公开(公告)号：US20160169309A1

公开(公告)日：2016-06-16

申请号：US14945660

申请日：2015-11-19

Applicant: MESSIER-BUGATTI-DOWTY

Inventor： Jean-Baptiste ROBIN ,  Robin LUCIENNE

IPC: F16D65/74 ,  B64C25/44

CPC classification number: F16D65/74 ,  B64C25/42 ,  B64C25/44 ,  F16D55/226 ,  F16D55/40 ,  F16D65/18 ,  F16D65/186 ,  F16D65/38 ,  F16D65/44 ,  F16D65/48 ,  F16D65/54 ,  F16D2121/02 ,  F16D2125/04 ,  F16D2125/06 ,  F16D2129/02

Abstract: The invention relates to a brake actuator for an aircraft hydraulic brake, which is intended to be added into one of the cavities of a brake ring, the actuator comprising a liner (1) designed to be housed sealingly in the cavity of the ring, a piston (3) mounted to slide sealingly in the liner along an axis of sliding (X) so as to apply a braking force on friction pads when a fluid is introduced under pressure into the cavity, and having a determined operational travel, a wear compensation device (10) which defines a position to which the piston retreats into the liner by means of a mobile stop (11) that can be moved forward by the piston as a braking force is applied, and an elastic return member (16) returning the piston towards the retracted position bearing against the mobile stop. According to the invention, the mobile stop is reduced to a friction member rubbing against the liner, such that one of the faces of the friction member serves as a stop defining the retracted position of the piston, and the other of the faces serves as a support for the elastic return member, the elastic member having, when compressed, a sufficient increase in force in order to be able to push back the mobile stop in the event that the piston is not in contact with the friction pads while its operational travel is already exhausted.

Abstract translation: 本发明涉及一种用于飞行器液压制动器的制动致动器，其旨在被添加到制动环的一个空腔中，所述致动器包括设计成密封地容纳在所述环的空腔中的衬套（1） 活塞（3），其安装成沿着滑动轴线（X）密封地滑动在所述衬套中，以便当流体在压力下被引入所述空腔中时，在摩擦垫上施加制动力，并且具有确定的操作行程，磨损补偿 装置（10），其通过可移动的止动件（11）限定活塞后退到所述衬套中的位置，所述移动止动件（11）作为制动力被所述活塞向前移动;以及弹性返回构件（16） 活塞朝着缩回位置抵靠移动止挡。 根据本发明，移动式止动件被还原成摩擦件抵靠衬套，使得摩擦构件的一个面用作限定活塞缩回位置的止挡件，另一个面部用作 支撑弹性返回构件，弹性构件在被压缩时具有足够的力的增加，以便在活塞不与摩擦垫接触的情况下能够推回移动止挡件，同时其操作行程为 已经耗尽

公开(公告)号：US20160137295A1

公开(公告)日：2016-05-19

申请号：US14937145

申请日：2015-11-10

Applicant: Messier-Dowty Limited ,  Messier-Bugatti-Dowty

Inventor： David Bond ,  Melvin Ekbote ,  Mayur Kallabettu ,  Gerard Balducci

IPC: B64C25/30 ,  B64C25/24

CPC classification number: B64C25/30 ,  B64C25/24 ,  B64C25/26

Abstract: An aircraft landing gear assembly includes a lock link and a rotary electromechanical actuator which includes motor and gearbox unit arranged to move a pawl into contact with the lock link to break the lock link. A release mechanism is provided to enable the lock link to be made in the event of the motor and gearbox unit jamming.

Abstract translation: 飞机起落架组件包括锁定连杆和旋转机电致动器，其包括马达和齿轮箱单元，该马达和齿轮箱单元布置成将棘爪移动到与锁定连杆接触以断开锁定连杆。 提供释放机构，以在电动机和变速箱单元卡住的情况下实现锁定连杆。

公开(公告)号：US20160091522A1

公开(公告)日：2016-03-31

申请号：US14862227

申请日：2015-09-23

Applicant: MESSIER-BUGATTI-DOWTY

Inventor： Joel ZABULON ,  David FRANK

IPC: G01P3/44 ,  G01R19/00

CPC classification number: G01P3/44 ,  G01P3/487 ,  G01R19/0084

Abstract: The invention relates to a measurement device for measuring the rotational speed of a vehicle wheel, the measurement device comprising a body (22) incorporating: a rotor (30) which can be rotated by the wheel and on which at least one permanent magnet (33) is mounted; a stator (31) comprising a winding (36) generating a measurement voltage when the wheel (2) and therefore the permanent magnet turn, the measurement voltage being indicative of the rotational speed of the wheel; an electronic board (32) comprising processing means for processing the measurement voltage; power supply means designed to generate, from the measurement voltage, a power supply voltage intended to power the electronic board.

