• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a braking actuator comprising a liner (1), a piston (3) slidably mounted in the liner for applying a braking force, the piston being equipped with an internal cage (21), a wear-compensating device (10) which defines a position of withdrawal of the piston in the liner by means of an axially movable stop that can be advanced by the piston during the application of a braking force and in frictional relation with a fixed part (12) of the wear compensating device secured to the liner, the mobile abutment comprising a radially deformable sleeve (16) which cooperates with an olive (15) integral with a distal end of the fixed part of the device retraction of wear, the sleeve having means for guiding its proximal end (17) against an inner face of the inner cage (21).
    公开号:FR3019145A1
    申请号:FR1452887
    申请日:2014-04-01
    公开日:2015-10-02
    发明作者:Vincent Gonzalez；Jacques Bussieres
    申请人:Messier Bugatti Dowty SA；
    IPC主号:
    专利说明:

    [0001] The invention relates to a brake actuator for an aircraft wheel hydraulic brake. BACKGROUND OF THE INVENTION The hydraulic brakes used to brake the wheels of aircraft generally comprise a ring having multiple cavities in which braking actuators are removably attached. Each of the actuators comprises a liner which is sealed to one of the cavities of the ring and in which a piston is slidably mounted on a sliding axis. The ring distributes hydraulic fluid under pressure to all its cavities, a fluid which acts on the piston to pull it out and apply a braking force on friction elements extending towards the crown, including rotating rotors. with the wheel, and stators that are motionless in rotation. The piston generally has an operating stroke that it travels when applying a braking force. This operating stroke, of the order of a few millimeters, is sufficient to allow the application of the braking force on the friction elements, and the recoil of the piston so as to allow free rotation of the rotors. For this purpose, a spring extending inside the piston ensures the retreat of the piston to a retracted position when the braking force is no longer applied. However, since the friction elements wear out gradually as a result of the repeated application of braking forces, it is important to ensure that the piston is always close to the friction elements. To do this, it is known to equip the brake actuators with a wear compensating device which extends inside the piston.
    [0002] Thus, wear-compensating devices are known which comprise a movable stop which is slidably mounted with friction along the axis of sliding on a central rod extending in the piston and which defines the retracted position of the piston. When applying a braking force, the piston is pushed towards the friction elements and, if appropriate, drives the movable stop with it by overcoming the friction between the rod and the stop, which causes the advancement of the movable stop on the rod. When the force is released, the spring moves the piston back to the new retracted position which has advanced due to the advancement of the movable stop relative to the rod.
    [0003] The friction can be organized as follows: the movable stop comprises a radially deformable sleeve which cooperates at a distal end with an integral olive of a distal end of the central rod to be deformed by said olive.
    [0004] However, the movable stop tends to tilt around the olive during its movement along the sliding axis. The proximal end of said movable stop then rubs against the central rod which can cause the formation of undesirable scratches on the central rod. Indeed, the proximal end of the piston is partly guided by the central rod of the wear compensating device, a seal being carried by the piston so as to extend between the central rod and the piston. proximal end of the piston. Thus, during movement of the piston along the sliding axis, the seal regularly rubs on said scratches which eventually result in deterioration of the seal harmful to the sealing of the actuator. OBJECT OF THE INVENTION The object of the invention is to propose a braking actuator for an aircraft wheel hydraulic brake that does not have the aforementioned drawback. PRESENTATION OF THE INVENTION In view of achieving this goal, there is provided a braking actuator for an aircraft wheel hydraulic brake, intended to be received in one of the cavities of a brake crown, the actuator comprising a liner adapted to be received sealingly in the cavity of the crown; - A piston slidably mounted in the sleeve according to a sliding axis for applying a braking force during the introduction of a pressurized fluid into the cavity, the piston being equipped with an inner cage; a wear-compensating device which defines, with the inner cage, a position of withdrawal of the piston in the liner by means of an axially movable abutment which can be advanced by the internal cage when a force of force is applied; braking and in frictional relation with a fixed part of the wear compensating device secured to the liner, the movable abutment comprises a radially deformable sleeve which cooperates with an olive, to be deformed by said olive, which is solid with a distal end of the fixed part of the wear compensating device; and - an elastic member for returning the piston to the retracted position defined by pressing the piston on the inner cage, inner cage itself bearing on the sleeve. According to the invention, the sleeve comprises means for guiding its proximal end against an inner face of the inner cage. Thus the sleeve is both guided at its inner wall in contact with the olive and at its proximal end in contact with the inner cage. This limits the tilting of the sleeve around the olive especially at the beginning of the cycle when the sleeve is not yet deformed and that the olive is in contact with the distal end of the sleeve. In this way, it avoids the formation of undesirable scratches on the fixed part of the wear compensating device during movement of the sleeve along the sliding axis.
