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公开(公告)号：US09802697B2
公开(公告)日：2017-10-31
申请号：US14877253
申请日：2015-10-07
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Pierre-Yves Liegeois , Thierry Blanpain , Edouard Campbell
CPC classification number: B64C25/505 , B64C25/34 , Y02T50/54
Abstract: The invention relates to an aircraft landing gear equipped with a steering device (7) for orienting the wheels (5), the steering device (7) comprising a body (8) in which is incorporated an electromechanical actuator (41) equipped with an electric motor (42). The landing gear is further equipped with damping means intended to limit the transmission of vibration from the wheel (5) to the rest of the landing gear (1) when the aircraft is on the ground. The body (8) of the steering device (7) is mounted with the ability to rotate with a limited amplitude of rotation. The damping means are mounted between the body (8) of the steering device (7) and the strut assembly (2) of the landing gear to damp the vibration between the body (8) of the steering device (7) and the strut assembly (2).
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公开(公告)号：US09739325B2
公开(公告)日：2017-08-22
申请号：US14945660
申请日：2015-11-19
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Jean-Baptiste Robin , Robin Lucienne
IPC: F16D65/54 , F16D65/74 , B64C25/42 , F16D55/40 , F16D65/44 , B64C25/44 , F16D65/38 , F16D121/02 , F16D55/226 , F16D65/48 , F16D65/18 , F16D125/04 , F16D125/06 , F16D129/02
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.
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公开(公告)号：US09718539B2
公开(公告)日：2017-08-01
申请号：US14857081
申请日：2015-09-17
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Joel Zabulon , David Frank
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).
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公开(公告)号：US09682770B2
公开(公告)日：2017-06-20
申请号：US14640440
申请日：2015-03-06
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Nicolas Mazarguil
IPC: B64C25/40
CPC classification number: B64C25/405 , Y02T50/823
Abstract: An aircraft landing gear including an axle and a wheel (5) that includes a rim (6) mounted to turn on the axle about a first rotation axis (X1), the landing gear further comprising an actuator (12) for driving the wheel (5) in rotation. The rim (6) includes obstacles (33) that project from a lateral face (F) of the rim and the driving actuator includes a lead screw (32) mounted to turn about a second rotation axis (X2) perpendicular to the first rotation axis (X1) and adapted to cooperate with the obstacles of the rim to drive the wheel in rotation.
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公开(公告)号：US09676473B2
公开(公告)日：2017-06-13
申请号：US14646796
申请日：2013-11-29
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Philippe Henrion , Dominique Ducos , Nicolas Nguyen
Abstract: Aircraft landing gear having 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 a double-acting type 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. The landing gear includes couplers (31, 33) for coupling to a second end of the unlocking actuator, which couplers 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.
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Patent Agency Ranking
116.发明授权公开(公告)号：US09561872B2
公开(公告)日：2017-02-07
申请号：US14789314
申请日：2015-07-01
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Graeme Steel
Abstract: A leak detection method for detecting a leak past a dynamic seal in aircraft landing gear (100) comprising: a strut (10); a rod (20) slidably mounted in the strut; and a bearing (70) fitted to an end (11) of the strut to guide the rod (20). The bearing includes a bushing (50) having a seal (62) arranged to rub against the rod (20) to provide sealing between the strut and the rod, defines a fluid chamber (2), and a stop nut (40) for preventing the bushing from moving relative to the strut. The method includes a step of installing a test nut (3) without a wiper seal in the place of the stop nut (40), the step of putting the hydraulic fluid in the landing gear under pressure, and the step of verifying the existence of a leak of hydraulic fluid on the outside surface (22) of the rod (20).
Abstract translation: 一种用于检测在飞机起落架（100）中通过动态密封件的泄漏的泄漏检测方法，包括：支柱（10）; 可滑动地安装在支柱中的杆（20） 以及装配到支柱的端部（11）以引导杆（20）的轴承（70）。 所述轴承包括具有密封件（62）的套管（50），所述密封件（62）布置成抵靠所述杆（20）摩擦，以在所述支柱和所述杆之间提供密封，限定流体室（2）和止动螺母（40） 衬套相对于支柱移动。 该方法包括安装没有刮水器密封件的测试螺母（3）代替止动螺母（40）的步骤，将起落架中的液压流体施加压力的步骤，以及验证是否存在 液压流体在杆（20）的外表面（22）上的泄漏。
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117.发明授权Aircraft landing gear equipped with means for driving in rotation wheels carried by the landing gear 有权飞机起落架配备有用于在由起落架承载的旋转轮中行驶的装置公开(公告)号：US09540098B2
公开(公告)日：2017-01-10
申请号：US14504605
申请日：2014-10-02
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Nicolas Mazarguil
CPC classification number: B64C25/405 , B64C25/34 , Y02T50/823
Abstract: A landing gear that comprises an axle (2) and a wheel (3, 3′). The wheel comprises a rim (4, 4′) mounted so as to rotate on the axle about a first axis of rotation (X), first blocks protruding from a lateral face (F, F′) of the rim, the first blocks being adapted to cooperate with a gearwheel (8) of a drive actuator (7) carried by the landing gear. The gearwheel is mounted rotatably about a second axis of rotation (Y) perpendicular to the first axis of rotation.
