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    DOOR FOR A TILTROTOR PROPROTOR PYLON
    2.
    发明公开
    DOOR FOR A TILTROTOR PROPROTOR PYLON 审中-公开

    公开(公告)号：EP3549861A1

    公开(公告)日：2019-10-09

    申请号：EP18179179.9

    申请日：2018-06-21

    Applicant: Bell Helicopter Textron Inc.

    Inventor： IVANS, Steven Ray ,  GIBSON, Terry Lee

    IPC: B64C29/00 ,  B64D29/06 ,  B64C7/00 ,  B64D7/00

    Abstract: The disclosure provides a blocking door (160) that is pivotally disposed on a fixed nacelle (137, 139) of a tiltrotor aircraft (101) for pivoting between a stowed position (S) when a proprotor pylon (115, 117) is in the substantially horizontal position and a protective blocking position (B) in front of the proprotor pylon (115, 117) when the proprotor pylon (115, 117) is positioned in the non-horizontal position. In other aspects, there is provided a method of reducing infrared and/or radar signatures of rotorcraft with a rotatable proprotor (116, 118).

    ROTATING PROPROTOR ARRANGEMENT FOR A TILTROTOR AIRCRAFT
    3.
    发明公开
    ROTATING PROPROTOR ARRANGEMENT FOR A TILTROTOR AIRCRAFT 审中-公开
    转向架飞行器的旋转传动装置

    公开(公告)号：EP3299290A1

    公开(公告)日：2018-03-28

    申请号：EP16206787.0

    申请日：2016-12-23

    Applicant: Bell Helicopter Textron Inc.

    Inventor： IVANS, Steven Ray ,  ROSS, Brent Chadwick

    IPC: B64C29/00

    CPC classification number: B64C29/0033 ,  B64C3/18 ,  B64C39/024 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/02 ,  B64D33/02 ,  B64D33/04 ,  B64D35/04 ,  B64D35/08 ,  F16H1/203 ,  F16H35/008

    Abstract: A propulsion system includes an engine (116) disposed within a fuselage (102), a first gearbox (130) coupled to the engine (116), a wing member having an upper wing skin and torque box formed by a first rib (172), a second rib (174), a first spar (176) and second spar (178), a drive shaft (132) coupled to the first gearbox (126) and disposed within the wing member, a second gear box (134) coupled to the drive shaft (132) and disposed outboard from the second rib (174) or inboard from the first rib (172), and a rotatable proprotor (106) coupled to the second gear box (134). The rotatable proprotor (106) includes a plurality of rotor blades (114), a rotor mast (140) having a mast axis of rotation (180), and a proprotor gearbox (136) coupled to the rotor mast (140). The proprotor gearbox (136) is rotatable about a conversion axis (156), which intersects with the mast axis of rotation (180) at a point within a central region of the torque box and above the upper wing skin.

    Abstract translation: 推进系统包括布置在机身（102）内的发动机（116），联接到发动机（116）的第一变速箱（130），具有上翼蒙皮和扭矩箱的翼构件，所述上翼蒙皮和扭矩箱由第一肋（172） ，第二肋（174），第一翼梁（176）和第二翼梁（178），联接到第一变速箱（126）并设置在翼构件内的驱动轴（132），联接第二齿轮箱 （132）并且设置在第二肋（174）的外侧或第一肋（172）的内侧，以及联接到第二齿轮箱（134）的可旋转的转速传感器（106）。 可旋转的旋翼桨叶（106）包括多个转子叶片（114），具有井架旋转轴线（180）的转子井架（140）以及联接到转子井架（140）的旋翼桨传动装置（136）。 推进器变速箱136可绕转换轴线156旋转，所述转换轴线156在转矩箱的中心区域内并且位于上机翼蒙皮上方的点处与转动轴线180相交。

    MODULAR PAYLOAD SYSTEMS FOR AIRCRAFT
    5.
    发明公开
    MODULAR PAYLOAD SYSTEMS FOR AIRCRAFT 审中-公开
    用于飞机的模块化有效载荷系统

    公开(公告)号：EP3296193A1

    公开(公告)日：2018-03-21

    申请号：EP17192070.5

    申请日：2017-09-20

    Applicant: Bell Helicopter Textron Inc.

    Inventor： IVANS, Steven Ray ,  ROSS, Brent Chadwick

    IPC: B64C1/00 ,  B64D7/00 ,  B64D1/04

    Abstract: A modular payload system (300) for an aircraft (10; 300; 400) includes a modular bay (38; 106, 108, 110; 202; 302) recessed within the aircraft. The modular bay includes a modular bay interface (206, 246). The modular payload system includes a plurality of payload modules (118; 208, 210, 212; 308) each having a respective function and a payload interface (230, 232, 234) adapted to connect to at least a portion of the modular bay interface. The plurality of payload modules are interchangeably insertable into the modular bay to enable the modular bay to support the functions of the plurality of payload modules.

    Abstract translation: 用于飞机（10; 300; 400）的模块化有效载荷系统（300）包括凹进飞机内的模块化隔间（38; 106,108,110; 202; 302）。 模块化托架包括模块化托架接口（206,246）。 所述模块化有效载荷系统包括多个有效载荷模块（118; 208,210,212; 308），每个有效载荷模块具有相应的功能和有效载荷接口（230,232,234），所述有效载荷接口适于连接到所述模块化托架接口 。 多个有效载荷模块可互换地插入到模块化托架中，以使模块化托架能够支持多个有效载荷模块的功能。

    WING EXTENSION WINGLETS FOR TILTROTOR AIRCRAFT
    9.
    发明公开
    WING EXTENSION WINGLETS FOR TILTROTOR AIRCRAFT 审中-公开
    WING延伸翼的TILTROTOR AIRCRAFT

    公开(公告)号：EP3296202A1

    公开(公告)日：2018-03-21

    申请号：EP17191927.7

    申请日：2017-09-19

    Applicant: Bell Helicopter Textron Inc.

    Inventor： ANDERSON, Adam Bryant ,  IVANS, Steven Ray ,  CHAVEZ, Jeremy Robert

    IPC: B64C29/00 ,  B64C23/06

    Abstract: A pylon assembly (100) for a tiltrotor aircraft (10) includes a rotor assembly (102) operable to rotate between a generally vertical orientation, in a VTOL flight mode, and a generally horizontal orientation, in a forward flight mode, and having an intermediate orientation therebetween, in a conversion flight mode. The rotor assembly (102) includes a proprotor (112) operable to produce a slipstream. A wing extension (104), positioned outboard of the rotor assembly (102), has a minimal dimension and an outboard end. A winglet (106) is coupled to the outboard end of the wing extension (104) and has a minimal dimension. The wing extension (104) and the winglet (106) are operable to rotate generally with the rotor assembly (102) such that the minimal dimensions of the wing extension (104) and the winglet (106) remain in the slipstream of the proprotor.

    Abstract translation: 用于倾转旋翼飞机（10）的挂架组件（100）包括转子组件（102），该转子组件可操作以在垂直飞行模式下在大致垂直定向和垂直定向之间旋转，并且具有 它们之间的中间取向，处于转换飞行模式。 转子组件（102）包括可操作以产生滑流的推进器（112）。 位于转子组件（102）外侧的机翼延伸部（104）具有最小尺寸和外侧端。 小翼（106）联接到机翼延伸部（104）的外侧端并具有最小尺寸。 机翼延伸部（104）和小翼（106）可操作以大致与转子组件（102）一起旋转，使得机翼延伸部（104）和小翼（106）的最小尺寸保持在旋翼飞行器的滑流中。

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