Abstract translation: 本发明涉及一种用于测量车轮转速的测量装置，该测量装置包括主体（22），该主体包括：转子（30），该转子可由车轮旋转，并且至少一个永磁体 ）安装; 定子（31）包括绕轮（36），所述绕组（36）在所述轮（2）产生测量电压，因此所述永磁体转动时，所述测量电压指示所述车轮的转速; 电子板（32），包括用于处理测量电压的处理装置; 电源装置被设计成从测量电压产生旨在为电子板供电的电源电压。

公开(公告)号：US20160090173A1

公开(公告)日：2016-03-31

申请号：US14857081

申请日：2015-09-17

Applicant: MESSIER-BUGATTI-DOWTY

Inventor： Joel ZABULON ,  David FRANK

IPC: B64C25/34 ,  G01P3/44 ,  G01P3/36 ,  B64D43/00

CPC classification number: B64C25/34 ,  B60T8/00 ,  B60T8/329 ,  B64C25/36 ,  B64D43/00 ,  F16C19/386 ,  F16C41/00 ,  F16C41/007 ,  G01P3/36 ,  G01P3/44

Abstract: An aircraft landing gear comprising an axle (3) intended to receive a wheel (4) comprising a rim (6) mounted to rotate on the axle (3) by means of at least one rolling bearing (8). The rolling bearing (8) comprises an inner ring (11) mounted around the axle (3) and an outer ring (12) rotationally secured to the rim (6) of the wheel (4). The landing gear further comprising a measurement device (21) intended to perform measurements of at least one operating parameter of the landing gear. The measurement device (21) is incorporated in the rolling bearing (8) by being secured to one of the inner or outer rings of the rolling bearing (8).

Abstract translation: 一种飞机起落架，包括用于接纳轮（4）的轴（3），所述轮（3）包括通过至少一个滚动轴承（8）安装成在轴（3）上旋转的轮缘（6）。 滚动轴承（8）包括围绕轴（3）安装的内环（11）和旋转地固定到轮（4）的轮辋（6）的外圈（12）。 起落架还包括用于执行起落架的至少一个操作参数的测量的测量装置（21）。 测量装置（21）通过固定在滚动轴承（8）的内圈或外圈中的一个上而结合在滚动轴承（8）中。

公开(公告)号：US20160084681A1

公开(公告)日：2016-03-24

申请号：US14849893

申请日：2015-09-10

Applicant: MESSIER-BUGATTI-DOWTY

Inventor： Gary ATAMAN

IPC: G01D11/24 ,  B64C25/00 ,  G01D5/12

CPC classification number: G01D11/24 ,  B64C25/001 ,  G01D5/12 ,  G01D11/245 ,  G01D11/30

Abstract: Sensor (1) comprising: a casing (2) delimiting an internal volume (3) and having a passage (31) between this internal volume and a first external zone (Z1) external to the casing; a moving part (4) able to move inside the said internal volume (3); detection means (5) for detecting a movement of the said moving part (4) comprising a detection portion (51) extending in the passage (31), and having a groove (52) open to the outside of the detection portion (51), this groove (52) extending between the said first external zone (Z1) external to the casing and the said internal volume (3) internal to the casing. The sensor (1) comprises first sealing means (14) positioned around the detection portion (51) inside the passage (31), these first sealing means (14) being arranged in such a way as to prevent fluid from passing between the internal volume (3) and the first external zone (Z1) via said groove (52).

Abstract translation: 传感器（1）包括：外壳（2），其限定内部容积（3）并且在该内部容积与壳体外部的第一外部区域（Z1）之间具有通道（31） 能够在所述内部容积（3）内移动的移动部件（4）; 用于检测所述移动部件（4）的运动的检测装置（5），包括在所述通道（31）中延伸的检测部分（51），并且具有向所述检测部分（51）的外部开口的凹槽（52） ，所述槽（52）在所述壳体外部的所述第一外部区域（Z1）与所述壳体内部的所述内部容积（3）之间延伸。 传感器（1）包括位于通道（31）内的检测部分（51）周围的第一密封装置（14），这些第一密封装置（14）被布置成防止流体在内部容积 （3）和所述第一外部区域（Z1）。

公开(公告)号：US20160016657A1

公开(公告)日：2016-01-21

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.

Abstract translation: 本发明涉及一种飞机起落架，其旨在安装成能够在展开位置和缩回位置之间在飞机上移动，底架包括由固定到起落架上的支撑件（4）承载的滚子（1），同时 能够相对于其移动，其特征在于，支撑件枢转地安装在起落架上。

公开(公告)号：US20150375855A1

公开(公告)日：2015-12-31

申请号：US14746953

申请日：2015-06-23

Applicant: MESSIER-BUGATTI-DOWTY

Inventor： Sylvain JABER ,  Raffi CEKIC

IPC: B64C25/40 ,  H02P3/22

CPC classification number: B64C25/405 ,  H02P3/12 ,  H02P3/22 ,  H02P9/008 ,  Y02T50/823

Abstract: The invention relates to a method for managing an electric motor (6) intended to drive rotationally a wheel (4) of an aircraft (1), the method comprising the step of short-circuiting the phases of the electric motor (6) when the aircraft (1) is in a period of deactivation of the motor (6) during which it is envisaged not using the electric motor (6).

