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    CONSTANT-VELOCITY DRIVE SYSTEM FOR GIMBALED ROTOR HUBS
    1.
    发明公开
    CONSTANT-VELOCITY DRIVE SYSTEM FOR GIMBALED ROTOR HUBS 审中-公开
    恒定转速恒星恒速驱动系统

    公开(公告)号：KR20090029215A

    公开(公告)日：2009-03-20

    申请号：KR20087030745

    申请日：2008-12-17

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： RAUBER RICHARD ,  STAMPS FRANK B ,  BRASWELL JAMES LEE JR

    IPC: B64C27/35

    Abstract: A constant-velocity drive system for a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed. A rotary-wing aircraft having a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed.

    Abstract translation: 公开了一种用于旋转翼飞行器转子的恒速驱动系统，其包括差动转矩分解机构和万向架机构。 公开了具有旋转翼飞行器转子的旋转翼飞机，其包括差速扭矩分离机构和万向架机构。

    ROTARY-WING AIRCRAFT TORQUE COUPLING WITH PAD BEARINGS
    2.
    发明公开
    ROTARY-WING AIRCRAFT TORQUE COUPLING WITH PAD BEARINGS 审中-公开
    旋转式飞机扭矩联轴器与垫片轴承

    公开(公告)号：KR20090047531A

    公开(公告)日：2009-05-12

    申请号：KR20097005506

    申请日：2009-03-17

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： STAMPS FRANK B ,  RAUBER RICHARD ,  POPELKA DAVID ,  TISDALE PAT ,  CAMPBELL TOM ,  BRASWELL JAMES LEE JR

    IPC: B64C27/12 ,  B64C27/35 ,  B64C27/473 ,  B64C27/48

    Abstract: 회전익 항공기의 로터 헤드용 토크 커플링은 마스트와 함께 회전하고 부착된 요크를 회전시키도록 구성된다. 토크 커플링은 마스트와 함께 회전하고 대체로 반경 방향으로 연장되는 트러니언을 구비한다. 패드 베어링 조립체는 적층식 구형 베어링에 의해 트러니언들 중 하나에 연결되는 중앙 부재를 각각 갖고 중앙 부재의 양측에 고정되는 적층식 패드 베어링을 구비한다. 적층식 베어링은 강성층과 탄성층을 번갈아 구비한다. 베어링 장착부는 각 패드 베어링에 고정되고 요크에 결합되어 요크를 마스트와 함께 회전시킨다. 패드 베어링 조립체는탄성층의 탄성 전단 변형을 통해 각 중앙 부재와 관련된 트러니언 간에 그리고 각 중앙 부재와 베어링 장착부 간에 상대 운동을 가능하게 하며, 이를 통해 마스트에 대해 부착된 요크의 짐벌링이 가능해 진다.

    CF BEARING WITH STEADY PITCHING MOMENT
    3.
    发明公开
    CF BEARING WITH STEADY PITCHING MOMENT 审中-公开
    CF轴承与稳定的俯仰动画

    公开(公告)号：KR20090033241A

    公开(公告)日：2009-04-01

    申请号：KR20097001233

    申请日：2009-01-20

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： STAMPS FRANK B ,  RAUBER RICHARD

    IPC: B64C27/48 ,  B64C27/28 ,  B64C27/54

    Abstract: A centrifugal force bearing having a means for providing a steady pitching moment is disclosed. The centrifugal force bearing may optionally comprise a coning means. A rotor system having the centrifugal force bearing is disclosed. A rotary-wing aircraft having the centrifugal force bearing is disclosed.

    Abstract translation: 公开了具有用于提供稳定俯仰力矩的装置的离心力轴承。 离心力轴承可以可选地包括锥形装置。 公开了一种具有离心力轴承的转子系统。 公开了一种具有离心力轴承的旋翼飞机。

    ROTATION PREVENTING CLIP
    4.
    发明专利
    ROTATION PREVENTING CLIP 失效

    公开(公告)号：JP2001122196A

    公开(公告)日：2001-05-08

    申请号：JP2000284813

    申请日：2000-09-20

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： DAY CLIFTON B ,  ZIERER JOSEPH J ,  COVINGTON ED C

    IPC: B64C27/28 ,  B64C27/04 ,  B64C27/22 ,  B64C27/605

    Abstract: PROBLEM TO BE SOLVED: To prevent contact between a bearing housing of an actuator rod and a crevice of a non-rotation swash plate in a rotation control system for a tilt-rotor aircraft or the like to prevent abrasion and structural damage. SOLUTION: This rotation preventing clip 65 restricting rotation of the actuator rod 129 disposed between a pair of crevice arms 117a, 117b for the non- rotation swash plate 111 around its axis has a restriction member 97 projecting toward the rod 129.

    TILT ROTOR DOWN STOP ASSEMBLY
    5.
    发明专利
    TILT ROTOR DOWN STOP ASSEMBLY 失效

    公开(公告)号：JP2001080587A

    公开(公告)日：2001-03-27

    申请号：JP2000238214

    申请日：2000-08-07

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： RYAN MICHAEL J ,  ZIMMERMAN BRETT R

    IPC: B64C27/58 ,  B64C27/26 ,  B64C27/28 ,  B64C27/32 ,  B64C29/00

    Abstract: PROBLEM TO BE SOLVED: To provide a tilt rotor down stop assembly for separating a horizontal load and having a low height by providing a pivotally movable striker assembly and a down stop assembly including a cradle assembly formed so as to receive the striker assembly freely to be removed. SOLUTION: A striker assembly 31 includes a base member 33 formed so as to receive an adjustable striker arm 35 formed with angle. The base member 33 includes an installation opening part 36. The striker arm 35 is formed into an L-shape having a post part 37 and a leg part 39. A down stop assembly is moved from a tip part 49 to a leg part 39 of the post part 37 generated by a tilt rotor assembly in the flying mode by the striker assembly 31. With this structure, a cradle assembly can be maintained at a low height.

