中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

52 records (took 0.041 seconds)

    WING EXTENSION CONTROL SURFACE
    21.
    发明申请
    WING EXTENSION CONTROL SURFACE 审中-公开
    WING扩展控制面

    公开(公告)号：WO2010104509A1

    公开(公告)日：2010-09-16

    申请号：PCT/US2009/036889

    申请日：2009-03-12

    Applicant: BELL HELICOPTER TEXTRON INC. ,  COLLINS, Bob ,  STAMPS, Frank, B. ,  CORRINGAN, John, J. III ,  DREIER, Mark, E.

    Inventor： COLLINS, Bob ,  STAMPS, Frank, B. ,  CORRINGAN, John, J. III ,  DREIER, Mark, E.

    IPC: B64C27/22

    CPC classification number: B64C29/0033

    Abstract: A tiltrotor aircraft includes a rotatable nacelle that supports a rotor assembly and is pivotally attached to the aircraft's fuselage. A wing extension attaches to an outboard section of the nacelle. The wing extension provides additional yaw control during helicopter mode and additional lift during airplane mode. A method for controlling at least a portion of yaw movement includes positioning the rotor assembly in helicopter mode, creating rotor wash with the rotor assembly, and pivotally rotating the wing extension in the rotor wash.

    Abstract translation: 倾斜旋转飞机包括支撑转子组件并可枢转地附接到飞机机身的可旋转机舱。 机翼延伸部连接到机舱的外侧部分。 机翼延伸在直升机模式下提供额外的偏航控制，并在飞机模式期间提供额外的提升。 用于控制偏转运动的至少一部分的方法包括将转子组件定位成直升机模式，与转子组件一起产生转子清洗，以及在转子清洗器中枢转地旋转机翼延伸部。

    STIFF-IN-PLANE ROTOR CONFIGURATION
    22.
    发明申请
    STIFF-IN-PLANE ROTOR CONFIGURATION 审中-公开
    棘轮式转子配置

    公开(公告)号：WO2010082936A1

    公开(公告)日：2010-07-22

    申请号：PCT/US2009/031381

    申请日：2009-01-19

    Applicant: BELL HELICOPTER TEXTRON INC. ,  STAMPS, Frank, B. ,  TISDALE, Patrick, R. ,  DONOVAN, Tom ,  RAUBER, Richard, E.

    Inventor： STAMPS, Frank, B. ,  TISDALE, Patrick, R. ,  DONOVAN, Tom ,  RAUBER, Richard, E.

    IPC: B64C27/48

    CPC classification number: B64C27/35 ,  B64C27/32 ,  B64C27/33 ,  B64C27/39 ,  B64C27/48

    Abstract: A rotor assembly for a rotary-wing aircraft, the rotor having a central hub assembly with a flexure-type, twist-shank yoke with multiple arms, each arm being adapted for a rotor blade to be mounted thereto. The arms provide for pitch changes of blades attached to the yoke through twisting of portions of the arms about a corresponding pitch axis. An inboard pitch bearing associated with each arm is attached to the hub assembly and allows for rotation of the attached blade about the pitch axis, the inboard pitch bearing also allowing for out-of-plane motion of the arm relative to the hub assembly about a flapping axis. An outboard pitch bearing associated with each arm is attached to the associated arm a selected distance from the inboard pitch bearing and allows for rotation of the attached blade about the pitch axis.

    Abstract translation: 一种用于旋转翼飞行器的转子组件，该转子具有中心轮毂组件，其具有带有多个臂的挠曲型扭转柄轭，每个臂适于安装在其上的转子叶片。 臂通过扭转相应的俯仰轴线的臂的部分来提供附接到轭的叶片的桨距变化。 与每个臂相关联的内侧变桨轴承附接到轮毂组件并且允许所附接的叶片围绕俯仰轴线旋转，内侧变桨轴承还允许臂相对于轮毂组件的平面外运动绕一个 拍动轴。 与每个臂相关联的外侧变桨轴承从相对于内侧变桨轴承的选定距离附接到相关联的臂，并且允许所附接的叶片围绕桨距轴线旋转。

    YOKE AND BEARING FITTING ASSEMBLY FOR ROTORS
    23.
    发明申请
    YOKE AND BEARING FITTING ASSEMBLY FOR ROTORS 审中-公开
    转子和轴承配件组装

    公开(公告)号：WO2010082935A1

    公开(公告)日：2010-07-22

    申请号：PCT/US2009/031378

    申请日：2009-01-19

    Applicant: BELL HELICOPTER TEXTRON INC. ,  STAMPS, Frank, B. ,  TISDALE, Patrick, R. ,  CAMPBELL, Thomas, C. ,  RAUBER, Richard, E. ,  BRASWELL, James, L., Jr.

    Inventor： STAMPS, Frank, B. ,  TISDALE, Patrick, R. ,  CAMPBELL, Thomas, C. ,  RAUBER, Richard, E. ,  BRASWELL, James, L., Jr.

