[특허]Rotor blade pitch control

The Boeing Company

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Rotor blade pitch control

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-011/06
미국특허분류(USC)	416/001; 416/163; 244/017.25
출원번호	UP-0559651 (2006-11-14)
등록번호	US-7674091 (2010-04-21)
발명자 / 주소	Zierten, Daniel T.
출원인 / 주소	The Boeing Company
대리인 / 주소	Haynes & Boone, LLP.
인용정보	피인용 횟수 : 6 인용 특허 : 4

초록
▼

A mechanical independent blade control (MIBC) mechanism for controlling the pitch of each of the blades of a rotor blade system or a main rotor of a rotor aircraft independently of the other blades includes a plurality of actuators disposed in the fuselage below the hub of the rotor, each being operable to selectively control the pitch of an associated one of the blades independently of the other blades, and a plurality of mechanical linkages disposed within the annulus of the rotor mast, each coupled between a blade and an actuator and operable to trans...

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청구항
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What is claimed is: 1. A mechanism for controlling the pitch of each of the blades of an aircraft rotor thrust system independently of the other blades thereof, comprising: an elongated tubular rotor mast having a long axis, an upper end coupled to a hub of the rotor for conjoint rotation therewith, and a lower end coupled to and rotationally driven by an engine of the aircraft; a plurality of pitch tubes equal in number to the number of blades of the rotor disposed coaxially within the rotor mast and fixed against conjoint rotation therewith; an actuator coupled to a lower end of an associated one of each of the pitch tubes, each being operable to selectably move the associated pitch tube back and forth in the axial direction independently of the other pitch tubes; a pitch plate disposed at an upper end of an associated one of each of the pitch tubes for conjoint rotation with the rotor mast, each having an inner periphery coupled to the upper end of the associated pitch tube for both conjoint axial movement therewith and rotational movement relative thereto, and an outer periphery coupled to an inner surface of the rotor mast for both conjoint rotation therewith and axial movement relative thereto; and, an elongated pitch link having a lower end fixed to an associated one of each of the pitch plates for conjoint axial and rotational movement therewith, and an upper end coupled to a pitch horn disposed at an inner end of an associated one of the blades of the rotor. 2. The mechanism of claim 1, further comprising a mechanism disposed at a lower end portion of each of the pitch tubes for providing lateral support to the lower end portion of the pitch tube and for fixing the pitch tube against conjoint rotation with the rotor mast. 3. The mechanism of claim 1, wherein the outer periphery of each of the pitch plates is coupled to the inner surface of the associated rotor mast by a slider disposed at the outer periphery of the pitch plate and slidably engaged in an axial slot in the inner surface of the rotor mast for both conjoint rotation therewith and for relative sliding axial movement therein. 4. The mechanism of claim 1, wherein the inner periphery of each of the pitch plates is coupled to the upper end of the associated pitch tube by a bearing coupled between the inner periphery of the pitch plate and the upper end of the pitch tube so as to enable both conjoint axial movement therewith and rotational movement relative thereto. 5. The mechanism of claim 1, wherein: the aircraft includes a gearbox having an opening therethrough; the lower end of the rotor mast extends into the gearbox; and, the pitch tubes extend through the opening in the gearbox such that the pitch plates and the pitch links are disposed above the actuators and the lower ends of the pitch tubes and the actuators are disposed below the gearbox. 6. The mechanism of claim 1, wherein the actuators comprise linear or rotary actuators. 7. The mechanism of claim 1, wherein the actuators are driven electrically or hydraulically. 8. The mechanism of claim 1, further comprising a plurality of redundant actuators coupled to the lower end of an associated one of each of the pitch tubes, each being capable of selectably moving the associated pitch tube back and forth in the axial direction independently of the operation of the other actuators coupled thereto. 9. The mechanism of claim 1, wherein the pitch plates are disposed one above the other, with the lower pitch links extending through openings in the upper pitch plates. 10. A rotor thrust system for an aircraft, comprising: at least one main rotor having a hub and a plurality of blades coupled thereto; and, the blade pitch control mechanism of claim 1 coupled to the hub and the blades of the rotor and controlling the pitch of each of the blades independently of the other blades. 11. A helicopter incorporating the rotor thrust system of claim 10. 