Helicopter in-flight rotor tracking system, method, and smart actuator therefor

• US 6,322,324 B1
• Filed: 03/03/2000
• Issued: 11/27/2001
• Est. Priority Date: 03/03/2000
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Hassan, Ahmed A., Kennedy, Dennis K., Straub, Friedrich K.
• Primary Examiner(s): Ryznic, John E.
• Application Number:
  US09/518,839
• Time in Patent Office: 634 Days
• Field of Search: 416/1, 416/19, 416/23, 416/33, 416/500, 244/17.13, 244/17.23, 244/17.25, 244/17.27
• US Class Current: 416/1
• CPC Class Codes: B64C 2027/7266 actuated by actuators
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: B64C 27/008 Rotors tracking or balancing devices
• CPC Class Codes: Y02T 50/30 Wing lift efficiency
• CPC Class Codes: Y10S 416/50 Vibration damping features

Abstract

A system for quasi-statically correcting tracking of rotor blades of a helicopter rotor during operation includes a trim tab mounted on each rotor blade and deflectable relative to the rotor blade so as to change a tracking path of the rotor blade, and a rotor track and balance analyzer that includes sensors for acquiring rotor tracking and balance information and is operable to process the rotor tracking and balance information so as to predetermine a new tab position to which the trim tab should be deflected for bringing the tracking path of a mistracking rotor blade into alignment with a reference path. The trim tab is deflected by an actuator mounted to the rotor blade, the actuator having an actuating element coupled with the trim tab and formed of a smart material such that the actuating element deforms proportional to a stimulus applied to the actuating element. An electrical locking device is included which is operable when de-energized to lock the trim tab against deflection, and operable when energized to unlock to permit the trim tab to be deflected. A trim actuation control system in communication with the rotor track and balance analyzer and the locking device is arranged to energize the locking device and to supply electrical power to the actuator so as to deflect the trim tab to the new tab position predetermined in the rotor track and balance analyzer, and to then de-energize the locking device and cut off the electrical power to the actuator. Thus, electrical power is supplied to the actuator only while the trim tab is being deflected, and is then discontinued once the tab has reached the desired position and the locking device has been de-energized to lock the tab against further movement.

Claims

1. A system for quasi-statically correcting tracking of a rotor blade of a helicopter rotor during operation, comprising:

a trim tab mounted on the rotor blade and deflectable relative to the rotor blade so as to change a tracking path of the rotor blade;

a rotor track and balance analyzer that includes sensors for acquiring rotor tracking and balance information and is operable to process said rotor tracking and balance information so as to predetermine a new tab position to which the trim tab should be deflected for bringing the tracking path of the rotor blade into alignment with a reference path;

an actuator mounted to the rotor blade, the actuator having an actuating element coupled with the trim tab and formed of a smart material such that the actuating element deforms proportional to a stimulus applied to the actuating element, the actuator further including stimulus means for applying a stimulus to the actuating element upon supplying electrical power to said stimulus means, whereby the actuator deflects the trim tab when electrical power is supplied to the actuator;

an electrical locking device operable when de-energized to lock the trim tab against deflection, and operable when energized to unlock to permit the trim tab to be deflected; and

a trim actuation control system in communication with the rotor track and balance analyzer and the locking device, the trim actuation control system being arranged to energize the locking device and to supply electrical power to the actuator so as to deflect the trim tab to the new tab position predetermined in the rotor track and balance analyzer, and to then de-energize the locking device and cut off the electrical power to the actuator, the locking device fixing the trim tab in the new tab position.

2. The system of claim 1, further comprising a position sensor for monitoring position of the trim tab, and a stimulus sensor for monitoring the stimulus applied to the actuating element, and wherein the trim actuation control system includes a position control unit arranged to receive signals from the position sensor and stimulus sensor, the position control unit being operable to regulate the stimulus applied to the actuating element such that the trim tab is deflected to the new tab position.