    IPC: B64C27/04

    CPC classification number: B64C27/33 ,  B64C27/32

    Abstract: A yoke and bearing fitting assembly for a multi-blade aircraft rotor is disclosed. The assembly has a yoke having arms extending generally radially from a central portion of the yoke, the arms each having opposing surfaces. An aperture is formed in each arm and extends between the surfaces. A bearing fitting has a body configured for insertion into the aperture of the yoke and has two rims protruding from a periphery of the body, the body also having a bearing mount adapted for mounting a pitch change bearing assembly to the yoke. Each rim abuts one of the surfaces of the associated yoke arm when the bearing fitting is installed within the aperture, so as to create clamping forces between the rims and the arm and the arm. The bearing fitting transmits forces from the pitch bearing assembly into the yoke.

    Abstract translation: 公开了一种用于多叶片飞行器转子的轭和轴承配件组件。 组件具有轭，其具有从轭的中心部分大致径向延伸的臂，每个臂具有相对的表面。 在每个臂中形成一个孔，并在表面之间延伸。 轴承配件具有构造成用于插入轭的孔中并具有从主体的周边突出的两个轮缘的主体，该主体还具有适于将变桨轴承组件安装到轭的轴承座。 当轴承配件安装在孔内时，每个轮辋邻接相关联的轭臂的一个表面，以便在轮辋与臂和臂之间产生夹紧力。 轴承配件将变桨轴承组件的力传递到轭架中。

    LEAD-LAG DAMPER FOR ROTOR HUBS
    24.
    发明申请
    LEAD-LAG DAMPER FOR ROTOR HUBS 审中-公开
    用于转子的LEAD-LAG阻尼器

    公开(公告)号：WO2009102324A1

    公开(公告)日：2009-08-20

    申请号：PCT/US2008/053742

    申请日：2008-02-12

    Applicant: BELL HELICOPTER TEXTRON INC. ,  STAMPS, Frank, B. ,  BRASWELL, James, L. ,  HAYNIE, David, A. ,  YUCE, Mithat

    Inventor： STAMPS, Frank, B. ,  BRASWELL, James, L. ,  HAYNIE, David, A. ,  YUCE, Mithat

    IPC: B64C27/51

    CPC classification number: B64C27/51 ,  F16F13/08

    Abstract: A lead-lag damper for a rotor assembly has a body mounted to either an inboard portion of a blade assembly or a fixed portion of the rotor assembly. A piston carried within the body is configured to allow for relative motion between the body and the piston. The piston defines opposing chambers within the body, the chambers being in fluid communication through a fluid passage. A link connects the piston to the other of the inboard portion of the blade assembly and the fixed portion of the rotor assembly, and the link engages a central portion of the piston. The piston acts on fluid in the chambers during relative motion between the piston and the body and causes fluid flow between the chambers through the fluid passage. Flow through the passage acts to damp lead-lag motion of the blade assembly relative to the fixed portion of the rotor assembly.

    Abstract translation: 用于转子组件的超前滞后阻尼器具有安装到叶片组件的内侧部分或转子组件的固定部分的主体。 承载在主体内的活塞构造成允许主体和活塞之间的相对运动。 活塞在体内限定相对的腔室，腔室通过流体通道流体连通。 连杆将活塞连接到叶片组件的内侧部分中的另一个和转子组件的固定部分，并且连杆接合活塞的中心部分。 在活塞和主体之间的相对运动期间，活塞作用在腔室中的流体上，并且通过流体通道引起腔室之间的流体流动。 通过通道的流动用于阻止叶片组件相对于转子组件的固定部分的牵引延迟运动。

    VIBRATION-ATTENUATING HARD-MOUNTED PYLON
    26.
    发明申请
    VIBRATION-ATTENUATING HARD-MOUNTED PYLON 审中-公开
    减振硬式安装的PYLON

    公开(公告)号：WO2008045073A3

    公开(公告)日：2008-11-27

    申请号：PCT/US2006039992

    申请日：2006-10-12

    Applicant: BELL HELICOPTER TEXTRON INC ,  SMITH MICHAEL R ,  STAMPS FRANK B

    Inventor： SMITH MICHAEL R ,  STAMPS FRANK B

    IPC: B64C27/04

    CPC classification number: B64C27/12 ,  B64C2027/002 ,  F16F7/10 ,  F16F15/02 ,  F16F2230/16

    Abstract: A preferred embodiment of a pylon has six pylon mounting links for mounting the pylon to an airframe. Each link is considered "near-rigid" and has a spherical-bearing rod-end on both ends such that the link can only transmit axial loads. At least one of the links has a mass carried within the link and selectively moveable by an actuating means along the axis of the link in an oscillatory manner for attenuating vibrations traveling axially through the link. The actuating means may be an electromechanical, hydraulic, pneumatic, or piezoelectric system. By mounting each link in a selected orientation relative to the other links, the actuating means may be operated in a manner that attenuates axial vibration that would otherwise be transmitted through the link and into the airframe.

    Abstract translation: 挂架的优选实施例具有六个挂架安装连杆，用于将挂架安装到机身上。 每条连杆都被认为是“接近刚性的”，并且在两端都有一个带有球面轴承的杆端，这样连杆只能传递轴向载荷。 至少一个连杆具有承载在连杆内的质量并且可以通过致动装置沿着连杆的轴线以摆动的方式选择性地移动，以衰减沿轴向行进通过连杆的振动。 致动装置可以是机电，液压，气动或压电系统。 通过将每个连杆相对于其他连杆以选定的方位安装，致动装置可以以衰减轴向振动的方式操作，否则该轴向振动将通过连杆传递到机身中。

Patent Agency Ranking