[특허]Gearbox mounted force generator

Sikorsky Aircraft Corporation

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특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Gearbox mounted force generator

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F03B-011/00
미국특허분류(USC)	415/170.R; 244/017.27
출원번호	US-0799982 (2004-03-12)
발명자 / 주소	Welsh,William A. Eller,Erez Goodman,Robert K.
출원인 / 주소	Sikorsky Aircraft Corporation
대리인 / 주소	Carlson, Gaskey &
인용정보	피인용 횟수 : 13 인용 특허 : 7

초록

An active vibration control (AVC) system includes a shaft-driven gearbox mounted force generator (GMFG) mounted to a main rotor transmission. The GMFGs receive shaft power from an output shaft driven by the main rotor transmission and/or engine-to-transmission gearbox to avoid separate drive motors.

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What is claimed is: 1. An active vibration control system comprising: a first shaft defined along a first axis; a first gear mounted to said first shaft; an input shaft engaged with said first gear; a second gear mounted to said first shaft; a first mass mounted to said second gear; a third gear mounted to said first shaft; a second mass mounted to said third gear; a fourth gear engaged with said second gear and said third gear such that said third gear and said second gear counter-rotate; and a first differential assembly engaged with said first gear and said second gear to selectively adjust rotation of said first mass and said second mass relative said first gear to generate a first vibratory force output. 2. The active vibration control system as recited in claim 1, further comprising: a fifth gear mounted to said first shaft; a sixth gear mounted to said first shaft; a third mass mounted to said sixth gear; a seventh gear mounted to said first shaft; a fourth mass mounted to said seventh gear; an eight gear engaged with said sixth gear and said seventh gear such that said sixth gear and said seventh gear counter-rotate; and a second differential assembly engaged with said fifth gear and said sixth gear to selectively adjust rotation of said third mass and said fourth mass relative said fifth gear to generate a second vibratory force output. 3. The active vibration control system as recited in claim 2, wherein said input shaft is engaged with said first gear and said fifth gear such that said first gear and said fifth gear counter-rotate. 4. The active vibration control system as recited in claim 1, wherein said differential assembly comprises: a second shaft mounted perpendicular to said first shaft; a differential gear mounted to said second shaft, said differential gear engaged with said first gear and said second gear. 5. The active vibration control system as recited in claim 4, further comprising a drive system to rotate said second shaft about said first shaft. 6. The active vibration control system as recited in claim 1, wherein said input shaft is driven by a helicopter engine-to-transmission gearbox. 7. The active vibration control system as recited in claim 1, wherein said input shaft drives a helicopter tail rotor. 8. An active vibration control system comprising: a first shaft defined along a first axis; a first gear mounted to said first shaft; a second gear mounted to said first shaft; a first mass mounted to said second gear; a third gear mounted to said first shaft; a second mass mounted to said third gear; a fourth gear engaged with said second gear and said third gear such that said third gear and said second gear counter-rotate; and a first differential assembly engaged with said first gear and said second gear to selectively adjust rotation of said first mass and said second mass relative said first gear to generate a first vibratory force output wherein said first differential assembly comprises a clutch. 9. An active vibration control system comprising: a first shaft defined along a first axis; a first gear mounted to said first shaft; a second gear mounted to said first shaft; a first mass mounted to said second gear; a third gear mounted to said first shaft; a second mass mounted to said third gear; a fourth gear engaged with said second gear and said third gear such that said third gear and said second gear counter-rotate; and a first differential assembly engaged with said first gear and said second gear to selectively adjust rotation or said first mass and said second mass relative said first gear to generate a first vibratory force output wherein said first differential assembly comprises a magnetorheological fluid clutch. 10. An active vibration control system comprising: a helicopter transmission; an engine-to-transmission gearbox which drives said helicopter transmission; and a force generator mounted to said engine-to-transmission gearbox, said force generator mechanically driven by an input shaft rotated by said engine-to-transmission gearbox. 11. The active vibration control system as recited in claim 10, wherein said force generator is mechanically rotated by said input shaft. 12. The active vibration control system as recited in claim 10, wherein said force generator is directly driven by said input shaft. 