    [0005] For the present application, the term "proximal end" means the end closest to the bottom of the crown cavity associated with the actuator in question and therefore the term "distal end" means the end closest to the brake.
    [0006] BRIEF DESCRIPTION OF THE FIGURES The invention will be better understood in the light of the description which follows with reference to the figures of the accompanying drawings, in which: FIG. 1 is a sectional view of a braking actuator according to the invention; illustrated in place in a ring of an aircraft hydraulic brake; FIG. 2 is a figure similar to FIG. 1, the actuator being illustrated during the application of a braking force; - Figure 3 is a figure similar to Figure 2, the actuator being illustrated after releasing the braking force; FIG. 4 is an enlarged view of the detail A illustrated in FIG. 1, an exaggerated space having been illustrated between the cage and the socket. DETAILED DESCRIPTION OF THE INVENTION With reference to FIG. 1, the braking actuator 100 of the invention is intended to be received in one of the cavities 200 of a ring of an aircraft hydraulic brake, further comprising friction elements 300 comprising a succession of rotor disks and stator disks, for example carbon disks, on which the actuator selectively exerts a braking force during the admission of fluid under pressure (illustrated by points) in the cavity 200. The actuator 100 first comprises a generally cylindrical liner 1 which is received sealingly in the cavity 200 of the crown. For this purpose, a seal 2 cooperates with an outer face of the jacket to contain the hydraulic fluid in the cavity 200. A piston 3 is slidably mounted in the sleeve 1 along a sliding axis X. For this purpose, the distal end 5 of the liner 1 is shaped in a bearing to guide the piston 3. The distal end 5 of the liner 1 is provided with a scraper 7. In addition, the proximal end 4 is shaped. on its outer bearing face which extends to fit against an inner face of the liner 1. The proximal end of the piston 1 is thus provided with a first seal 6 arranged between the inner face of the liner 1 and the outer face of the proximal end 4 of the piston 3. In addition, the distal end of the piston 3 carries a pad 25 intended to come into service on the friction elements 300. In addition, the piston 3 is equipped with an inner cage 21 which is stopped on the piston 3 by means of a segment stop 22 secured to the piston 3. The inner cage 21 and has on its outer wall a first step 14 adapted to cooperate with said stop segment 22. The inner cage further has a second step 18 adapted to cooperate with a spring 24 extending between said second step 18 and the proximal end 4 of the piston 3. The actuator 100 is also provided with a wear compensating device 10.
    [0007] The wear compensating device 10 comprises a fixed part integral with the liner 1. The fixed part here comprises a central rod 12, a proximal end 8 of which is secured to the liner 1. The central rod 12 is arranged so that the piston 3 and the inner cage 21 extend around the central rod 12. More specifically, the proximal end 4 of the piston 3 is shaped on its inner bearing face which extends to fit against the central rod 12. L The proximal end 4 of the piston 3 thus comprises a second seal 9 arranged between the central rod 12 and the piston 3. In this way, the central rod 12 also serves to guide the sliding of the piston 3 in the liner 1 according to the sliding axis X.