12. A method for controlling the pitch of each of the blades of an aircraft rotor thrust system, the method comprising: coupling an upper end of an elongated annular rotor mast to a hub of the rotor system for conjoint rotation therewith; rotationally driving a lower end of the rotor mast; disposing a plurality of mechanical linkages within the annulus of the rotor mast; providing a plurality of actuators below the hub of the rotor, each actuator being operable to selectively control the pitch of an associated one of the blades independently of the other blades; and, coupling each of a plurality of mechanical linkages between an associated one of the blades and an associated one of the actuators, each linkage being operable to transmit a force output by the associated actuator to a pitch horn fixed to an inner end of the associated blade; and, controlling the pitch of each blade of the rotor system independently of the other blades with the associated actuator. 13. The method of claim 12, wherein controlling the pitch of the blades comprises changing the direction of pitch of each blade more than twice during a single revolution of the hub. 14. A rotor aircraft, comprising: a fuselage; a main rotor rotatably coupled to the fuselage, the rotor including a rotatable hub and a plurality of radially extending blades, each having an inner end coupled to the hub for rotation of the blade about each of three mutually perpendicular axes relative to the hub; an engine for rotatably driving the hub; an elongated annular rotor mast having a long axis, an upper end coupled to the hub for conjoint rotation therewith, and a lower end coupled to and rotationally driven by the engine; and, a mechanical individual blade control (MIBC) mechanism for controlling the pitch of each of the blades of the rotor independently of the other blades during rotation of the hub, the MIBC comprising: a plurality of actuators equal in number to the number of blades of the rotor disposed in the fuselage below the hub, each being operable to selectively control the pitch of an associated one of the blades independently of the other blades; and, a plurality of mechanical linkages disposed within the annulus of the rotor mast, each linkage being coupled between an associated one of the blades and an associated one of the actuators and operable to transmit a force output by the associated actuator to a pitch horn fixed to an inner end of the associated blade. 15. The rotor aircraft of claim 14, wherein each mechanical linkage comprises: a pitch tube disposed within the rotor mast and fixed against conjoint rotation therewith; a pitch plate disposed at an upper end of the pitch tube for conjoint rotation with the rotor mast and having an inner periphery coupled to the upper end of the pitch tube for both conjoint axial movement therewith and rotational movement relative thereto, and an outer periphery coupled to an inner surface of the rotor mast for both conjoint rotation therewith and axial movement relative thereto; and, an elongated pitch link having a lower end fixed to the pitch plate for conjoint axial and rotational movement therewith, and an upper end coupled to the pitch horn of the associated blade of the rotor. 16. The rotor aircraft of claim 15, wherein the pitch tubes are disposed concentrically within the rotor mast. 17. The rotor aircraft of claim 15, wherein the outer periphery of the pitch plate is coupled to the inner surface of the rotor mast by a slider disposed at the outer periphery of the pitch plate and engaged in an axial feature in the inner surface of the rotor mast for both conjoint rotation therewith and relative sliding axial movement therein. 18. The rotor aircraft of claim 15, wherein the inner periphery of the pitch plate is coupled to the upper end of the pitch tube by a bearing coupled between the inner periphery of the pitch plate and the upper end of the pitch tube so as to enable both conjoint axial movement therewith and rotational movement relative thereto. 19. The rotor aircraft of claim 14, wherein: the aircraft includes a gearbox having an opening therethrough; the lower end of the rotor mast extends into the gearbox; and, the mechanical linkages extend through the opening in the gearbox such that an upper end of each of the linkages is disposed above the actuators and a lower end of each of the linkages is disposed below the gearbox. 20. The rotor aircraft of claim 14, wherein the actuators comprise linear or rotary actuators.

이 특허에 인용된 특허 (4)

이 특허를 인용한 특허 피인용횟수: 6

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Rotor blade pitch control

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이 특허에 인용된 특허 (4)

이 특허를 인용한 특허 피인용횟수: 6

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Rotor blade pitch control

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이 특허에 인용된 특허 (4)

이 특허를 인용한 특허 피인용횟수: 6

IPC 상위 출원인

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IPC 상세정보(version : 201201)

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