• 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:
    Electromechanical actuator comprising a frame (1) and an electric motor (2) driving at least one element (3) for motion transmission connected to the frame via a braking device (6), a magnetic torque limiter (5) and an element unidirectional transmission means (4), the braking device comprising an electrical activation member (6.5) such that, when the activation member is energized, the unidirectional transmission member is disengaged from the frame and, when the activation member is not powered, the unidirectional transmission member is secured to the frame and opposes the pivoting of the transmission element in a direction of rotation up to a maximum transmissible torque defined by the limiter magnetic torque (5).
    公开号:FR3022526A1
    申请号:FR1455726
    申请日:2014-06-20
    公开日:2015-12-25
    发明作者:Xavier Defosse
    申请人:Sagem Defense Securite SA；
    IPC主号:
    专利说明:

    [0001] The present invention relates to the displacement of a movable element relative to a fixed frame and more precisely to an electromechanical actuator usable for example in aeronautics, in particular for moving a flight control surface relative to the structure of the aircraft. an aircraft. Such a flight control surface is, for example, a fin, an elevon, a flap, a rudder, a elevator, a spoiler. The aircraft generally comprise a fixed structure, such as a wing or empennage, on which are articulated flight control surfaces mounted on the fixed structure for pivoting. Actuators mechanically connect the moving surfaces to the fixed structure and are connected to be controlled by a control unit on which the pilot of the aircraft acts. Actuators are known comprising an electric motor and a motion transmission member driven by a rotor of the electric motor. Generally, in these actuators, the electric motor has a stator fixed to a frame fixed to the fixed structure and the transmission element drives an input element of a transmission system, such as a screw-nut and / or or a reduction assembly, having an output member attached to the flight control surface such that movement of the output member causes the flight control surface to pivot between an extended position and a position retracted or a neutral position.
    [0002] In the event of a failure of the engine or its control means, it may be preferable, depending on the type of flight control surface, to allow the movement of the flight control surface to one of its positions but to prevent the movement of the flight control surface to its second position for example 3022526 2 under the effect of aerodynamic forces. To this end, the transmission assembly generally comprises a freewheel which can be engaged in the event of a failure of the motorization to oppose the pivoting of the transmission element in the direction corresponding to the displacement of the control surface of the transmission. flight to his second position. When the freewheel is engaged, the flight control surface tending to move to its deployed position exerts a torque on the transmission member, which torque is transmitted to the frame. In some cases, this torque may be important and may deteriorate the entire transmission chain to the structure of the aircraft. An object of the invention is to remedy this disadvantage. For this purpose, according to the invention, an electromechanical actuator comprising a fixed frame, an electric motor having a stator fixed to the frame, and at least one movement transmission element linked in rotation to a rotor of the motor are provided. said element being connected to the fixed frame via a braking device and a unidirectional transmission member. The actuator comprises a magnetic torque limiter and the braking device comprises an electrical activation member such that, when the activation member is energized, the unidirectional transmission member is disengaged from the frame and that, when the activation member is not energized, the unidirectional transmission member is secured to the frame and opposes the pivoting of the transmission element in a direction of rotation up to a maximum transmissible torque defined by the magnetic torque limiter. In case of excessive torque, the torque limiter will allow a sliding of the transmission element 35 relative to the frame, thus limiting the risk of deterioration of the frame. The use of a magnetic torque limiter is particularly advantageous because there is no friction and the limiter characteristics vary little with temperature (over a range of temperatures in relation to the applications of such an actuator, for example between -40 ° C and + 79 ° C). As a result, the limiter is weakly generating dispersions, dispersions which can be very detrimental and more particularly in actuators having a high transmission ratio which tends to amplify the dispersions. Advantageously, the magnetic torque limiter is mounted between the frame and the unidirectional transmission member.
    [0003] This embodiment has a particularly compact structure and makes it possible to integrate the braking device, the unidirectional transmission member and the magnetic torque limiter into the same subassembly.
    [0004] Preferably, the magnetic torque limiter is mounted between the braking device and the unidirectional transmission member. This arrangement allows a simple integration of the magnetic torque limiter.