3. The system of claim 2, wherein the actuating element comprises a shape memory alloy that deforms upon heating, the stimulus means comprising a heating means for causing heating of the actuating element, and the stimulus sensor comprising a temperature sensor for monitoring a temperature of the actuating element.

4. The system of claim 3, wherein the actuator includes two actuating elements of shape memory alloy, the actuating elements each being coupled to the trim tab and being arranged to deflect the trim tab in opposite directions.

5. The system of claim 4, wherein each of the actuating elements includes an independently controllable heating means associated therewith.

6. The system of claim 2, wherein the trim actuation control system includes a trim actuation controller located in non-rotating structure of the helicopter, and wherein the position control unit is mounted to the rotor blade and is electrically connected to the trim actuation controller by a rotating electrical interface and a conductor leading from the interface along the rotor blade to the position control unit, whereby the trim actuation controller transmits the new tab position through the interface and conductor to the position control unit, and the position control unit then operates in a feedback mode to drive the position of the trim tab to the new tab position.

7. The system of claim 1, wherein the sensors of the rotor track and balance analyzer include a blade path sensor for detecting a position of the tracking path of the rotor blade relative to said reference path.

8. The system of claim 7, wherein the helicopter rotor includes a plurality of rotor blades each having the trim tab and actuator, one of the rotor blades comprising a master blade whose tracking path defines the reference path, and wherein the sensors of the rotor track and balance analyzer include a rotor azimuth sensor for detecting an azimuth position of the rotor, the rotor track and balance analyzer synchronously processing signals provided by the blade path sensor and rotor azimuth sensor so as to identify which of the rotor blades is mistracking.

9. The system of claim 8, wherein each actuator defines a unique electrical address and the trim actuation control system is operable to transmit the new tab position to any selected one of the electrical addresses for independently controlling tracking of each rotor blade.

10. The system of claim 1, wherein the sensors of the rotor track and balance analyzer include at least one vibration sensor arranged for detecting rotor vibration and operable to provide vibration data in the form of signals indicative of a magnitude of the rotor vibration, and at least one tracking sensor for detecting mistracking of the rotor blade and operable to provide tracking data in the form of signals indicative of deviation of the tracking path from said reference path, the rotor track and balance analyzer being operable to deduce, based on the vibration data and tracking data, components of the rotor vibration caused by inertial unbalance and by aerodynamic unbalance.

11. The system of claim 10, further comprising a data recording device operable to record the vibration data and the tracking data.

12. The system of claim 11, further comprising a pilot interface operatively coupled to the trim actuation control system, the pilot interface including a display for displaying information to a crew member and switches activatable by the crew member for initiating functions of the trim actuation control system.

13. The system of claim 12, wherein the trim actuation control system is operable in response to activation of one of the switches on the pilot interface to operate in an automatic mode wherein the trim actuation control system periodically analyzes the vibration and tracking data stored in the data recording device to determine whether the magnitude of the rotor vibration has exceeded a predetermined threshold, and automatically initiates a tracking correction procedure upon determining that the predetermined threshold has been exceeded.

14. The system of claim 13, wherein the trim actuation control system is operable in response to another of the switches on the pilot interface to operate in a pilot-in-the-loop mode wherein the crew member operates the pilot interface to command the trim actuation control system to cause the rotor track and balance analyzer to analyze the tracking of the rotor blade, and the trim actuation control system is operable to cause the tracking and vibration data to be displayed on the display of the pilot interface.

15. The system of claim 14, wherein the trim actuation control system in the pilot-in-the-loop mode is operable to initiate a tracking correction procedure only upon receiving a command from the pilot interface.

