Flight control actuation system

• US 7,007,897 B2
• Filed: 06/22/2004
• Issued: 03/07/2006
• Est. Priority Date: 04/07/2003
• Status: Expired due to Fees

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Kern, James I., Gaines, Louie T., Wingett, Paul T., Evans, Paul S.
• Primary Examiner(s): Swiatek, Robert P.
• Application Number:
  US10/874,729
• Publication Number:
  US 20050127241A1
• Time in Patent Office: 623 Days
• Field of Search: 244/75.R, 244/76.A, 244/78, 244/82, 244/227, 244/228, 244/229
• US Class Current: 244/227
• 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:

an electromechanical actuator responsive to a control signal, for operating a flight control surface, the electromechanical actuator operable to supply a load signal representative of a load thereon;

a pneumatic supply module responsive to a load assist signal for selectively supplying a flow of pressurized gas;

a pneumatic actuator responsive to the flow pressurized gas for assisting the electromechanical actuator, to thereby reduce the load on the electromechanical actuator; and

a controller coupled to receive an input signal and the load signal and operable, in response thereto, to (i) supply the control signal to the electromechanical actuator, (ii) determine the load on the electromechanical actuator, and (iii) supply the load assist signal if the load on the electromechanical actuator exceeds a predetermined value.

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 9, comprising at least one pressurization solenoid valve connected to the pneumatic actuator and connected to the at least one vent solenoid valve.

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

12. The flight control actuation system of claim 1, wherein the flight control surface comprises at least one element selected from the group:

an aileron, a wing flap, a body flap, a slat, a flaperon, an elevator, a spoiler, and a rudder.

13. 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 surface;

a controller adapted to produce a first electrical signal and, if a load on the at least one electromechanical actuator exceeds a predetermined value, a second electrical signal;

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 second 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.

14. The flight control actuation system of claim 13, wherein a control surface position sensor detects position information from the at least one aerodynamic flight control surface and sends the information to the controller.

15. The flight control actuation system of claim 13, wherein an electromechanical actuator position sensor detects position information from the electromechanical actuator and sends the information to the controller.

16. The flight control actuation system of claim 13, wherein the stroke length of the electromechanical actuator is substantially the same as the stroke length of the pneumatic actuator stroke length.

17. The flight control actuation system of claim 13, wherein the electromechanical actuator comprises a piezoelectric crystal.

18. A flight control actuation system, comprising:

a flight control surface for controlling flight of a flight vehicle;

an electromechanical actuator, responsive to a control signal, and adapted for controlling a position of said flight control surface;

a pneumatic actuator also adapted for controlling the position of said flight control surface;

a pneumatic supply module in communication with said pneumatic actuator and responsive to a load assist signal to selectively supply pressurized gas to the pneumatic actuator; and

a controller coupled to receive an input signal and a load signal representative of a load on the electromechanical actuator and operable, in response thereto, to (i) supply the control signal to the electromechanical actuator, (ii) determine the load on the electromechanical actuator, and (iii) supply the load assist signal if the load on the electromechanical actuator exceeds a predetermined value.

19. The flight control actuation system of claim 18, wherein said controller is adapted for receiving a flight control surface position demand and for generating an actuator position demand for controlling said electromechanical actuator in response to said flight control surface position demand.

20. The flight control actuation system of claim 19, wherein said flight control surface position demand is generated by at least one of:

a pilot, a computer, and a remote control device.

21. The flight control actuation system of claim 18, wherein said controller is adapted for receiving feedback signals indicative of movement of said flight control surface.

22. The flight control actuation system of claim 18, further comprising a control surface position sensor in communication with said controller for indicating the position of said flight control surface.

23. The flight control actuation system of claim 18, further comprising an electromechanical actuator position sensor in communication with said controller for indicating a linear stroke position of said electromechanical actuator.

24. The flight control actuation system of claim 18, wherein said controller generates an actuator position demand signal representing a stroke position for the electromechanical actuator in response to input from a control surface position sensor or an electromechanical actuator position sensor.

25. The flight control actuation system of claim 18, wherein said electromechanical actuator includes a shaft, and the position of said flight control surface is adjusted by extending or retracting said shaft thereby exerting a force on said flight control surface.

26. The flight control actuation system of claim 18, wherein said pneumatic actuator and said electromechanical actuator are adapted to provide a combined force sufficient for controlling the position of said flight control surface.

27. The flight control actuation system of claim 18, wherein said flight control surface comprises at least one element selected from the group:

an aileron, a wing flap, a body flap, a slat, a flaperon, an elevator, a spoiler, and a rudder.

28. The flight control actuation system of claim 18, wherein said pneumatic supply module comprises:

a pressure vessel for storing a pressurized gas;

a manifold coupled to said pressure vessel for directing flow of said pressurized gas from said pressure vessel;

at least one pressurization valve in communication with said pressure vessel for controlling flow of said pressurized gas to said pneumatic actuator; and

at least one vent valve for controlling venting of said pressurized gas from said pneumatic actuator.