    [0005] Other characteristics and advantages of the invention will emerge on reading the following description of particular non-limiting embodiments of the invention. Reference is made to the accompanying drawings, among which: FIG. 1 is a diagrammatic view in longitudinal section of an actuator according to a first embodiment of the invention; FIG. 2 is a view similar to FIG. 1 of a variant of the first embodiment; FIG. 3 is a diagrammatic view in longitudinal section of an actuator according to a second embodiment of the invention; FIG. 4 is a view similar to FIG. 1 of a variant of the second embodiment. The actuator according to the invention is here described in application to the displacement of a flight control surface relative to the structure of an aircraft. The flight control surface is movable between a deployed position and a neutral or retracted position. With reference to the figures, the electromechanical actuator comprises a frame 1 and an electric motor 2 having a stator fixed to the frame 1 and a rotor rotatably connected to a movement transmission element.
    [0006] The frame 1 is provided with means known in itself for its attachment to the structure of the aircraft. The electric motor 2 is powered via a control unit, not shown, which is connected to the electrical network of the aircraft for its power supply and that of the actuator and which is connected to the cockpit of the aircraft to receive it. Deployment or retraction orders from the flight control surface. The motion transmission element here is a shaft 3 mounted in the frame 1 for pivoting and connected to the flight control surface via a motion transmission assembly, not shown. The motion transmission assembly includes, for example, a reduction device and / or a motion transformation device such as a screw-nut assembly and an input member rotatably connected to the shaft 3 and an element output linked for example to the free end of a lever secured to the flight control surface. The shaft 3 is guided in rotation relative to the frame by bearings not shown and is connected to the frame 1 via a unidirectional transmission member, namely here a free wheel generally designated 4, a torque limiter generally designated at 5 and a braking device, generally designated 6. The freewheel 4 comprises an inner portion 4.1 5 secured to the shaft 3, an outer portion 4.2 mounted to pivot on the lower portion 4.1 and a ratchet assembly n. allowing rotation of the outer part 4.2 only in one direction of rotation. The torque limiter 5 is a magnetic torque limiter comprising a first plate 5.1 for a first series of magnets 7.1 and a second plate 5.2 provided with a second series of magnets 7.2. The first plate 5.1 is fixed to the outer part 4.2 of the freewheel 4 and the second plate 5.2 is rotatably connected to an inner ring 6.1 of the braking device 6. The first series of magnets 7.1 extends substantially in look at the second series of magnets 7.2 and is spaced from it by a gap 7.3. The magnetic field produced by the magnets and the width of the gap 7.3 define a maximum transmittable torque from the first plate 5.1 to the second plate 5.2. Sealing means are provided to prevent particles from agglomerating with the magnets and impairing the operation of the torque limiter 5.
    [0007] In addition to the movable ring gear 6.1, the braking device 6 comprises an outer ring gear 6.2 rigidly fixed to the frame 1 (more precisely, the outer ring gear 6.2 is here a part of the frame 1) and an outer ring gear 6.3 fixed to the frame 1 with a set axial. The inner ring 6.1 is fixed with axial play on the second plate 5.2 (the inner ring 6.1 is more precisely engaged on a grooved portion of the second plate 5.2) and has a portion which has faces each provided with a friction lining and which extends between friction guards carried by the external crowns 6.2, 6.3. Springs 6.4 extend between the frame 1 and the outer ring 6.3 to tighten the inner ring 6.1 between the outer rings 6.3 and 6.2. The braking device 6 also comprises an electrical activation member 6.5 in the form of a solenoid sized to, when energized, attract the outer ring gear 6.3 and away from the inner ring gear 6.1 by opposing the effort exerted by the springs 6.4. In operation, when the activation member 6.5 is energized, the shaft 3 can pivot in two directions of rotation (it should be noted that, in the forward direction of the freewheel 4, the motor 2 does not drive or only the inner ring 6.1 and the torque limiter 5) and, when the activation member 6.5 is not energized, the freewheel 4 opposes the rotation of the shaft 3 in one both directions of rotation. Thus, when the activation member 6.5 is energized, the electric motor 2, which is also powered, drives the shaft 3 in rotation in both directions of rotation. When the activation member 6.5 is not powered, the electric motor 2 is also not powered so that only aerodynamic forces exerted on the flight control surface can cause a pivoting of the 3. Because of the free wheel 4 which opposes the rotation of the shaft 3 in one of the two directions of rotation, the shaft 3 prevents the flight control surface from being displaced from its position. neutral position towards its deployed position, the displacement of the flight control surface to its neutral position being left free. However, if the aerodynamic forces exerted on the flight control surface generate on the shaft 3 a torque greater than the maximum torque transmissible between the plates 5.1, 5.2 of the torque limiter 5, the first plate 5.1 will pivot 35 relative to the second plate 5.2 thus allowing the rotation of the shaft 3 and a displacement of the flight control surface to its deployed position. The torque limiter 5 thus limits the torque transmissible to the structure of the aircraft and to the frame 1 via the shaft 3, the free wheel 4 and the braking device 6 when the activation member is not powered. With reference to FIG. 1 and according to the first embodiment, the gap 7.3 extends in a plane perpendicular to the axis A of rotation of the shaft 3.
