• 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 for an aircraft hydraulic brake, intended to be received in one of the cavities of a brake ring, the actuator comprising: - a jacket (1) adapted to be received at sealing in the cavity of the crown; - A piston (3) slidably mounted in the liner according to a sliding axis for applying a braking force when introducing a fluid under pressure into the cavity; - a wear compensating device (10) which defines a position of withdrawal of the piston in the liner by means of a movable stop (11; 111) which can be advanced by the piston during the application of a force of braking; - An elastic return member (18) of the piston to the withdrawal position bearing on the movable stop; According to the invention, the movable stop is associated with a notched indexing member (13) allowing displacement of the movable stop under the thrust of the piston, but preventing any retreat of the movable stop relative to the sleeve.
    公开号:FR3030662A1
    申请号:FR1462611
    申请日:2014-12-17
    公开日:2016-06-24
    发明作者:Victor Eyanga；Vincent Gonzalez
    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 attached to a seal in one of the cavities of the ring and in which a piston is mounted to slide tightly along a sliding axis. The ring distributes hydraulic fluid under pressure to all its cavities, which fluid acts on the piston to pull it out and apply a braking force on friction elements extending opposite the crown, including rotors which rotate 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 retraction of the pusher so as to allow free rotation of the rotors. For this purpose, a spring extending inside the piston ensures the retraction of the pusher 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. The wear compensating device comprises 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.
    [0002] 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 the movable stop on the central rod. When the force is released, the spring, which extends between the movable stop and the piston, back the piston to the new withdrawal position, which has advanced due to the advancement of the movable stop. For this purpose, the movable stop is associated with a friction member which immobilizes the movable stop, but which nevertheless allows its advancement under the thrust of the piston when it does not reach the friction elements of the brake. In certain circumstances, it has been observed that, in the zones of the liner on which the friction member associated with the movable abutment bears, the piston seal could undergo a faster wear which puts into question the tightness of the actuator.
    [0003] OBJECT OF THE INVENTION The object of the invention is to propose a braking actuator for an aircraft hydraulic brake that avoids the aforementioned drawbacks. PRESENTATION OF THE INVENTION In view of achieving this goal, there is provided a braking actuator for an aircraft hydraulic brake, intended to be received in one of the cavities of a brake ring, the actuator comprising: a jacket adapted to be received sealingly in the cavity of the crown; - A piston slidably mounted in the liner according to a sliding axis for applying a braking force when introducing a fluid under pressure into the cavity; a wear-compensating device which defines a position of withdrawal of the piston in the liner by means of a movable stop that can be advanced by the piston during the application of a braking force; an elastic member for returning the piston towards the retracted position bearing on the mobile stop; wherein, according to the invention, the movable stop is associated with a notched indexing member allowing movement of the movable stop under the thrust of the piston, but preventing any retreat of the movable stop relative to the sleeve. Thus, it avoids the problems associated with the use of friction materials in an environment potentially polluted by carbon dust or hydraulic fluid. The notched indexing member defines a succession of stable positions of the movable stop preventing it from moving back even in the event of pollution. The seal of the piston no longer passes over a portion of the wall of the liner that would have been stressed or even damaged by a friction member, made unnecessary by the presence of the notched indexing member. According to a preferred embodiment, the notched indexing member comprises: a notched wall associated with one of the sleeve or the movable stop; - A deformable ring having on the one hand a notched portion adapted to cooperate with the toothed wall, and on the other hand a conical seat adapted to cooperate with a conical seat associated with the other of the sleeve or the movable stop; - Reminder means of the deformable ring against the seat so as to immobilize the stop by cooperation of the ring with the toothed wall; - The movable stop being able to advance one or more notches relative to the deformable ring when the piston abuts against the movable stop and causes the detachment of the ring of the toothed wall against the return means. 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 FIG. place in a ring of an aircraft hydraulic brake at rest; - Figure 2 is a figure similar to Figure 1, the actuator being illustrated during the application of a standard braking force, the operational stroke of the piston is not fully consumed; - Figure 3 is a figure similar to Figure 2, the actuator being illustrated during the application of a braking force, the operational stroke of the piston being fully consumed before the piston comes into contact with the discs; - Figure 4 is a figure similar to Figure 3, illustrating the advancement of the movable stop to allow the piston to come into contact with the discs; FIG. 5 is a figure similar to FIG. 4, the actuator being illustrated after releasing the braking force; FIGS. 6 and 7 are figures similar to FIG. 1 of alternative embodiments of the actuator of the invention. 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 crown of an aircraft hydraulic brake, comprising furthermore, 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 comprises firstly a generally cylindrical liner 1 which is received sealingly in the cavity 200 of the ring gear. For this purpose, a seal 2 cooperates with an outer face of the jacket to contain the hydraulic fluid in the cavity. A piston 3 is mounted to slide in the liner 1 along a sliding axis X. For this purpose, the piston 3 comprises a bearing-shaped end 8 which extends in adjustment against an inner face of the liner 1 and which receives a seal 6. It will be noted that the proximal end 8 of the piston 3 is here closed by a wall integral with the piston, so as to confine the hydraulic fluid 25 in a zone remote from the discs 300. The end distal of the piston 3 receives a pad 9 to exert a bearing against the discs 300. The actuator 100 is provided with a wear compensating device 10 which, according to the invention, extends between the jacket 1 and the 3. The wear compensating device 10 comprises a movable stop 11 in the general shape of a bushing whose external wall comprises notches 12. This notched outer wall 12 cooperates with a deformable split ring 13 whose internal diameter is also notched, and which has a conical seat which cooperates with a conical seat 14 of the liner 1 to close the ring 13 on the notched wall 12. For this purpose, a series of spring washers 15 extends between the split ring 13 and a stop ring 16 serving as a stop. The function of these spring washers 15 is to permanently push the split ring 13 against the conical seat 14 to force it to close on the notches of the notched outer wall 12, and thus immobilize the movable stop 11. The movable stop 11 comprises an internal protrusion 17 which defines a stop for a return spring 18 extending between said protrusion 17 and the piston 3 to return it to the retracted position. One of the end faces 19 of the movable stop 11 (turned towards the proximal end 8 of the piston 3) can be engaged by the piston 3 itself when the operational stroke has been fully consumed before the piston 3 n reaches the discs 300, as will be detailed later.
