapted to produce an electrical signal for controlling at least one of the aerodynamic flight control surfaces;

an electrical circuit connected to the at least one electromechanical actuator with at least one electromechanical actuator adapted to receive the electrical signal;

the pneumatic actuator system solely associated with the at least one electromechanical actuator;

the pneumatic actuator system comprising;

a piston;

a pressure vessel;

a vent solenoid valve;

a pressurization solenoid valve; and

a pressure switch;

the vent solenoid valve and pressurization solenoid valve adapted to receive the electrical signal to route a pneumatic pressure;

an actuation device adapted to receive the pneumatic pressure and produce a pneumatic force; and

the actuation device being adapted to continuously actuate the distinct one of the aerodynamic flight control surfaces of a flight vehicle in response to the pneumatic force.

19. The flight control actuation system of claim 18, wherein a control surface position sensor detects position information from the aerodynamic flight control surface and sends the information to the controller.

20. The flight control actuation system of claim 18, wherein an electromechanical actuator position sensor detects position information from the electromechanical actuator and sends the information to the controller.

21. The flight control actuation system of claim 18, wherein the stroke length of the electromechanical actuator is substantially the same as the stroke length of the pneumatic actuator stroke length.

22. The flight control actuation system of claim 18, wherein the electromechanical actuator comprises a piezoelectric crystal.

23. A method for operating a flight control actuation system, the system being adapted to activate at least one pneumatic load assist actuator in response to at least one signal produced by a control surface actuation signal system for positioning at least one control surface, the method comprising the steps of:

receiving an input signal in the form of a position demand providing an instruction for deflecting a control surface to a new position;

generating a corresponding control signal for operating an electromechanical actuator;

receiving a feedback signal in the form of an electrical current measurement at the electromechanical actuator;

comparing the electrical current measurement to a predetermined electrical current value; and

,

generating a corresponding control signal for operating a pneumatic actuator for reducing the load on the electromechanical actuator.

24. The method of claim 23, comprising a further step wherein the pneumatic actuator vents and relieves force when the electromechanical actuator tension load increases.

25. The method of claim 23, wherein the electromechanical actuator and the pneumatic actuator are attached to the same flight control surface.

26. A method for operating a flight control actuation system comprising the steps of:

operating a flight vehicle;

receiving a flight control surface position demand instruction;

comparing the position demand with output from a control surface position sensor;

generating an actuator position demand to at least one electromechanical actuator;

monitoring the electromechanical actuator electrical current load;

comparing the electrical current load with a predetermined electrical current load limit;

closing at least one vent solenoid valve;

opening at least one pressurization solenoid valve whenever the electromechanical actuator current is more than the predetermined electrical current load limit; and

closing a pressurization solenoid valve whenever the electromechanical actuator electrical current load decreases below the predetermined electrical current load limit.

27. The method of claim 26, further comprising the step of:

opening at least one vent solenoid valve whenever the electromechanical actuator current is negative.

28. The method of claim 26, further comprising the step of:

closing at least one exhaust valve whenever the electromechanical actuator current is positive.

29. The method of claim 26, further comprising the step of:

opening at least one exhaust valve and closing at least one pressurization solenoid valve during a failure condition.

30. The method of claim 26, further comprising the step of generating a pneumatic load assistance requirement instruction to at least one pneumatic load assistance device, for manipulating a flight vehicle control surface.

31. The method of claim 26, wherein the flight vehicle is an aircraft.

32. The method of claim 26, wherein the flight vehicle is a spacecraft.

33. The method of claim 26, wherein the flight vehicle is a missile.