Abstract translation: 本发明涉及一种用于管理旨在旋转地驱动飞行器（1）的车轮（4）的电动机（6）的方法，所述方法包括以下步骤：当电动机（6）的相位短路时， 飞机（1）处于停止使用电动机（6）的期间，在此期间，设想不使用电动机（6）。

公开(公告)号：US20150337915A1

公开(公告)日：2015-11-26

申请号：US14691825

申请日：2015-04-21

Applicant: MESSIER-BUGATTI-DOWTY

Inventor： Pierre CHAMBARD ,  Come DORGE ,  Richard MASSON ,  Jean-Baptiste VANEY

IPC: F16D55/42 ,  B64C25/44

CPC classification number: F16D55/42 ,  B64C25/44 ,  F16D55/24 ,  F16D55/36 ,  F16D2055/0058 ,  F16D2055/0095

Abstract: The invention relates to a disc brake for an aircraft wheel, comprising friction discs (20,30), including rotor discs and stator discs, a structure comprising a torsion tube (11) on which the discs are fitted, a rear plate (12) which is located at one end of the tube, and a support (13) for braking actuators (14,15) at another end of the tube, the actuators being able to be selectively activated in order to apply a pressing force to the discs. According to the invention, the discs are separated into two groups, including a first group (20) which can be used alone for taxiing braking operations, and a second group (30) which can be used alone or in conjunction with the first group for take-off/landing braking operations.

Abstract translation: 本发明涉及一种用于飞行器轮的盘式制动器，包括摩擦盘（20,30），包括转子盘和定子盘，包括其上安装有盘的扭力管（11）的结构，后板（12） 其位于所述管的一端，以及用于在所述管的另一端制动致动器（14,15）的支撑件（13），所述致动器能够被选择性地启动以向所述盘施加按压力。 根据本发明，盘被分成两组，包括可以单独用于滑行制动操作的第一组（20），以及可以单独使用或与第一组一起使用的第二组（30） 起飞/着陆制动操作。

公开(公告)号：US20150314860A1

公开(公告)日：2015-11-05

申请号：US14646796

申请日：2013-11-29

Applicant: MESSIER-BUGATTI-DOWTY

Inventor： Philippe HENRION ,  Dominique DUCOS ,  Nicolas NGUYEN

IPC: B64C25/20

CPC classification number: B64C25/20 ,  B64C25/22 ,  B64C25/26

Abstract: The invention relates to aircraft landing gear comprising: a leg (12) for hinging to a structure of the aircraft so as to be movable between a deployed position and a retracted position, a main brace (15), a secondary brace (20), and an unlocking actuator (30) having a first end coupled to the secondary brace and controllable for causing its links to move out of alignment against the action of the resilient member during retraction or deployment of the landing gear. According to the invention, the unlocking actuator is of the double-acting type and the landing gear includes coupling means (31, 33) for coupling to a second end of the unlocking actuator, which means ensure movement of said second end relative to the leg so that, for a given action, the unlocking actuator tends to break the alignment of the links when the landing gear is in one of its positions and tends to confirm said alignment when the landing gear is in its other position.

Abstract translation: 本发明涉及飞机起落架，其包括：用于铰接到飞行器的结构以便在展开位置和缩回位置之间移动的支腿（12），主支架（15），辅助支架（20） 以及解锁致动器（30），其具有联接到所述辅助支架的第一端，并且可控制地使其连杆在所述起落架的缩回或展开期间抵抗所述弹性构件的作用移动离开对准。 根据本发明，解锁致动器是双作用型的，并且起落架包括联接装置（31,33），用于联接到解锁致动器的第二端，这意味着确保所述第二端相对于腿的运动 使得对于给定的动作，当起落架处于其一个位置时，解锁致动器倾向于破坏连杆的对准，并且当起落架处于其另一位置时倾向于确认所述对准。

公开(公告)号：US09169002B2

公开(公告)日：2015-10-27

申请号：US13779397

申请日：2013-02-27

Applicant: MESSIER-BUGATTI-DOWTY

Inventor： Michael Benmoussa ,  David Poiret ,  Jerome Fraval

IPC: B64C25/50 ,  B64C19/00 ,  G05D1/00

CPC classification number: B64C19/00 ,  B64C25/50 ,  G05D1/0083

Abstract: A method of managing a steering command for a steerable portion 3 of nose landing gear 2 of an aircraft 1. The method implements servo-control to servo-control of a steering actuator 6 to an angle position setpoint θset for the steerable portion 3. The servo-control includes calculating an error ε by subtracting a reference angle θest from the angle position setpoint θset. The reference angle θest is an angle determined by calculation as a function of a longitudinal speed Vlong and a yaw rate τ of the aircraft 1.

Abstract translation: 管理飞机1的起落架2的可转向部分3的转向命令的方法。该方法实现伺服控制以将转向致动器6的伺服控制转换成角度位置设定点;为可转向部分3设定 伺服控制包括计算误差＆egr; 通过从角度位置设定点＆thetas; set中减去参考角度＆amp; est; est。 参考角度＆amp; est;是通过作为飞行器1的纵向速度Vlong和横摆角速度τ的函数的计算确定的角度。