    [0008] The first plate 5.1 here has a distal shape which is perpendicular to the axis A and which is pierced at its center to be fixed on a sleeve integral with the outer part of the freewheel 4. The second plate 5.2 a it also has a disc shape which is perpendicular to the axis A and which is pierced at its center to be fixed on a socket received pivotally in a bearing fixed to the frame 1. The end portion of the sleeve opposite the second platinum 5.2 is splined to receive axially sliding 20 the inner ring 6.1. In the variant of Figure 2, the second plate 5.2 has the same shape as before. The first plate 5.1 here has an annular shape centered on the axis A. The first plate 5.1 has an inner edge which extends around the socket of the second plate 5.2 leaving a space filled by a seal and an outer edge fixed to the flange of a socket integral with the outer part of the freewheel 4. A bearing is mounted between the socket of the second plate 5.2 and the socket of the first plate 5.1. The second plate 5.2 also has a disc shape which is perpendicular to the axis A and which is pierced at its center to be fixed on a socket pivotally received in a bearing fixed to the frame 1. end of the sleeve opposite the second plate 5.2 is splined to receive axially sliding the inner ring 6.1. With reference to FIG. 3 and according to the second embodiment, the gap 7.3 extends along a cylindrical surface centered on the axis A of rotation of the shaft 3. The first plate 5.1 here has a tubular centered shape. on the axis A and fixed on the outer part of the freewheel 4. The second plate 5.2 also has a tubular shape centered on the axis A: the second plate 5.2 surrounds the first plate 5.1 and is pivotally received in a bearing integral with the frame 1. The end portion 15 of the second plate 5.2 is splined to receive axially sliding the inner ring 6.1. Seals are mounted between the plates 5.1, 5.2 to oppose the introduction of particles into the air gap 7.3.
    [0009] In the variant of FIG. 4, the second platen 5.2 has the same shape as before. The first plate 5.1 also has an annular shape centered on the axis A but it extends around the second plate 5.2. The first plate 5.1 has one end carried by a flange integral with a socket integral with the outer portion of the freewheel 4. A bearing is mounted between the sleeve of the second plate 5.2 and the sleeve of the first plate 5.1. Of course, the invention is not limited to the embodiments described but encompasses any variant within the scope of the invention as defined by the claims. In particular, the magnetic torque limiter is mounted downstream of the unidirectional transmission member or between the braking device and the frame.
    [0010] The unidirectional transmission member may employ ratchets, rollers, or bracing members.
    权利要求:
    Claims (8)
    [0001]
    REVENDICATIONS1. Electromechanical actuator comprising a frame (1), an electric motor (2) having a stator fixed to the housing and at least one motion transmission member (3) rotatably connected to a rotor of the motor, said element being connected to the fixed frame via a braking device (6) and a unidirectional transmission member (4), characterized in that the actuator comprises a magnetic torque limiter (5) and the braking device comprises an electric actuator ( 6.5) such that, when the activation member is energized, the unidirectional transmission member is disengaged from the frame and, when the activation member is not energized, the unidirectional transmission member is secured to the frame and opposes the pivoting of the transmission element in a direction of rotation up to a maximum transmittable torque defined by the magnetic torque limiter (5).
