초록 ▼

There is described herein a real-time scheme, implementable in software, hardware, or a combination thereof, to detect a resonating frequency of a structure from a sensed signal and dynamically set the center frequency of an adaptive compensator for effective attenuation of the resonating frequency.

There is described herein a real-time scheme, implementable in software, hardware, or a combination thereof, to detect a resonating frequency of a structure from a sensed signal and dynamically set the center frequency of an adaptive compensator for effective attenuation of the resonating frequency.

대표청구항 ▼

1. A method for attenuating a frequency from a gas turbine engine system comprising a helicopter rotor-damper system and an engine, the method comprising: dynamically detecting a resonating frequency of the gas turbine engine system during closed loop operation thereof by filtering a sensed signal f

1. A method for attenuating a frequency from a gas turbine engine system comprising a helicopter rotor-damper system and an engine, the method comprising: dynamically detecting a resonating frequency of the gas turbine engine system during closed loop operation thereof by filtering a sensed signal from the gas turbine engine system through a bank of filters spaced along a frequency detection range;setting a variable parameter of an adaptive compensator in accordance with the resonating frequency as detected; andattenuating the frequency from the gas turbine engine system using the adaptive compensator set in accordance with the resonating frequency as detected. 2. The method of claim 1, wherein the system is part of a full authority digital engine control (FADEC) for managing operation of the engine. 3. The method of claim 1, wherein the bank of filters comprises adaptive filters, and the method comprises dynamically setting center frequencies of the bank of filters to maintain an overall range centered around the resonating frequency as detected. 4. The method of claim 1, wherein the bank of filters comprises overlapping filters to fully cover the frequency detection range. 5. A system for attenuating a frequency from a gas turbine engine system comprising a helicopter rotor-damper system and an engine, the system comprising: a filtering and detection unit comprising a bank of filters spaced along a frequency detection range for receiving a sensed signal and dynamically detecting a resonating frequency of the gas turbine engine system during closed loop operation thereof; andan adaptive compensator operatively connected to the filtering and detection unit, the adaptive compensator having a variable parameter to be set by the filtering and detection unit in accordance with the resonating frequency as detected and configured to receive the sensed signal attenuate the resonating frequency therefrom. 6. The system of claim 5, wherein the system is part of a full authority digital engine control (FADEC) for managing operation of the engine. 7. The system of claim 5, wherein the bank of filters comprises adaptive filters, and the method comprises dynamically setting center frequencies of the bank of filters to maintain an overall range centered around the resonating frequency as detected. 8. The system of claim 5, wherein the bank of filters comprises overlapping filters to fully cover the frequency detection range. 9. A method for attenuating a frequency from a gas turbine engine system, the method comprising: dynamically detecting a resonating frequency of the gas turbine engine system during closed loop operation thereof by filtering a sensed signal from the gas turbine engine system through a bank of filters spaced along a frequency detection range and comprising overlapping filters to fully cover the frequency detection range;setting a variable parameter of an adaptive compensator in accordance with the resonating frequency as detected; andattenuating the frequency from the gas turbine engine system using the adaptive compensator set in accordance with the resonating frequency as detected. 10. The method of claim 9, wherein the gas turbine engine system comprises a helicopter rotor-damper system and an engine. 11. The method of claim 10, wherein the system is part of a full authority digital engine control (FADEC) for managing operation of the engine. 12. The method of claim 9, wherein the bank of filters comprises adaptive filters, and the method comprises dynamically setting center frequencies of the bank of filters to maintain an overall range centered around the resonating frequency as detected. 13. A system for attenuating a frequency from a gas turbine engine system, the system comprising: a filtering and detection unit comprising a bank of filters spaced along a frequency detection range comprising overlapping filters to fully cover the frequency detection range, the filtering and detection unit for receiving a sensed signal and dynamically detecting a resonating frequency of the gas turbine engine system during closed loop operation thereof; andan adaptive compensator operatively connected to the filtering and detection unit, the adaptive compensator having a variable parameter to be set by the filtering and detection unit in accordance with the resonating frequency as detected and configured to receive the sensed signal attenuate the resonating frequency therefrom. 14. The system of claim 13, wherein the gas turbine engine system comprises a helicopter rotor-damper system and an engine. 15. The system of claim 14, wherein the system is part of a full authority digital engine control (FADEC) for managing operation of the engine. 16. The system of claim 13, wherein the bank of filters comprises adaptive filters, and the method comprises dynamically setting center frequencies of the bank of filters to maintain an overall range centered around the resonating frequency as detected.