16. A system for acquiring and recording tracking and vibration data for a helicopter rotor and for correcting tracking of a rotor blade of the rotor during operation, comprising:

a trim tab mounted on the rotor blade and deflectable relative to the rotor blade so as to change a tracking path of the rotor blade;

a rotor track and balance analyzer that includes sensors for acquiring rotor tracking and balance information, said sensors including at least one tracking sensor for detecting mistracking of the rotor blade and operable to provide tracking data in the form of signals indicative of deviation of a tracking path of the rotor blade from a reference path, and at least one vibration sensor arranged for detecting rotor vibration and operable to provide vibration data in the form of signals indicative of a magnitude of the rotor vibration, the rotor track and balance analyzer being operable to process said rotor tracking and balance information so as to predetermine a new tab position to which the trim tab should be deflected for bringing the tracking path of the rotor blade into alignment with said reference path;

an actuator mounted to the rotor blade, the actuator having an actuating element coupled with the trim tab and formed of a smart material such that the actuating element deforms proportional to a stimulus applied to the actuating element, the actuator further including stimulus means for applying a stimulus to the actuating element upon supplying electrical power to said stimulus means, whereby the actuator deflects the trim tab when electrical power is supplied to the actuator;

a trim actuation control system in communication with the rotor track and balance analyzer, the trim actuation control system being arranged to supply electrical power to the actuator so as to deflect the trim tab to the new tab position determined in the rotor track and balance analyzer; and

a data recording device operable to record the vibration data and the tracking data for later analysis.

17. The system of claim 16, further comprising a pilot interface operatively coupled to the trim actuation control system, the pilot interface including a display for displaying information to a crew member and switches activatable by the crew member for initiating functions of the trim actuation control system.

18. The system of claim 17, wherein the trim actuation control system is operable in response to activation of one of the switches on the pilot interface to operate in an automatic mode wherein the trim actuation control system periodically analyzes the vibration and tracking data stored in the data recording device to determine whether the magnitude of the rotor vibration has exceeded a predetermined threshold, and automatically initiates a tracking correction procedure upon determining that the predetermined threshold has been exceeded.

19. The system of claim 18, wherein the trim actuation control system is operable in response to another of the switches on the pilot interface to operate in a pilot-in-the-loop mode wherein the crew member operates the pilot interface to command the trim actuation control system to cause the rotor track and balance analyzer to analyze the tracking of the rotor blade, and the trim actuation control system is operable to cause the tracking and vibration data to be displayed on the display of the pilot interface.

20. The system of claim 19, wherein the trim actuation control system in the pilot-in-the-loop mode is operable to initiate a tracking correction procedure only upon receiving a command from the pilot interface.

21. A system for quasi-statically correcting tracking of a rotor blade of a helicopter rotor during operation, comprising:

a trim tab on the rotor blade and pivotally deflectable relative to the rotor blade so as to change a tracking path of the rotor blade;

a linkage coupled with the trim tab and movable so as to pivotally deflect the trim tab;

an actuator mounted to the rotor blade, the actuator having an actuating element coupled with the linkage and formed of a smart material such that the actuating element deforms proportional to a stimulus applied to the actuating element, the actuator further including stimulus means for applying a stimulus to the actuating element upon supplying electrical power to said stimulus means, whereby the actuator moves the linkage so as to pivotally deflect the trim tab when electrical power is supplied to the actuator;

a trim actuation control system arranged to supply electrical power to the actuator so as to deflect the trim tab toward a predetermined new tab position for correcting the tracking of the rotor blade;

a position sensor for monitoring position of the trim tab;

a stimulus sensor for monitoring the stimulus applied to the actuating element; and

a position control unit associated with the trim actuation control system and arranged to receive signals from the position sensor and stimulus sensor, the position control unit being operable to regulate the stimulus applied to the actuating element such that the trim tab is deflected to the new tab position.

22. The system of claim 21, wherein the actuating element comprises a shape memory alloy that deforms upon heating, the stimulus means comprising a heating means for causing heating of the actuating element, and the stimulus sensor comprising a temperature sensor for monitoring a temperature of the actuating element.

