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    Method for fixing an actuator for rotatably driving a wheel of an aircraft
    1.
    发明授权
    Method for fixing an actuator for rotatably driving a wheel of an aircraft 有权

    公开(公告)号：US10399672B2

    公开(公告)日：2019-09-03

    申请号：US14945552

    申请日：2015-11-19

    Applicant: MESSIER-BUGATTI-DOWTY

    Inventor： Frederic Martin

    IPC: B64C25/34 ,  B64C25/40 ,  B64C25/44 ,  F16H1/10

    Abstract: A method for fixing to an aircraft landing gear (1) at least one actuator (30) for rotatably driving a wheel (3) which is rotatably mounted on an axle (2) of the landing gear, the wheel being associated with a brake (5). The brake has an actuator carrier (8) which carries brake actuators, the actuator carrier being fitted onto the axle and stopped in terms of rotation by an obstacle (12) which is fixedly joined to the landing gear and which is introduced into one of several stop holes (11) of the actuator carrier. The drive actuator is fixedly joined to the actuator carrier in the region of a stop hole of the actuator carrier which does not receive the obstacle.

    Drive roller
    2.
    发明授权
    Drive roller 有权

    公开(公告)号：US10309499B2

    公开(公告)日：2019-06-04

    申请号：US15149657

    申请日：2016-05-09

    Applicant: MESSIER-BUGATTI-DOWTY

    Inventor： Norbert Lartigue

    IPC: F16H13/04 ,  B64C25/40 ,  F16H55/32

    Abstract: A roller (1) having a rigid reinforcement (4) defining a hub (5) for rotation of the roller about an axis of rotation X and a plurality of bars (6) regularly arranged around the hub (5) and extending parallel to the axis X. The roller further has bushings (10), each engaged on a respective one of the bars (6) and each comprising an outer rigid ring (11) surrounding a bushing body (12) made of deformable material.

    Control system comprising a control rod
    3.
    发明授权
    Control system comprising a control rod 有权

    公开(公告)号：US10131420B2

    公开(公告)日：2018-11-20

    申请号：US15012339

    申请日：2016-02-01

    Applicant: MESSIER-BUGATTI-DOWTY

    Inventor： Gary Ataman

    IPC: F01B31/12 ,  B64C25/22 ,  F15B15/28 ,  F16H21/04 ,  F16H21/44 ,  F16H51/00 ,  F16J15/18 ,  F16J15/50 ,  F16J15/52

    Abstract: Control system (1) comprising a control rod (5) extending between a first zone (2) situated in a hydraulic chamber delimited by a chamber wall (3) and a second zone (4) situated outside the hydraulic chamber. The control system (1) further comprising a seal (6) arranged around and against this control rod (5) to oppose the passage of fluid between the first and second zones (2, 4). The system further comprises a guide piece (7) assembled removably with respect to the chamber wall (3), the seal (6) is assembled inside the guide piece (7) so as to allow relative movement of the rod (5) with respect to the guide piece (7) while at the same time achieving sealing between the first and second zones (2, 4).

    Aircraft undercarriage with shimmy-damping means
    4.
    发明授权
    Aircraft undercarriage with shimmy-damping means 有权

    公开(公告)号：US10005547B2

    公开(公告)日：2018-06-26

    申请号：US15151593

    申请日：2016-05-11

    Applicant: MESSIER-BUGATTI-DOWTY

    Inventor： Jerome Fraval ,  David Frank

    IPC: B64C25/58 ,  B64C25/50 ,  B64C25/34 ,  F16F9/12 ,  F16F9/18

    CPC classification number: B64C25/505 ,  B64C25/34 ,  B64C25/58 ,  F16F9/12 ,  F16F9/182

    Abstract: The invention relates to an aircraft undercarriage comprising: a strut (1) for connecting to the aircraft, a slide rod (3) slidably engaged in leaktight manner in the strut via the bottom opening, which rod carries at least one wheel at its bottom end, a diaphragm (7) carried by a support (8) attached to the top wall of the strut to cooperate in leaktight manner with an inside wall of the slide rod so as to define a first chamber (C1) under the diaphragm inside the rod and completely filled with hydraulic fluid, and a second chamber (C2) above the diaphragm and partially filled with hydraulic fluid, a throttle needle (10) secured to the slide rod and penetrating into a calibrated orifice (12) in the diaphragm so as to define a calibrated fluid passage between the first and second chambers, and angular connection means for imposing an angular position on the slide rod relative to the strut. According to the invention, the undercarriage includes at least one vane (20) fastened to the end of the throttle needle in order to extend inside a portion of the second chamber that is filled with hydraulic fluid.