Abstract translation: 一种起落架，包括轴（2）和轮（3,3'）。 所述轮包括安装成围绕第一旋转轴线（X）在所述车轴上旋转的轮缘（4,4'），所述第一块从所述轮辋的侧面（F，F'）突出，所述第一块为 适于与由起落架承载的驱动致动器（7）的齿轮（8）配合。 齿轮围绕垂直于第一旋转轴线的第二旋转轴线（Y）可旋转地安装。
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公开(公告)号：US20160340032A1
公开(公告)日：2016-11-24
申请号：US15096345
申请日：2016-04-12
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Mathieu DAFFOS
CPC classification number: B64C25/405 , B64C25/34 , Y02T50/823
Abstract: A method of applying rotary drive by friction to an aircraft wheel that is provided with a drive track and that is mounted to rotate about an axis of rotation (X) on an axle carried by a low portion of aircraft landing gear by means of at least one friction roller (21) driven by a drive actuator (11) and associated with an actuator (23A, 23B, 30) for moving the roller between a disengaged position in which the roller is spaced apart from the drive track of the wheel and an engaged position in which the roller is kept pressed against the drive track. The method includes the step of controlling the force delivered by the actuator while they are holding the roller in the engaged position.
Abstract translation: 一种通过摩擦将旋转驱动器施加到具有驱动轨道的飞行器轮的方法，该飞行器轮被安装成通过至少借助于飞机起落架的低部分承载的轴上的旋转轴线（X）旋转 一个由驱动致动器（11）驱动并与致动器（23A，23B，30）相关联的摩擦辊（21），用于在所述辊与所述车轮的驱动轨道间隔开的脱离位置和所述致动器 其中辊被保持压靠在驱动轨道上。 该方法包括在将辊保持在接合位置时控制由致动器传递的力的步骤。
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公开(公告)号：US09476473B2
公开(公告)日：2016-10-25
申请号：US14645792
申请日：2015-03-12
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Vincent Gonzalez , Jacques Bussiere
IPC: F16D65/38 , F16D65/58 , F16D55/24 , B64C25/44 , B64C25/42 , F16D65/54 , F16D55/40 , F16D65/18 , F16D121/04
CPC classification number: F16D65/58 , B64C25/42 , B64C25/44 , F16D55/24 , F16D55/40 , F16D65/186 , F16D65/543 , F16D2121/04
Abstract: A brake actuator comprising a sleeve (1), a piston (3) sealingly slidably mounted in the sleeve to apply a braking force, the piston being provided with an internal cage (21), and a wear compensating device (10) which defines a retracted position of the piston in the sleeve by means of an axially mobile stop which is able to be moved forward by the piston during the application of a braking force and/in frictional relationship with a fixed part (12) of the wear compensating device attached to the sleeve. The mobile stop comprises a radially deformable bushing (16) which cooperates with an olive (15) which is attached to a distal end of the fixed part of the wear compensating device. The bushing comprises means for guiding its proximal end (17) against an internal face of the internal cage (21).
Abstract translation: 一种制动致动器，包括套筒（1），密封地可滑动地安装在套筒中以施加制动力的活塞（3），所述活塞设置有内部保持架（21），以及磨损补偿装置（10） 活塞在套筒中的缩回位置借助于轴向移动的止挡件，该止动件能够在施加制动力期间由活塞向前移动，并且与附接的磨损补偿装置的固定部件（12）成摩擦关系 到袖子。 移动式止动件包括可径向变形的衬套（16），该衬套与附接到磨损补偿装置的固定部分的远端的橄榄（15）配合。 衬套包括用于将其近端（17）引导到内部保持架（21）的内表面的装置。
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公开(公告)号：US09476471B2
公开(公告)日：2016-10-25
申请号：US14529320
申请日：2014-10-31
Applicant: MESSIER-BUGATTI-DOWTY
Inventor： Jacques Bussiere , Vincent Gonzalez , Marie-Laure De Crescenzo
IPC: F16D65/54 , F16D55/40 , F16D65/18 , B64C25/44 , F16D55/24 , F16D55/00 , F16D121/02 , F16D121/04
CPC classification number: F16D65/543 , B64C25/44 , F16D55/24 , F16D55/40 , F16D65/186 , F16D65/54 , F16D2055/0058 , F16D2121/02 , F16D2121/04
Abstract: A braking actuator for a hydraulic aircraft brake, received in a cavity of a ring of the brake. The actuator comprises a liner structure (1) sealed in the cavity of the ring, and a piston (3) slidably mounted in the liner structure to apply a braking force. A wear-compensating device (10) defines a retreated position of the piston in the liner structure by an axially movable stop (11) which can be advanced by the piston during the application of a braking force and in frictional relationship with a fixed part (18) of the wear-compensating device secured to the liner. An elastic member (24) returns the piston to the retreated position defined by the piston bearing against the movable stop, the movable stop being in frictional relationship with the fixed part via at least one telescopic intermediate element (16) interposed between the movable stop (11) and the fixed part (18).
Abstract translation: 用于液压飞行器制动器的制动致动器，容纳在制动器环的空腔中。 致动器包括密封在环的空腔中的衬垫结构（1）和可滑动地安装在衬套结构中以施加制动力的活塞（3）。 磨损补偿装置（10）通过可轴向移动的止动件（11）限定活塞在衬套结构中的后退位置，该止动件可在施加制动力期间由活塞推进并与固定部件 磨损补偿装置被固定到衬套上。 弹性构件（24）将活塞返回到由活塞轴承限定的退回位置抵靠可动止动件，可移动止动件通过至少一个伸缩中间元件（16）与固定部件形成摩擦关系，该伸缩中间元件插入在可动止动件 11）和固定部分（18）。
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