    METHOD FOR FORMING COMPOSITE FIBER ARTICLE
    7.
    发明专利
    METHOD FOR FORMING COMPOSITE FIBER ARTICLE 失效

    公开(公告)号：JP2001097287A

    公开(公告)日：2001-04-10

    申请号：JP2000236446

    申请日：2000-08-04

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： MOORE ROBERT A ,  MEASOM RONALD J

    IPC: B64C27/473 ,  B29C70/06 ,  B29C70/24 ,  B29C70/30 ,  B29C70/38 ,  B29D99/00

    Abstract: PROBLEM TO BE SOLVED: To provide a method for manufacturing a complicated shape such as the shape of beams of a rotor blade of tilt rotor aircraft and a product manufactured using the method. SOLUTION: This method for forming a composite fiber article comprises the steps of selecting a plurality of cross-sections determining an article, defining a plurality of points in each cross-section as fiber strip disposing points, grouping these points in some sets so that each cross-section includes one point to define the continuous arrangement of the fiber strips, and applying strips 62 to the article at these points.

    Engine exhaust gas deflection system
    9.
    发明专利
    Engine exhaust gas deflection system 有权
    发动机排气选择系统

    公开(公告)号：JP2005231626A

    公开(公告)日：2005-09-02

    申请号：JP2005146677

    申请日：2005-05-19

    Applicant: Bell Helicopter Textron Inc ,  ベル、ヘリカプタ、テクストロン、インク

    Inventor： JENKINS JULIAN L ,  WOOD TOMMIE L ,  BRAND ALBERT G

    IPC: B64D33/04 ,  F02K1/28

    CPC classification number: F02K1/28 ,  Y10S239/07

    Abstract: PROBLEM TO BE SOLVED: To deflect the exhaust gas stream of an aircraft engine from an aircraft's fuselage structure.
    SOLUTION: Nozzles (3, 5) for discharging high velocity air are positioned on each side of an exit of an aircraft engine duct (1) exit. High velocity air is discharged tangential to an outer surface of each nozzle (3, 5) and follows the contour thereof. Each nozzle (3, 5) is positioned so that when the high velocity air separates from the outer surface of the respective nozzles (3, 5), it flows outwardly relative to the aircraft's fuselage structure. The high velocity air from the nozzle (3) closest to the aircraft's fuselage structure impinges on the exhaust gas stream (35, 57), deflecting the stream in a direction (43) away from the fuselage. The high velocity air from the nozzle (5) furthest from the fuselage creates a low pressure area which deflects the exhaust gas stream (35, 37) away from the fuselage. In combination, the two nozzles (3, 5) deflect the exhaust gas stream (35, 37) away from the fuselage to some extent.
    COPYRIGHT: (C)2005,JPO&NCIPI

    Abstract translation: 要解决的问题：使飞机发动机的废气流从飞行器的机身结构偏转。

    解决方案：用于排出高速空气的喷嘴（3,5）位于飞机发动机导管（1）出口的出口的每一侧。 高速空气与每个喷嘴（3,5）的外表面相切地排出并且遵循其轮廓。 每个喷嘴（3,5）被定位成使得当高速空气与相应喷嘴（3,5）的外表面分离时，其相对于飞行器的机身结构向外流动。 来自最靠近飞机机身结构的喷嘴（3）的高速空气撞击排气流（35,57），使流沿机身偏离方向（43）偏转。 距离机身最远的喷嘴（5）的高速空气产生使排气流（35,37）远离机身偏转的低压区域。 两个喷嘴（3,5）组合地使排气流（35,37）偏离机身一定程度。 版权所有（C）2005，JPO＆NCIPI

    VIBRATION ABSORBING DEVICE
    10.
    发明专利
    VIBRATION ABSORBING DEVICE 失效

    公开(公告)号：JPH109341A

    公开(公告)日：1998-01-13

    申请号：JP35875496

    申请日：1996-12-27

    Applicant: BELL HELICOPTER TEXTRON INC

    Inventor： SEHGAL AJAY ,  COVINGTON CECIL E ,  YUCE MITHAT ,  MARSHALL BRYAN W

    IPC: B64C27/51 ,  B64C27/00 ,  F16F15/12 ,  F16F15/133 ,  F16F15/121

    Abstract: PROBLEM TO BE SOLVED: To provide a vibration absorbing device with which the weight compensates the vibration effectively in all five directions, i.e., ahead and aside in the plane, vertically, and in the pitching and rolling directions. SOLUTION: This vibration absorbing device concerned 20 is equipped with a mass member borne in the stationary state by intra-plane springs 36 at a certain spacing from a base plate 22, top plate, and spring holding structure 45. The mass member has a buffer surface contacting with a motion restrictor 30 for the base plate. The mass member, base plate, and top plate can be equipped with a passage 24 passing the axis 26. Adjustment of this vibration absorbing device can be made by varying the intra-plane spring (s), the degree of preliminary compression, and the size of the mass achieved through addition or removal of a mass adjusting weight.

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