    Mechanical actuator with a hydraulic damper device
    5.
    发明授权
    Mechanical actuator with a hydraulic damper device 有权

    公开(公告)号：US09969233B2

    公开(公告)日：2018-05-15

    申请号：US14075642

    申请日：2013-11-08

    Applicant: MESSIER-BUGATTI-DOWTY

    Inventor： Ludovic Leglize

    IPC: B60G15/12 ,  B64C25/22 ,  F16H25/20 ,  B64C25/18

    CPC classification number: B60G15/12 ,  B64C25/18 ,  B64C25/22 ,  F16H25/20 ,  F16H25/2021 ,  Y10T74/18648

    Abstract: The invention relates to an actuator comprising a cylinder (1) in which a rod (2) is mounted to slide, the actuator having a screw (8) extending inside the rod to co-operate with a nut (7) secured to the rod, the screw being driven in rotation by a motor (10), the actuator being characterized in that a hydraulic chamber (CH) filled with hydraulic fluid is arranged inside the actuator by means of a floating piston (20) sliding in sealed manner against the rod inside of the actuator, the hydraulic chamber being in fluid flow communication with an accumulator (21) via a solenoid valve (22) that is controllable between a closed state in which the chamber is isolated from the accumulator, and a fluid-passing state in which the hydraulic chamber and the accumulator are in communication, calibrated resistance being exerted against the passage of fluid from the chamber towards the accumulator.

    Aircraft landing gear provided with an adjustable roller
    6.
    发明授权
    Aircraft landing gear provided with an adjustable roller 有权

    公开(公告)号：US09834302B2

    公开(公告)日：2017-12-05

    申请号：US14774055

    申请日：2014-03-12

    Applicant: MESSIER-BUGATTI-DOWTY

    Inventor： Domenico La Commara ,  Thibault Faure

    IPC: B64C25/26

    CPC classification number: B64C25/26

    Abstract: The invention relates to an aircraft undercarriage intended to be mounted so as to be able to move on the aircraft between a deployed position and a retracted position, the undercarriage comprising a roller (1) carried by a support (4) secured to the undercarriage while being able to be moved with respect thereto, characterised in that the support is mounted pivotally on the undercarriage.

    Electromechanical actuator for a brake
    9.
    发明授权
    Electromechanical actuator for a brake 有权
    用于制动器的机电致动器

    公开(公告)号：US09566970B2

    公开(公告)日：2017-02-14

    申请号：US14192036

    申请日：2014-02-27

    Applicant: MESSIER-BUGATTI-DOWTY

    Inventor： Nathanael Richard ,  Eric Evenor ,  Franck Selles

    IPC: B60T13/74 ,  H02K7/06 ,  H02K7/116 ,  F16D65/16 ,  F16D65/18 ,  B64C25/44 ,  F16D66/00 ,  F16D121/24

    CPC classification number: B60T13/746 ,  B64C25/44 ,  F16D65/16 ,  F16D65/18 ,  F16D2066/005 ,  F16D2121/24 ,  H02K7/06 ,  H02K7/116 ,  H02K11/24 ,  H02K11/35

    Abstract: An electromechanical actuator for a vehicle brake, the actuator comprising first and second portions 8 and 9 that are separable. The first portion 8 includes an electric motor 5 and connection structure 15 for connecting the actuator to an external control structure 4. The second portion 9 including a slidable pusher 6, the second portion 9 also including measurement structure 21. The first portion 8 includes a first antenna 14 connected to the connection structure 15, and the second portion 9 includes a second antenna 22 connected to the measurement structure 21, the two antennas 14, 22 being arranged to be electromagnetically coupled together when the first portion 8 and the second portion 9 are coupled together, so as to enable electrical signals to be transferred between the measurement structure 21 and the connection structure 15.

    Abstract translation: 一种用于车辆制动器的机电致动器，致动器包括可分离的第一和第二部分8和9。 第一部分8包括电动机5和用于将致动器连接到外部控制结构4的连接结构15.第二部分9包括可滑动的推动器6，第二部分9还包括测量结构21.第一部分8包括 第一天线14连接到连接结构15，并且第二部分9包括连接到测量结构21的第二天线22，两个天线14,22布置成当第一部分8和第二部分9电磁耦合在一起时 耦合在一起，以便能够在测量结构21和连接结构15之间传输电信号。

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