13. An active vibration control system comprising: a helicopter transmission; an engine-to-transmission gearbox which drives said helicopter transmission; and a force generator mounted to said engine-to-transmission gearbox, said force generator driven by an input shaft rotated by said engine-to-transmission gearbox; a first shaft defined along a first axis; a first gear mounted to said first shaft, said first gear driven by said input shaft; a second gear mounted to said first shaft; a first mass mounted to said second gear, a third gear mounted to said first shaft; a second mass mounted to said third gear; a fourth gear engaged with said second gear and said third gear such that said third gear and said second gear counter-rotate; and a first differential assembly engaged with said first gear and said second gear to selectively adjust rotation of said first mass and said second mass relative said first gear to generate a first vibratory force output. 14. An active vibration control system comprising: a helicopter transmission; an engine-to-transmission gearbox which drives said helicopter transmission; and a force generator mounted to said engine-to-transmission gearbox, said force generator driven by an input shaft rotated by said engine-to-transmission gearbox; and a second force generator mounted to said helicopter transmission, said second force generator driven by an output to a helicopter tail rotor. 15. An active vibration control system comprising: a helicopter transmission; and a force generator mounted to and mechanically driven by said helicopter transmission. 16. The active vibration control system as recited in claim 15, further comprising a second force generator mounted to said helicopter transmission, said second force generator mechanically driven by an output to a helicopter tail rotor. 17. The active vibration control system as recited in claim 15, further comprising: an engine-to-transmission gearbox which drives said helicopter transmission; and a second force generator mechanically driven by said engine-to-transmission gearbox. 18. The active vibration control system as recited in claim 15, wherein said force generator is mechanically rotated by a shaft driven by said helicopter transmission. 19. The active vibration control system as recited in claim 15, wherein said force generator is directly driven by a shaft driven by said helicopter transmission. 20. The active vibration control system as recited in claim 15, further comprising a plurality of sensors located adjacent an aircraft cabin, said plurality of sensor in communication with said force generator for operation of said force generator in response thereto. 21. The active vibration control system as recited in claim 15, wherein said force generator includes a shaft driven gearbox that is mechanically driven by a shaft rotated by said helicopter transmission. 22. The active vibration control system as recited in claim 15, wherein said force generator includes a shaft driven gearbox that is mechanically driven by a tail rotor driveshaft rotated by said helicopter transmission. 23. An active vibration control system comprising: a helicopter transmission; and a force generator mechanically driven by said helicopter transmission. 24. The active vibration control system as recited in claim 23, wherein said force generator is directly driven by a shaft driven by said helicopter transmission. 25. The active vibration control system as recited in claim 23, wherein said force generator is directly driven by a tail rotor driveshaft driven by said helicopter transmission. 26. The active vibration control system as recited in claim 23, wherein said force generator further comprises: a first shaft defined along a first axis; a first gear mounted to said first shaft; a second gear mounted to said first shaft; a second shaft mounted perpendicular to said first shaft, said first shaft mechanically driven by said helicopter transmission to rotate said second shaft about said first shaft; and a differential gear mounted to said second shaft, said differential gear engaged with said first gear and said second gear to selectively, adjust rotation of a first mass and a second mass relative said first gear to generate a first vibratory force output.

이 특허에 인용된 특허 (7)

이 특허를 인용한 특허 피인용횟수: 13

IPC 상위 출원인

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상세정보
내보내기 구분	파일저장 인쇄 메일전송
구성항목	관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
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특허 상세정보

Gearbox mounted force generator

초록

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이 특허에 인용된 특허 (7)

이 특허를 인용한 특허 피인용횟수: 13

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IPC 상세정보(version : 201201)

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특허 상세정보

Gearbox mounted force generator

초록

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이 특허에 인용된 특허 (7)

이 특허를 인용한 특허 피인용횟수: 13

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

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