    [0008] Moreover, the distal end of the central rod 12 carries an olive 15 with a spherical outer surface. The wear compensating device further comprises a movable stop which comprises a deformable bush 16 extending around the central rod 12 between said central rod 12 and the inner cage 21. The olive 15 is of a diameter greater than an internal diameter of the sleeve 16, so that the displacement of the olive 15 in the sleeve 16 causes the radial deformation of the sleeve 16, which generates a sufficient frictional force to retain the sleeve in position on the olive 15 in the absence of external solicitation. Moreover, because of the radial deformation of the bushing 16, the deformed portion of the bushing 16 abuts against the internal face of the inner cage 21, which also generates a sufficient frictional force to hold the cage internal 21 in position on the sleeve 16, and therefore on the olive 15, in the absence of internal stress. The distal end of the sleeve 16 further comprises a flange 11 forming an abutment against which the distal end 13 of the inner cage 21 comes into contact during the application of a braking force. According to the invention, and as more visible in FIG. 4, the proximal end 17 of the sleeve 16 is shaped so as to widen radially towards the inner face of the inner cage 21. The proximal end 17 is thus curved in the direction of the inner face of the inner cage 21. In this way, the proximal end 17 extends in adjustment against the internal face of the inner cage 21 and thus forms means for guiding the proximal end 17 against the inner face of the inner cage 21 (the space between the proximal end 17 and the inner cage being shown here exaggerated to facilitate understanding of the invention).
    [0009] The sleeve 16 is thus guided at its proximal end by the inner cage 21 and at its distal end, when the sleeve 16 is not or slightly deformed, by the olive 15. In a rest situation, the spring 24 pushes back. the piston 3 to the position of withdrawal illustrated in Figure 1, defined by the support of the stop segment 22 against the first step 14 of the inner cage 21. The operation of the braking actuator of the invention is the next. Starting from the retracted position illustrated in FIG. 1, a braking force is applied by admitting pressurized fluid into the cavity 200. The fluid pushes the piston 3 towards the discs 300. If, before the pad 25 touches the disks 300, the proximal end 4 of the piston 3 abuts against the proximal end 19 of the inner cage 21, the distal end 13 of the inner cage 21 is advanced by the piston 3 and bears against the collar 11 of the sleeve 16 which causes a simultaneous displacement of the inner cage 21 and the sleeve 16 along the axis of sliding X.
    [0010] The sleeve 16 is thus advanced, via the inner cage 21, by the piston 3 against the friction generated by the radial deformation that the olive 15 imposes on the bushing 16, until it contacts the pad 25 with the discs 300, as illustrated in Figure 2. Then, when the braking force is released, the piston 3 returns under the effect of the spring 24, until the stop segment 22 comes into stop against the first redan 14 of the inner cage 21, thereby defining a new withdrawal position, advanced relative to the previous one, as shown in Figure 3. The operational stroke of the piston (between the position of Figure 2 and the position of FIG. 3) is unchanged, only the retracted position having slightly advanced to compensate for the wear of the discs 300. The invention is not limited to what has just been described, but rather encompasses any variant falling within the scope defined by the claims.
    权利要求:
    Claims (3)
    [0001]
    REVENDICATIONS1. Brake actuator for an aircraft wheel hydraulic brake, to be received in one of the cavities (200) of a brake ring, the actuator comprising - a jacket (1) adapted to be received sealing in the cavity of the crown; a piston (3) slidably mounted in the sleeve according to a sliding axis (X) for applying a braking force when introducing a fluid under pressure into the cavity, the piston being equipped with an inner cage (21); - a wear compensating device (10) which defines, with the inner cage, a position of withdrawal of the piston in the liner by means of an axially movable abutment which can be advanced by the inner cage during the application of a braking force and in frictional relation with a fixed part (12) of the integral wear-catching device of the liner, the movable abutment comprises a radially deformable sleeve (16) which cooperates with an olive (15), to be deformed by said olive, which is secured to a distal end of the fixed part of the wear-compensating device; and - an elastic return member (24) of the piston to the retracted position defined by pressing the piston on the inner cage, inner cage itself bearing on the sleeve; characterized in that the sleeve comprises means for guiding its proximal end (17) against an inner face of the inner cage (21).