23. The system of claim 22, wherein the actuator includes two actuating elements of shape memory alloy, the actuating elements each being coupled to the linkage and being arranged to deflect the trim tab in opposite directions.

24. The system of claim 23, wherein each of the actuating elements includes an independently controllable heating means and a separate temperature sensor associated therewith.

25. The system of claim 21, wherein the trim actuation control system includes a trim actuation controller located in non-rotating structure of the helicopter, and wherein the position control unit is mounted to the rotor blade and is electrically connected to the trim actuation controller by a rotating electrical interface and a conductor leading from the interface along the rotor blade to the position control unit, whereby the trim actuation controller transmits the new tab position through the interface and conductor to the position control unit, and the position control unit then operates in a feedback mode to drive the position of the trim tab to the new tab position.

26. The system of claim 21, further comprising an electrical locking device operable when de-energized to lock the trim tab against deflection, and operable when energized to unlock to permit the trim tab to be deflected, and wherein the position control unit is operable to energize the locking device when the trim tab is deflected to the new position and to de-energize the locking device to lock the trim tab in the new position.

27. The system of claim 21, wherein the actuator is disposed internally within the rotor blade.

28. A method for quasi-statically correcting tracking of a rotor blade of a helicopter rotor during operation so as to reduce rotor vibration caused by mistracking of the rotor blade, comprising:

providing a trim tab on the rotor blade, the trim tab being deflectable relative to the rotor blade for altering a tracking path of the rotor blade;

providing an actuator on the rotor blade and coupled with the trim tab for deflecting the trim tab, the actuator incorporating an electrically activatable smart material such that the actuator is activated to deflect the trim tab when electrical power is supplied to the actuator;

determining a degree of mistracking of the rotor blade relative to a reference;

measuring a level of vibration induced by unbalance of the rotor;

predetermining, based on the degree of mistracking and the level of vibration, a new tab position to which the trim tab should be deflected for bringing the tracking path of the rotor blade into alignment with a reference path;

communicating the predetermined new tab position to a position control unit located adjacent the actuator on the rotor blade, the position control unit being operable to regulate electrical power supplied to the actuator via a position feedback loop so as to cause the actuator to deflect the trim tab to the predetermined new tab position; and

supplying electrical power to the actuator through the position control unit such that the position control unit controls the actuator to deflect the trim tab to the predetermined new tab position, whereby position feedback control of the trim tab position is performed locally on the rotor blade.

29. The method of claim 28, further comprising operating a locking device located on the rotor blade so as to fix the trim tab against further deflection once the trim tab reaches the predetermined new tab position, and discontinuing electrical power to the actuator once the locking device has been operated to fix the trim tab.

30. A method for acquiring and recording tracking and vibration data for a helicopter rotor and for correcting tracking of a rotor blade of the rotor during operation, comprising:

providing a trim tab on the rotor blade, the trim tab being deflectable relative to the rotor blade for altering a tracking path of the rotor blade;

providing an actuator on the rotor blade and coupled with the trim tab for deflecting the trim tab, the actuator incorporating an electrically activatable element operable to deflect the trim tab when electrical power is supplied to the actuator;

periodically acquiring tracking data from at least one tracking sensor operable to measure a degree of mistracking of the rotor blade relative to a reference;

periodically acquiring vibration data from at least one vibration sensor mounted adjacent the rotor and operable to measure a level of vibration induced by unbalance of the rotor;

storing the tracking data and vibration data in a data recording device located in the helicopter;

periodically analyzing the stored data to determine whether the level of vibration indicated by the vibration data exceeds a predetermined threshold;

upon determining that the level of vibration exceeds the predetermined threshold, initiating a tracking analysis procedure wherein the stored tracking and vibration data are analyzed to predetermine a new tab position to which the trim tab should be deflected for correcting the mistracking of the rotor blade and for reducing an aerodynamically induced component of the vibration; and

operating the actuator to deflect the trim tab to the predetermined new tab position.