DIRECTIONAL CONTROL ARRANGEMENT TO PROVIDE STABILIZING FEEDBACK TO A STRUCTURAL BENDING MODE

• US 20090283628A1
• Filed: 05/19/2008
• Published: 11/19/2009
• Est. Priority Date: 05/19/2008
• Status: Abandoned Application

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Frederickson, Kirk C.
• Application Number:
  US12/123,420
• Publication Number:
  US 20090283628A1
• Time in Patent Office: Days
• US Class Current: 244/17.210
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: B64C 27/04 Helicopters
• CPC Class Codes: B64C 27/57 automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
• CPC Class Codes: B64C 27/59 mechanical
• CPC Class Codes: B64C 27/82 characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 74/20402 Flexible transmitter [e.g., Bowden cable]

Abstract

A control system and method of producing a stabilizing feedback includes generating a control output with a link in response to a deflection of a structure, the control output operable to at least partially resist the deflection.

Claims

1. A control system comprising:

a control; and

a link connected to said control, said link oriented to generate a control output in said control in response to a deflection, said control output operable to at least partially resist said deflection.

2. The system as recited in claim 1, wherein said control comprises a flight control.

3. The system as recited in claim 1, wherein said link comprises a flexible cable.

4. The system as recited in claim 1, wherein said control is a tail rotor.

5. The system as recited in claim 4, wherein said link comprises a flexible cable.

6. The system as recited in claim 1, further comprising an input, said input connected to said control through said link to operate said control.

7. The system as recited in claim 6, wherein said input comprises a pedal system.

8. A rotary wing aircraft comprising:

an airframe comprising an extended tail;

an tail rotor system mounted to said extended tail;

an input; and

a link which connects said input to said tail rotor system, said link oriented to generate a pitch output in said tail rotor system in response to a deflection of said extended tail, said pitch output operable to at least partially resist said deflection.

9. The aircraft as recited in claim 8, wherein said link comprises a flexible cable.

10. The aircraft as recited in claim 9, wherein said input comprises a pedal system

11. The aircraft as recited in claim 10, wherein said link is connected to said pedal system through a mixing unit.

12. The aircraft as recited in claim 11, wherein said mixing unit positions a forward control quadrant connected to a first end section of said flexible cable, said forward control quadrant mounted for rotational motion about an axis of rotation.

13. The aircraft as recited in claim 12, further comprising an aft control quadrant connected to a second end section of said flexible cable, said aft control quadrant mounted for rotational motion about an axis of rotation, said aft control quadrant rotates in response to said forward control quadrant.

14. The aircraft as recited in claim 13, further comprising a servo which operates said tail rotor system, said aft control quadrant operable to command said servo.

15. A method of producing a stabilizing feedback comprising:

orienting a link within a structure; and

generating a control output with the link in response to a deflection of the structure, the control output operable to at least partially resist the deflection.

16. A method as recited in claim 15, wherein orienting the link comprises:

orienting the link off of a neutral axis of the structure.

17. A method as recited in claim 15, wherein orienting the link comprises:

orienting a flexible cable within an extended tail of a rotary wing aircraft.

18. A method as recited in claim 15, wherein generating the control output comprises:

generating a yaw force opposite the deflection of the structure.

19. A method as recited in claim 15, wherein generating the control output comprises:

transmitting a pitch command to a tail rotor through the link.