    [0004] The operation of the braking actuator of the invention is as follows. Starting from the retracted position illustrated in FIG. 1, a braking force is applied by admitting fluid under pressure into the cavity 200. The fluid pushes the piston 3 towards the discs 300 against the force of the spring. The piston 3 then applies a press force on the discs 300, as illustrated in FIG. 2. However, it is possible that the distance between the pad 9 and the discs is greater than the operational stroke of the piston 3. In this situation, and as illustrated in Figure 3, before touching the discs 300, the piston 3 causes the compression of the spring 18 to the point that the piston 3 comes dock the end face 19 of the movable stop 11. The piston 3 then pushes the movable stop 11 against the resistant force of the spring washers 15, which has the effect of raising the split ring 13 on its conical seat 14. If the thrust of the piston 3 continues, the resistant force elastic washers 15 will dev enir important enough to force the opening of the split ring 13, so that it jumps one or more notches to allow the advance of the movable stop 11 under the thrust of the piston 3, while returning in abutment against its conical seat 14, as shown in Figure 4. The return of the split ring 13 against the bottom of the conical seat 14 has the effect of confirming it around the movable stop 11, which immobilizes it in a new position, advanced compared to the previous one. The notches prevent any recoil movement of the mobile stop 11. Then, when the braking force is released, the piston 3 retreats under the effect of the spring 18, thus defining a new withdrawal position, advanced compared to the previous . The operational stroke of the piston (between the position of Figure 4 and the position of Figure 5) is unchanged, only the withdrawal position has advanced slightly to compensate for the wear of the discs 300.
    [0005] On the embodiment shown in Figure 6, the notches are now carried by an inner surface 21 of the liner 1 which extends in extension of the cylindrical surface against which rubs the seal 6. It should be noted that the notches have inverted slopes with respect to their slope of Figures 1 to 4. The split ring 13 is also reversed, and its outer diameter is now notched. The conical seat 14 is now formed in the movable stop 11, the spring washers 15 always forcing the split ring 13 bearing against the conical seat 14. The operation of this variant is in all respects similar to what has been described before. In the variant embodiment illustrated in FIG. 7, the notches are now carried by a central rod 22. Here the movable stop 111 is always in the form of a sleeve, but extends between the central rod 22 and the piston 3, so that that the spring 18 extends inside the piston 3 and not around, as before. The conical seat 14 is now formed inside the movable stop 111. The central rod 22 comprises a head 23 secured to the liner 1 by screws 24, so that the notched wall is associated with the liner 1. It will be noted that here the hydraulic fluid is not stopped by a wall of the proximal end of the piston 3, and so it completely bathes the inside of the piston 3, including the wear compensating mechanism 10 whose operation in no way altered. Indeed, the notches and the closing of the split ring 13 on the notches due to its support on the conical seat 14 ensure the immobilization of the movable stop 111, even though the wear compensating mechanism 10 bathes in the hydraulic fluid. The invention is not limited to what has just been described, but on the contrary covers any variant within the scope defined by the claims.
    权利要求:
    Claims (5)
    [0001]
    REVENDICATIONS1. Brake actuator for an aircraft hydraulic brake, intended to be received in one of the cavities of a brake crown, the actuator comprising: a jacket (1) adapted to be received sealingly in the cavity of the crown ; - A piston (3) slidably mounted in the liner according to a sliding axis for applying a braking force when introducing a fluid under pressure into the cavity; - a wear compensating device (10) which defines a position of withdrawal of the piston in the liner by means of a movable stop (11; 111) which can be advanced by the piston during the application of a force of braking; - An elastic return member (18) of the piston to the withdrawal position bearing on the movable stop; wherein, according to the invention, the movable stop is associated with a notched indexing member (13) allowing the moving stop to move under the thrust of the piston, but preventing the mobile stop from moving back relative to the sleeve.
