Method and control arrangement for adjusting a flap that is pivotally supported in a rotor blade of a helicopter

• US 6,648,599 B2
• Filed: 04/01/2002
• Issued: 11/18/2003
• Est. Priority Date: 04/03/2001
• Status: Expired due to Fees

• Current Assignee: Airbus Helicopters Deutschland Gmbh (Airbus SE)
• Original Assignee: Eurocopter Deutschland Gesellschaft Mit Beschrã¤Nkter Haftung (European Aeronautic Defence and Space Company EADS NV)
• Inventors: Preissler, Dieter
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): McAleenan, J. M.
• Application Number:
  US10/114,168
• Publication Number:
  US 20020141867A1
• Time in Patent Office: 596 Days
• Field of Search: 416/1, 416/23, 416/24, 244/21.S, 244/75.R, 244/213, 244/214, 244/216, 244/217, 310/330, 310/328, 310/331, 605/28, 605/29
• US Class Current: 416/1
• CPC Class Codes: B64C 2027/7283 of the piezoelectric type
• CPC Class Codes: B64C 27/615 including flaps mounted on blades
• CPC Class Codes: Y02T 50/30 Wing lift efficiency

Abstract

A force transmitting linkage connects a piezoelectric actuator to a flap that is pivotably connected to a helicopter rotor blade. In a flap actuation control arrangement and method, a force transducer senses the force being transmitted through the linkage and generates a corresponding actual force signal, a flap position sensor senses the position of the flap and generates a corresponding actual flap position signal, a first controller receives a desired flap position signal and the actual flap position signal and responsively thereto generates a reference signal, and a second controller receives the reference signal and the actual force signal and responsively thereto generates a control signal that is provided to the piezoelectric actuator. This provides a real time flap actuation control with respect to highly dynamic forces as well as friction forces acting on the flap.

Claims

1. In a helicopter rotor blade arrangement including a rotor blade body, a flap that is pivotable relative to said rotor blade body, a piezoelectric actuator, a force transmitting linkage connected from an actuator output of said piezoelectric actuator to said flap, and a control arrangement that is connected and provides a control signal to a control input of said piezoelectric actuator,

an improvement in said control arrangement comprising:

a primary control with a primary feedback input and a primary control output;

a flap position sensor that is arranged to sense an actual position of said flap, and that has a position sensor output which is connected to said primary feedback input and which is adapted to provide a flap position signal responsive and corresponding to said actual position of said flap;

a secondary control with a secondary reference input, a secondary feedback input and a secondary control output, wherein said secondary control output is connected and provides said control signal to said control input of said piezoelectric actuator, and wherein said primary control output is connected to said secondary reference input; and

a measuring element that is coupled with said force transmitting linkage and that has a measuring element output which is connected to said secondary feedback input.

2. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 1, wherein said primary control further has an external control input, and further comprising an external controller having an external controller output connected to said external control input.

3. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 2, wherein said primary control comprises a nominal flap position value transducer that has said external control input which is connected to said external controller output of said external controller.

4. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 3, wherein said primary control further comprises a primary controller amplifier having said primary control output, said primary feedback input as an inverting input thereof, and a non-inverting input that is connected to an output of said nominal flap position value transducer.

5. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 2, wherein said external controller has a first external signal input, and further comprising an external vibration or sound sensor connected to said first external signal input.

6. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 5, wherein said external controller further has a second external signal input, and further comprising a flight control device that is connected and provides pilot flight control command signals to said second external signal input.

7. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 2, wherein said external controller contains programed algorithms or circuitry for reduction of blade-vortex-interactions (BVI), for reduction of vibrations of the helicopter, or for reduction of airflow resistance of the rotor blade arrangement.

8. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 1, wherein said secondary control comprises a secondary controller servo amplifier having said secondary reference input as a non-inverting input thereof, said secondary feedback input as an inverting input thereof, and said secondary control output.

9. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 1, wherein said measuring element is a force measuring element that is coupled with said force transmitting linkage so as to measure a force being transmitted through said force transmitting linkage.

10. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 9, wherein said force measuring element is a strain gage.

11. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 10, wherein said force transmitting linkage comprises a mechanical link member interposed and connected between said actuator output of said piezoelectric actuator and said flap, and said strain gage is arranged on said mechanical link member.

12. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 9, wherein said secondary control adjusts said control signal provided at said secondary control output responsive to and dependent on said force being transmitted through said force transmitting linkage.

13. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 12, wherein said primary control provides and adjusts a primary reference signal at said primary control output to said secondary reference input of said secondary control responsive to and dependent on said flap position signal, and said secondary control further adjusts said control signal provided at said secondary control output responsive to and dependent on said primary reference signal.

14. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 1, wherein said flap position sensor comprises a flap angle sensor coupled to said flap so as to sense an actual flap angle of said flap as said actual position of said flap.

15. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 14, wherein said flap angle sensor comprises two electrical coils fixedly mounted with respect to said rotor blade body, and a metal vane that is fixed to said flap and movably arranged between said two electrical coils.

16. The improvement in the control arrangement in the helicopter rotor blade arrangement according to claim 1, wherein said flap position sensor comprises a position sensor arranged and adapted to sense a position of said force transmitting linkage connected to said flap.

17. In a helicopter rotor blade arrangement including a rotor blade body, a flap that is pivotable relative to said rotor blade body, a piezoelectric actuator, a mechanical link member that is connected and transmits an actuating force between an actuator output of said piezoelectric actuator and said flap, and a control arrangement that is connected and provides a control signal to a control input of said piezoelectric actuator,

an improvement in said control arrangement comprising:

a servo amplifier having a feedback input and having a control output that is connected and provides said control signal to said control input of said piezoelectric actuator; and

a strain gage that is arranged on said mechanical link member and that has a force signal output connected to said feedback input of said servo amplifier.

18. A method of actuating a pivotable flap that is pivotally connected to a helicopter rotor blade, using a piezoelectric actuator connected to said flap by a force transmitting linkage, comprising the following steps:

a) operating said piezoelectric actuator to transmit an actuating force through said force transmitting linkage to said flap so as to pivot said flap relative to said rotor blade;

b) sensing an actual position of said flap relative to said blade and generating an actual flap position signal corresponding to said actual position of said flap;

c) sensing an actual force value of said actuating force being transmitted through said force transmitting linkage and generating an actuating force signal corresponding to said actual force value;

d) forming an actuator control signal responsive to and dependent on said actual flap position signal and said actuating force signal; and

e) controlling said operating of said piezoelectric actuator by providing said actuator control signal to said piezoelectric actuator.

19. The method according to claim 18, wherein said step of forming said actuator control signal comprises applying said actual flap position signal to a feedback input of a first stage control amplifier, generating a first stage output signal in said first stage control amplifier responsive to and dependent on said actual flap position signal, applying said first stage output signal to a reference input of a second stage control amplifier, applying said actuating force signal to a feedback input of said second stage control amplifier, and generating said actuator control signal in said second stage control amplifier responsive to and dependent on said first stage output signal and said actuating force signal.

20. The method according to claim 19, wherein said step of forming said actuator control signal further comprises generating a nominal rated flap position in an external controller, and applying said nominal rated flap position as a nominal rated flap position signal through a nominal value transducer to a reference input of said first stage control amplifier, and wherein said step of generating said first stage output signal in said first stage control amplifier is carried out responsive to and dependent on said actual flap position signal and said nominal rated flap position signal.

21. The method according to claim 20, further comprising sensing vibration or sound and generating a corresponding vibration or sound signal, and providing said vibration or sound signal to said external controller, and wherein said generating of said nominal rated flap position is carried out in said external controller responsive to and dependent on said vibration or sound signal.

22. The method according to claim 18, further comprising arranging a force measuring transducer on said force transmitting linkage, and wherein said step c) is carried out by said force measuring transducer.