[특허]Modules and methods for biasing power to a multi-engine power plant suitable for one engine inoperative flight procedure training

Modules and methods for biasing power to a multi-engine power plant suitable for one engine inoperative flight procedure training 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G09B-009/16 G09B-009/08 G09B-009/18 G09B-009/46 B62D-001/22 G09B-009/20 A63H-027/00 B64C-027/04 G09B-009/44 B62D-001/02
출원번호	US-0018219 (2008-01-23)
등록번호	US-9355571 (2016-05-31)
발명자 / 주소	Rucci, John Stobiecki, Anthony Z. Davis, Brent Myers, Christopher James
출원인 / 주소	Sikorsky Aircraft Corporation
대리인 / 주소	Carlson, Gaskey & Olds, P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 38

초록 ▼

A system and method for conducting flight procedures training in a rotary-wing aircraft with a multi-engine powerplant includes determining a variable bias relative an available power margin to simulate a reduced power available flight condition; and displaying symbology indicative of the simulated

대표청구항 ▼

1. A method for conducting flight procedures training in a rotary-wing aircraft with a multi-engine powerplant comprising: continuously determining an instantaneous available power margin of the multi-engine powerplant system in real time;continuously determining a variable bias relative to the instantaneous available power margin;limiting a torque of each engine of the multi-engine powerplant system relative to the variable bias to simulate a reduced power available for a flight condition; anddisplaying symbology indicative of the simulated reduced power available flight condition. 2. A method as recited in claim 1, wherein said determining an available power margin further comprises: utilizing current ambient conditions and current aircraft weight to determine the available power margin. 3. A method as recited in claim 1, further comprising: equally reducing a power from each engine of the multi-engine powerplant to simulate the reduced power available flight condition in response to the reduced power available flight condition such that said reduced power available flight condition will result in a rotor droop condition. 4. A method as recited in claim 1, wherein limiting the torque of each engine maintains level-loading of a main rotor gearbox. 5. A method as recited in claim 1, further comprising: selecting the reduced power available flight condition based at least in part on a predefined aircraft weight. 6. A method as recited in claim 1, further comprising: selecting the reduced power available flight condition based at least in part on a predefined maximum internal aircraft weight condition. 7. A method as recited in claim 1, further comprising: selecting the reduced power available flight condition based at least in part on a predefined maximum external aircraft weight condition. 8. A method as recited in claim 1, further comprising: selecting the reduced power available flight condition based at least in part on one engine inoperable (OEI) condition. 9. A method as recited in claim 1, further comprising: associating the reduced power available flight condition in relation to a one engine inoperable (OEI) condition at a predefined aircraft weight. 10. A method as recited in claim 9, wherein said displaying symbology step further comprises: randomly selecting one engine for simulated failure display symbology; anddisplaying symbology indicative of the simulated failure of the selected engine. 11. A method as recited in claim 10, wherein said displaying symbology step further comprises: displaying a timer representing engine operation in response to the simulated operation when operating above a predetermined operational time limit. 12. A method as recited in claim 1, wherein said displaying symbology step further comprises: displaying symbology indicative that a training state is active. 13. A method as recited in claim 1, wherein said displaying symbology step further comprises: modifying symbology indicating turbine gas temperature (TGT) and engine torque of all engines of the multi-engine powerplant to indicate increases in TGT and engine torque to simulate an increase in aircraft weight. 14. A method as recited in claim 1, wherein said displaying symbology step further comprises: modifying symbology indicating turbine gas temperature (TGT) and engine torque of all engines of the multi-engine powerplant to indicate decreases in the TGT and engine torque to simulate decrease in aircraft weight. 15. A method as recited in claim 1, wherein said displaying symbology step further comprises: displaying a symbology indicative of a First Limit Indicator (FLI) adjacent symbology indicative of a rotor torque. 16. A module for conducting flight procedures training in a rotary-wing aircraft, comprising: a multi-engine powerplant system;a cockpit instrument display system; andan OEI/BIAS training system in communication with said multi-engine powerplant system and said cockpit instrument display system, said OEI/BIAS training system operable to continuously determine a variable bias relative to a continuously updated available power margin by limiting a torque of each engine of said multi-engine powerplant system to simulate a reduced power available flight condition, wherein the continuously updated available power margin is continuously updated in real time. 17. The module as recited in claim 16, wherein said multi-engine powerplant system includes three engines. 18. The module as recited in claim 17, wherein said training system operates to apply a symmetrical load limit on each of the three engines of the multi-engine powerplant system. 19. The module as recited in claim 16, wherein said cockpit instrument display system is operable to display a TORQUE DISPLAY which expands to a QUAD TAC DISPLAY in response to a rotor droop condition. 20. The module as recited in claim 19, wherein said QUAD TAC DISPLAY is operable to display a torque bar for each engine in response to the rotor droop condition. 21. The module as recited in claim 16, wherein said cockpit instrument display system comprises an OEI/BIAS display operable to displays a multiple of selectable weight biases associated with a respective multiple of reduced power available flight conditions. 22. A method as recited in claim 1, further comprising: simulating releasing an external load; andchanging the torque of each engine of the multi-engine powerplant system to simulate the reduced power available flight condition related to an aircraft weight condition without the external load. 23. A method as recited in claim 1, further comprising: continuously calculating the available power margin from an actual aircraft weight and a desired training weight. 24. A method as recited in claim 23, wherein the desired training weight is a maximum internal aircraft weight condition. 25. A method as recited in claim 23, wherein the desired training weight is a maximum external aircraft weight condition. 26. A method as recited in claim 23, wherein the desired training weight is a one engine inoperable (OEI) condition.

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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

내보내기 구분	파일저장 인쇄 메일전송
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Modules and methods for biasing power to a multi-engine power plant suitable for one engine inoperative flight procedure training 원문보기

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Modules and methods for biasing power to a multi-engine power plant suitable for one engine inoperative flight procedure training 원문보기

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