    [0002]
    2. Brake actuator according to claim 1, wherein the notched indexing member comprises: - a notched wall associated with one of the liner (1) or the movable stop (11; 111); - A deformable ring (13) having on the one hand a notched portion adapted to cooperate with the toothed wall, and on the other hand a conical seat adapted to cooperate with a conical seat associated with the other of the sleeve or the stop movable; - return means (15) of the deformable ring against the seat so as to immobilize the stop by cooperation of the ring with the toothed wall; the movable stop being able to advance one or more notches relative to the deformable ring when the piston abuts against the movable stop and takes off the ring of the toothed wall against the return means.
    [0003]
    3. Brake actuator according to claim 2, wherein the movable stop (11) extends around the piston and has an outer wall facing the liner which is notched.
    [0004]
    An actuator according to claim 2, wherein the movable abutment (11) extends around the piston, the liner having an inner wall facing towards the movable stopper which is serrated.
    [0005]
    5. An actuator according to claim 2, wherein the movable stop (111) extends inside the piston, the liner being associated with a central rod (22) having an outer wall facing the movable stop which is notched.
    类似技术:
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    同族专利:
    公开号 | 公开日
    EP3034368B1|2017-04-12|
    FR3030662B1|2016-12-30|
    EP3034368A1|2016-06-22|
    US20160176518A1|2016-06-23|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB359068A|1930-07-24|1931-10-22|Lockheed Hydraulic Brake Compa|Improvements in or relating to brake mechanism|
    GB1378795A|1971-03-10|1974-12-27|Gunthart R|Self adjusting connecting rods|
    FR2297359A1|1975-01-11|1976-08-06|Schubeler & Mattli Ag|Adjusting mechanism for clutch and brake wear - has differential rolling drive with balls wedged between conical seat and cylinder|
    JPS59200823A|1983-04-30|1984-11-14|Hino Motors Ltd|Automatic regulator for shoe gap of drum brake|
    US2952338A|1957-10-28|1960-09-13|Goodrich Co B F|Hydraulic brake actuating mechanism|
    DE1600157B1|1967-01-27|1970-08-06|Teves Gmbh Alfred|Adjustment device for a floating caliper partially lined disc brake|
    FR2142829B1|1971-06-25|1973-05-25|Pont A Mousson Fond|
    US3920102A|1973-01-19|1975-11-18|Tokico Ltd|Disc brake actuating and adjusting mechanism|
    US3887042A|1974-07-22|1975-06-03|Bendix Corp|Piston and extensible cylinder therefor|
    US4751985A|1986-09-15|1988-06-21|Allied Corporation|Compact brake piston-return mechanism|
    US4815359A|1987-12-17|1989-03-28|Allied-Signal Inc.|Compact brake piston return mechanism|
    US5209154A|1990-11-08|1993-05-11|Allied-Signal Inc.|Dual area brake actuation piston mechanism|
    US5219046A|1992-02-13|1993-06-15|The B. F. Goodrich Company|Aircraft brake|
    US6016892A|1997-08-01|2000-01-25|Alliedsignal Inc.|Pinless internal automatic adjuster for brake piston|FR3030001B1|2014-12-12|2018-04-20|Safran Landing Systems|BRAKE ACTUATOR FOR AN AIRCRAFT WHEEL HYDRAULIC BRAKE.|
    EP3626993A1|2018-09-18|2020-03-25|KNORR-BREMSE Systeme für Nutzfahrzeuge GmbH|Brake assembly and method for controlling a brake assembly|
    US20200347900A1|2019-04-30|2020-11-05|Goodrich Corporation|Hydraulic brake actuator piston adjuster assembly|
    EP3763963A1|2019-07-12|2021-01-13|Goodrich Corporation|Brake actuator|
    EP3910211A1|2020-05-12|2021-11-17|Goodrich Corporation|Brake actuator|
    CN112145596A|2020-09-25|2020-12-29|湖北联统机械有限公司|Brake caliper piston return pressing device and working process thereof|
    法律状态:
    2015-06-26| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-24| PLSC| Publication of the preliminary search report|Effective date: 20160624 |
    2016-12-22| PLFP| Fee payment|Year of fee payment: 3 |
    2017-06-23| CD| Change of name or company name|Owner name: MESSIER-BUGATTI-DOWTY, FR Effective date: 20170518 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 4 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-11-17| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1462611A|FR3030662B1|2014-12-17|2014-12-17|BRAKE ACTUATOR FOR AN AIRCRAFT WHEEL HYDRAULIC BRAKE.|FR1462611A| FR3030662B1|2014-12-17|2014-12-17|BRAKE ACTUATOR FOR AN AIRCRAFT WHEEL HYDRAULIC BRAKE.|
    EP15198115.6A| EP3034368B1|2014-12-17|2015-12-04|Brake actuator for aircraft wheel hydraulic brake|
    US14/967,435| US20160176518A1|2014-12-17|2015-12-14|Brake actuator for aircraft wheel hydraulic brake|
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