SYSTEM, METHOD AND APPARATUS FOR CONTROL SURFACE WITH DYNAMIC COMPENSATION

• US 20090302516A1
• Filed: 06/05/2008
• Published: 12/10/2009
• Est. Priority Date: 06/05/2008
• Status: Abandoned Application

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Steele, Jean P.
• Application Number:
  US12/133,822
• Publication Number:
  US 20090302516A1
• Time in Patent Office: Days
• US Class Current: 267/140.150
• CPC Class Codes: B64C 13/341 having duplication or stand-by provisions
• 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: B64C 13/507 with artificial feel
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

An aircraft flight control surface has an actuator that employs a magneto-rheological (MR) fluid for dynamically adjusting the responsiveness of the control surface. The MR fluid may be used as a primary or secondary control in the event that a primary control actuator fails. In the event of system failures associated with the primary control, an alternate level of performance may be provided by the secondary control and communicated to the overall flight control system. This permits the control surface actuator to reactively and proactively respond to changes associated with the flight control system. If the design fails, it also permits a safe mode of operation should the ability to dynamically adjust the viscosity of the MR fluid be negatively impacted. The safe mode of operation may involve a reduced level of performance.

Claims

1. A system for controlling and manipulating a flight control device on an aircraft, comprising:

an aircraft having a body;

a flight control device movably mounted to the body for adjusting flight of the aircraft;

a sensor mounted to the body for detecting a movement of the flight control device;

a primary manipulation device for primarily manipulating the flight control device during operation of the aircraft; and

a secondary manipulation device coupled to the flight control device and the primary manipulation device, the secondary manipulation device being responsive to the sensor for manipulating the flight control device when inadequate manipulation of the flight control device is provided by the primary manipulation device, and the secondary manipulation device acting as a damper for selectively damping motion of the flight control device during flight of the aircraft.

2. A system according to claim 1, wherein the flight control device is selected from the group consisting of a rudder, an aileron, and an elevator.

3. A system according to claim 1, further comprising an aircraft flight control system, wherein the secondary manipulation device is coupled to the aircraft flight control system for responding proactively to planned maneuvers of the flight control device.

4. A system according to claim 1, wherein the secondary manipulation device is used to match maneuver force requirements of the flight control device.

5. A system according to claim 1, wherein the secondary manipulation device comprises an actuator having chambers with a magneto-rheological (MR) fluid, a valve through which the MR fluid passes between the chambers, and a magnetic field generator for generating a magnetic field that selectively and dynamically manipulates a property of the MR fluid as it passes through the valve to adjust a stiffness and responsiveness of the flight control device.

6. A system according to claim 5, wherein the secondary manipulation device is a sealed unit and has no plumbing connections, and a stiffness of the flight control device is controlled at frequencies that are critical for structural dynamics.

7. A system according to claim 5, wherein only a portion of the MR fluid is manipulated locally at and adjacent to the valve, rather than an entire volume of the MR fluid.

8. A system according to claim 5, wherein the property of the MR fluid is viscosity, and is variable and responsive to the magnetic field for providing a range of active and passive mechanical damping.

9. A system according to claim 8, wherein the MR fluid and magnetic field fail to a safe mode if an ability to control viscosity fails.

10. A system according to claim 1, wherein the secondary manipulation device comprises an actuator having chambers with a siliconized fluid, a valve through which the siliconized fluid passes between the chambers to provide active mechanical damping of the flight control device.

11. A system according to claim 1, wherein the sensor measures acceleration of the flight control device to generate a signal to drive damping motion of the secondary manipulation device.

12. A system according to claim 11, further comprising:

filtering and conditioning the signal;

using the filtered and conditioned signal to drive inputs; and

receiving the inputs with a servo amplifier to produce current output to drive a valve coil in the secondary manipulation device.

13. A system for controlling and manipulating a flap on an aircraft, comprising:

an aircraft having a body;

a flap movably mounted to the body for adjusting flight of the aircraft;

a sensor mounted to the body for detecting an acceleration of the flap;

a flap manipulation device coupled to the flap for manipulating the flap during operation of the aircraft, the flap manipulation device also being responsive to the sensor for manipulating the flap and selectively damping motion of the flap during flight of the aircraft; and

the flap manipulation device having an actuator having chambers with a magneto-rheological (MR) fluid, a valve through which the MR fluid passes between the chambers, and a magnetic field generator for generating a magnetic field that selectively and dynamically manipulates a property of the MR fluid as it passes through the valve to adjust a stiffness and responsiveness of the flap.

14. A system according to claim 13, wherein the flap is selected from the group consisting of a rudder, an aileron, and an elevator.

15. A system according to claim 13, further comprising an aircraft flight control system, wherein the flap manipulation device is coupled to the aircraft flight control system for responding proactively to planned maneuvers of the flap.

16. A system according to claim 13, wherein the flap manipulation device is used to match maneuver force requirements of the flap.

17. A system according to claim 13, wherein the flap manipulation device is a sealed unit and has no plumbing connections, and a stiffness of the flap is controlled at frequencies that are critical for structural dynamics.

18. A system according to claim 13, wherein only a portion of the MR fluid is manipulated locally at and adjacent to the valve, rather than an entire volume of the MR fluid.

19. A system according to claim 13, wherein the property of the MR fluid is viscosity, and is variable and responsive to the magnetic field for providing a range of active and passive mechanical damping for the flap.

20. A system according to claim 19, wherein the MR fluid and magnetic field fail to a safe mode if an ability to control viscosity fails.

21. A system according to claim 13, wherein the sensor measures acceleration of the flap to generate a signal to drive damping motion of the flap manipulation device.

22. A system according to claim 21, further comprising:

filtering and conditioning the signal;

using the filtered and conditioned signal to drive inputs; and

receiving the inputs with a servo amplifier to produce current output to drive a valve coil in the flap manipulation device to manipulate the MR fluid.