[특허]Gas turbine engine fixed collective takeoff compensation control system and method

Honeywell International Inc.

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특허 상세정보

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Gas turbine engine fixed collective takeoff compensation control system and method

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G05D-001/00
미국특허분류(USC)	701/015; 701/003; 701/004; 701/005; 701/100; 244/017.11; 244/017.13; 244/181; 434/033
출원번호	US-0046245 (2008-03-11)
등록번호	US-8275500 (2012-09-25)
발명자 / 주소	Buehman, Guerry
출원인 / 주소	Honeywell International Inc.
대리인 / 주소	Ingrassia Fisher & Lorenz, P.C.
인용정보	피인용 횟수 : 1 인용 특허 : 23

초록

A system and method of controlling a gas turbine engine controller in a rotorwing aircraft includes determining when a fixed collective takeoff (FCTO) of the rotorwing aircraft is being conducted. A control loop gain of the gas turbine engine controller is at least selectively varied when the FCTO is being conducted.

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1. A method of controlling a gas turbine engine controller in a rotorwing aircraft that includes a gas turbine engine, an engine throttle, and a collective, the method comprising the steps of: determining when a fixed collective takeoff (FCTO) of the rotorwing aircraft is being conducted; andwhen the FCTO is being conducted, at least selectively varying a control loop gain of the gas turbine engine controller,wherein the step of determining when the FCTO is being conducted comprises: determining that the collective is positioned at a collective pitch that is less than a predetermined collective pitch; anddetermining that the engine throttle is positioned at a throttle position that is less than a predetermined throttle position. 2. The method of claim 1, wherein the step of determining when the FCTO is being conducted further comprises determining that the gas turbine engine is generating an amount of torque that is within a predetermined torque range. 3. The method of claim 1, further comprising: determining when the FCTO is complete; andwhen the FCTO is complete, no longer at least selectively varying the control loop gain of the gas turbine engine controller. 4. The method of claim 3, wherein the step of determining when the FCTO is complete comprises: determining when the rotorwing aircraft has increased in altitude a predetermined amount. 5. The method of claim 4, wherein the step of determining when the rotorwing aircraft has increased in altitude a predetermined amount comprises: determining an initial ambient pressure, the initial ambient pressure being ambient pressure around the rotorwing aircraft when the FCTO was commenced; anddetermining when the ambient pressure around the rotorwing aircraft has varied a predetermined pressure magnitude from the initial ambient pressure. 6. The method of claim 1, wherein the gas turbine engine controller is operable to control the speed of a gas turbine engine, and wherein the method further comprises: determining a speed error in the gas turbine engine controller, the speed error based on a difference between actual gas turbine engine speed and commanded gas turbine engine speed; andat least selectively varying the control loop gain of the gas turbine engine controller based on the determined speed error. 7. The method of claim 1, wherein the gas turbine engine controller includes a proportional gain and a derivative gain, and wherein the step of at least selectively varying a control loop gain of the gas turbine engine controller comprises: at least selectively varying the proportional gain; andat least selectively varying the derivative gain. 8. A gas turbine engine control system for a rotorwing aircraft, comprising: fixed collective takeoff (FCTO) determination logic, the FCTO determination logic operable to determine when a FCTO is being conducted and, when a FCTO is being conducted, supply a FCTO enable signal;a gas turbine engine controller operable to control the speed of a gas turbine engine, the gas turbine engine controller coupled to the FCTO determination logic and operable to supply a speed error signal representative of a difference between actual gas turbine engine speed and commanded gas turbine engine speed; andgain multiplier logic coupled to receive the speed error signal and the FCTO enable signal and operable, upon receipt thereof, to supply variable control loop gain multipliers. 9. The system of claim 8, wherein: the FCTO determination logic is adapted to receive one or more signals representative of gas turbine engine state and a signal representative of a collective position; andthe FCTO determination logic is operable, upon receipt of the one or more signals representative of gas turbine engine state and the signal representative of collective position, to determine when the FCTO is being conducted. 10. The system of claim 9, wherein the FCTO determination logic is operable: upon receipt of the one or more signals representative of gas turbine engine state, to determine that a gas turbine engine is in a predetermined state; andupon receipt of the signal representative of collective position, to determine that a collective is positioned at a collective pitch that is less than a predetermined collective pitch. 11. The system of claim 10, wherein: the one or more signals representative of gas turbine engine state include a signal representative of an amount of torque being generated by a gas turbine engine; andthe FCTO determination logic is operable to determine that the amount of torque being generated is within a predetermined torque range. 12. The system of claim 11, wherein: the one or more signals representative of gas turbine engine state further include a signal representative of engine throttle position; andthe FCTO determination logic is operable to determine that the engine throttle is positioned at a throttle position that is less than a predetermined throttle position. 13. The system of claim 8, wherein the FCTO determination logic is further operable to: determine when the FCTO is complete; andno longer supply the FCTO enable signal when the FCTO is determined to be complete. 14. The system of claim 13, wherein: the FCTO determination logic is adapted to receive a signal representative of rotorwing aircraft altitude; andthe FCTO determination logic is operable to determine when the FCTO is complete based on the signal representative of rotorwing aircraft altitude. 15. The system of claim 14, further comprising: an ambient pressure sensor operable to sense ambient pressure and supply an ambient pressure signal, the ambient pressure signal being the signal representative of rotorwing aircraft altitude. 16. The system of claim 15, wherein: the FCTO determination logic is further operable, upon initially determining that a FCTO is being conducted, to store an initial ambient pressure value, the initial ambient pressure being the sensed ambient pressure when the FCTO was commenced; andthe FCTO determination logic determines that the FCTO is complete when the sensed ambient pressure has varied a predetermined pressure magnitude from the initial ambient pressure value. 17. The system of claim 8, wherein the gain multiplier logic is further operable to selectively vary the control loop gain multipliers supplied thereby based on the speed error signal. 18. The system of claim 8, wherein the control loop gain multipliers include proportional gain multipliers and derivative gain multipliers, and wherein the system further comprises: a gas turbine engine controller that implements both a proportional gain and a derivative gain, the gas turbine engine controller coupled to receive the proportional gain multipliers and the derivative gain multipliers and, upon receipt thereof, to at least selectively vary the proportional gain and the derivative gain, respectively. 19. A method of controlling a gas turbine engine controller in a rotorwing aircraft, the gas turbine engine controller including a proportional gain and a derivative gain, the method comprising the steps of: determining when a fixed collective takeoff (FCTO) of the rotorwing aircraft is being conducted; andwhen the FCTO is being conducted, at least selectively varying a control loop gain of the gas turbine engine controller by at least selectively varying the proportional gain and at least selectively varying the derivative gain.

이 특허에 인용된 특허 (23)

이 특허를 인용한 특허 피인용횟수: 1

Marin, Jean Philippe Jacques; Gallot, Matthieu; Etchepare, Philippe. Device and method for controlling an auxiliary engine suitable for supplying thrust power to the rotor of a helicopter. USP2018039919806.

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Gas turbine engine fixed collective takeoff compensation control system and method

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