    [0002]
    2. An actuator according to claim 1, wherein the proximal end (17) of the sleeve (16) is shaped so as to widen radially towards the inner face of the inner cage (21) to extend to fit against said inner face.
    [0003]
    3. Hydraulic brake for an aircraft wheel, comprising at least one braking actuator according to one of the preceding claims.
    类似技术:
    公开号 | 公开日 | 专利标题
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    FR2611838A1|1988-09-09|HYDRAULICALLY CONTROLLED CLUTCH ACTUATING DEVICE
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    同族专利:
    公开号 | 公开日
    FR3019145B1|2016-04-29|
    US20150275992A1|2015-10-01|
    EP2927119B1|2017-07-12|
    CN104976255A|2015-10-14|
    CN104976255B|2017-10-24|
    US9476473B2|2016-10-25|
    EP2927119A1|2015-10-07|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3903999A|1974-12-05|1975-09-09|Bendix Corp|Extensible brake adjuster and reset apparatus|
    GB2017844A|1978-04-03|1979-10-10|Bendix Corp|Fluid pressure actuator|
    US4503950A|1983-01-27|1985-03-12|Allied Corporation|Brake actuator-adjuster mechanism|
    US4815359A|1987-12-17|1989-03-28|Allied-Signal Inc.|Compact brake piston return mechanism|
    EP0555819A1|1992-02-13|1993-08-18|The B.F. Goodrich Company|Aircraft brake|
    WO2005019679A1|2003-08-18|2005-03-03|Goodrich Corporation|Brake adjusting mechanism|
    US3990547A|1975-09-04|1976-11-09|The B. F. Goodrich Company|Brake retractor mechanism|
    US7344006B2|2004-03-03|2008-03-18|Goodrich Corporation|Piston assembly for use in a brake assembly|
    FR2987662B1|2012-03-02|2014-04-11|Messier Bugatti Dowty|AIRCRAFT WHEEL ELECTRIC BRAKE COMPRISING AN ELECTROMECHANICAL ACTUATOR EQUIPPED WITH A TEMPERATURE SENSOR|FR3012856B1|2013-11-04|2015-12-11|Messier Bugatti Dowty|BRAKE ACTUATOR FOR AN AIRCRAFT WHEEL HYDRAULIC BRAKE.|
    CN106763343A|2017-02-17|2017-05-31|西安航空制动科技有限公司|A kind of aviation spring shell type automatic gap adjusting piston component|
    CN107264782B|2017-05-22|2019-08-06|肇庆市广应科通用航空研究院|Aircraft brake valve arrangement, pilot system and airplane brake system|
    CN107387608B|2017-08-11|2019-05-03|广西柳工机械股份有限公司|Brake returning device and brake|
    CN110878800A|2018-09-05|2020-03-13|贵州新安航空机械有限责任公司|Brake actuating cylinder|
    法律状态:
    2015-04-21| PLFP| Fee payment|Year of fee payment: 2 |
    2016-04-21| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-19| PLFP| Fee payment|Year of fee payment: 4 |
    2017-06-23| CD| Change of name or company name|Owner name: MESSIER-BUGATTI-DOWTY, FR Effective date: 20170518 |
    2018-04-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1452887A|FR3019145B1|2014-04-01|2014-04-01|BRAKE ACTUATOR FOR AN AIRCRAFT WHEEL HYDRAULIC BRAKE|FR1452887A| FR3019145B1|2014-04-01|2014-04-01|BRAKE ACTUATOR FOR AN AIRCRAFT WHEEL HYDRAULIC BRAKE|
    EP15158896.9A| EP2927119B1|2014-04-01|2015-03-12|Brake actuator for an aircraft wheel hydraulic brake|
    US14/645,792| US9476473B2|2014-04-01|2015-03-12|Brake actuator for an aircraft wheel hydraulic brake|
    CN201510132997.0A| CN104976255B|2014-04-01|2015-03-25|Brake actuator for aircraft wheel liquid braking device|
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