Preventing rotation of a fixed ring of a swashplate
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0316061
(2011-12-09)
|
등록번호 |
US-8961138
(2015-02-24)
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발명자
/ 주소 |
- Wiinikka, Mark
- Griffin, Maurice
- Speller, Charles
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출원인 / 주소 |
- Bell Helicopter Textron Inc.
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
0 인용 특허 :
10 |
초록
▼
According to one embodiment, a rotor system, comprise a mating element, a sleeve, a first swashplate ring, a locking element, and a second swashplate ring. The mating element having a first plurality of grooves a first plurality of ridges. The sleeve is positioned inside the mating element such that
According to one embodiment, a rotor system, comprise a mating element, a sleeve, a first swashplate ring, a locking element, and a second swashplate ring. The mating element having a first plurality of grooves a first plurality of ridges. The sleeve is positioned inside the mating element such that the sleeve prevents rotation of the mating element about the sleeve while allowing the mating element to translate along the sleeve. The sleeve has a second plurality of grooves mating with the first plurality of ridges and a second plurality of ridges mating with the first plurality of grooves. The first swashplate ring is positioned around the mating element, and the locking element prevents. the first swashplate ring from rotating about the sleeve. The second swashplate ring is rotatable about the sleeve.
대표청구항
▼
1. A rotor system, comprising: a gearbox;a mating element having a first plurality of grooves and a first plurality of ridges;a sleeve coupled to and around the gearbox and positioned inside the mating element such that the sleeve prevents rotation of the mating element about the sleeve, the sleeve
1. A rotor system, comprising: a gearbox;a mating element having a first plurality of grooves and a first plurality of ridges;a sleeve coupled to and around the gearbox and positioned inside the mating element such that the sleeve prevents rotation of the mating element about the sleeve, the sleeve having a second plurality of grooves mating with the first plurality of ridges and a second plurality of ridges mating with the first plurality of grooves;a first swashplate ring positioned around the mating element;a locking element preventing the first swashplate ring from rotating about the axis of the sleeve; anda second swashplate ring rotatable about the sleeve. 2. The rotor system of claim 1, further comprising a gearbox, wherein the sleeve is coupled to and around the gearbox. 3. The rotor system of claim 1, wherein the second plurality of grooves and the second plurality of ridges alternate continuously about the sleeve. 4. The rotor system of claim 1, wherein: the mating element comprises a curved surface; andthe first swashplate ring is pivotable along the curved surface. 5. The rotor system of claim 1, further comprising a key element positioned in an opening of the mating element and configured to receive the locking element. 6. The rotor system of claim 1, wherein the plurality of first ridges comprises at least five ridges. 7. The rotor system of claim 1, wherein the mating element is configured to slide axially relative to the sleeve. 8. A helicopter, comprising: a power train operable to rotate a drive shaft;a plurality of rotor blades operable to rotate in response to rotation of the drive shaft;a gearbox surrounding a portion of the drive shaft;a mating element having a first plurality of grooves and a first plurality of ridges;a sleeve coupled to and around the gearbox and positioned inside the mating element such that the sleeve prevents rotation of the mating element about the sleeve, the sleeve having a second plurality of grooves mating with the first plurality of ridges and a second plurality of ridges mating with the first plurality of grooves;a first swashplate ring positioned around the mating element;a locking element preventing the first swashplate ring from rotating about the sleeve; anda second swashplate ring rotatable about the sleeve with rotation of the plurality of rotor blades. 9. The helicopter of claim 8, wherein the second plurality of grooves and the second plurality of ridges alternate continuously about the sleeve. 10. The helicopter of claim 8, wherein: the mating element comprises a curved surface; andthe first swashplate ring is pivotable along the curved surface. 11. The helicopter of claim 8, further comprising a key element positioned in an opening of the mating element and configured to receive the locking element. 12. The helicopter of claim 8, wherein the plurality of first ridges comprises at least five ridges. 13. The helicopter of claim 8, wherein the mating element is configured to slide axially relative to the sleeve. 14. A swashplate rotor system, comprising: a gearbox;a mating element having a first plurality of grooves and a first plurality of ridges;a sleeve coupled to and around the gear box and positioned inside the mating element such that the sleeve prevents rotation of the mating element about the sleeve, the sleeve having a second plurality of grooves mating with the first plurality of ridges and a second plurality of ridges mating with the first plurality of grooves. 15. The rotor system of claim 14, wherein the second plurality of grooves and the second plurality of ridges alternate continuously about the sleeve. 16. The rotor system of claim 14, wherein the plurality of first ridges comprises at least five ridges. 17. The rotor system of claim 14, wherein the mating element is configured to slide axially relative to the sleeve. 18. The rotor system of claim 14, further comprising: a first swashplate ring positioned around the mating element;a locking element preventing the first swashplate ring from rotating about the sleeve; anda second swashplate ring rotatable about the sleeve with rotation of the plurality of rotor blades. 19. The rotor system of claim 18, wherein: the mating element comprises a curved surface; andthe first swashplate ring is pivotable along the curved surface. 20. The rotor system of claim 18, further comprising a key element positioned in an opening of the mating element and configured to receive the locking element.
이 특허에 인용된 특허 (10)
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Scala,Vincent, Blade pitch control disk device for a rotorcraft rotor.
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Cycon James P. (Orange CT) Kohlhepp Fred W. (Hamden CT) Millea Vincent F. (Stratford CT), Coaxial transmission/center hub subassembly for a rotor assembly having ducted, coaxial counter-rotating rotors.
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White Kevin A. ; Hunter David H. ; Milne Robert J. ; Poulin Stephen V. ; Trembicki Robert J., Control rod mounting arrangement for helicopter swashplates.
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Pancotti Santino,ITX, Cyclic and collective pitch control device for a helicopter rotor.
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Daldosso Louis J. (Les Milles FRX), Device for controlling the pitch of the blades of a rotorcraft rotor.
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Byrnes Francis E. (White Plains NY) Hibyan Edward S. (Trumbull CT) Krauss Albert T. (Harwinton CT), Elastomeric swashplate configuration for helicopters.
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Leman Jean-Luc (Aix-en-Provence FRX), Helicopter swashplate mounted on articulations uncouled in pitching and rolling.
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Griffith Carl D. (9114 Luna Del Oro NE. Albuquerque NM 87111), Individual blade control system for helicopters.
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Rampal Etienne,FRX, Swash-plate device for controlling the pitch of rotor blades with non-rotating plate articulated on a central ball joint.
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Shepherd David S. (Wallingford PA), Swashplate anti-drive linkage for rotor controls of rotary wing aircraft.
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