    [0002]
    2. An actuator according to claim 1, wherein the magnetic torque limiter (5) is mounted between the frame (1) and the unidirectional transmission member (4).
    [0003]
    An actuator according to claim 2, wherein the magnetic torque limiter (5) is mounted between the braking device (6) and the unidirectional transmission member (4).
    [0004]
    4. An actuator according to claim 3, wherein the magnetic torque limiter (5) comprises a first series of magnets (7.1) integral with a first portion (5.1) rotatably connected to a first portion (4.1) of the unidirectional transmission member and a second series of magnets (7.2) integral with a second part (5.2) rotatably connected to a first part (6.1) of the braking device (6), the first series of magnets 3022526 11 extending substantially opposite the second series of magnets and being spaced therefrom by an air gap (7.3).
    [0005]
    5. An actuator according to claim 4, wherein the air gap (7.3) extends in a plane perpendicular to an axis (A) of rotation of the transmission element (3).
    [0006]
    6. Actuator according to claim 4, wherein the gap (7.3) extends along a cylindrical surface centered on an axis (A) of rotation of the transmission element (3).
    [0007]
    An actuator according to claim 1 comprising sealing means for preventing the introduction of particles into an air gap separating magnets from the magnetic torque limiter.
    [0008]
    8. An actuator according to claim 1, wherein the unidirectional transmission member is a freewheel (4).
    类似技术:
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    同族专利:
    公开号 | 公开日
    US9735647B2|2017-08-15|
    US20170141647A1|2017-05-18|
    WO2015193207A1|2015-12-23|
    CN106464115B|2017-11-10|
    FR3022526B1|2016-06-24|
    CN106464115A|2017-02-22|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2013076158A1|2011-11-22|2013-05-30|Sagem Defense Securite|An electromechanical actuator for an aircraft control surface, and an aircraft provided with such an actuator|
    US20130313067A1|2012-05-23|2013-11-28|Hamilton Sundstrand Corporation|Integrated torque limiter/no-back device|
    WO2014041143A1|2012-09-14|2014-03-20|Sagem Defense Securite|An electromechanical actuator with anti-blocking means|
    US2939973A|1956-10-10|1960-06-07|Bliss E W Co|Torque transmitting mechanism|
    EP0167626B1|1983-12-27|1988-08-24|Fanuc Ltd.|Electric motor with dc brake|
    US5465815A|1994-01-10|1995-11-14|Ikegami; Iwao|Magnetic brake|
    FR2877160B1|2004-10-27|2010-11-26|Eurocopter France|ELECTROMECHANICAL MOTOR WITH DOUBLE OUTPUT|
    JP2006250283A|2005-03-11|2006-09-21|Tok Bearing Co Ltd|Torque limiter|
    CN201230271Y|2008-07-15|2009-04-29|王雪霖|Flexible shaft connector|
    JP5748688B2|2012-02-24|2015-07-15|ジヤトコ株式会社|Motor and motor thrust type continuously variable transmission|JP6866981B2|2017-03-19|2021-04-28|学校法人早稲田大学|Torque limiter|
    US10975940B2|2017-08-24|2021-04-13|Eaton Intelligent Power Limited|Actuator and method|
    DE102017216399A1|2017-09-15|2019-03-21|Airbus Operations Gmbh|Control surface for an aircraft and aircraft with a flexible control surface|
    CN112087100B|2020-09-07|2021-11-02|台州泰力制动电机股份有限公司|Electromagnetic braking motor with abrasion compensation function|
    法律状态:
    2015-05-26| PLFP| Fee payment|Year of fee payment: 2 |
    2015-12-25| PLSC| Search report ready|Effective date: 20151225 |
    2016-05-26| PLFP| Fee payment|Year of fee payment: 3 |
    2017-02-17| CD| Change of name or company name|Owner name: SAFRAN ELECTRONICS & DEFENSE, FR Effective date: 20170111 |
    2017-05-23| PLFP| Fee payment|Year of fee payment: 4 |
    2018-05-25| PLFP| Fee payment|Year of fee payment: 5 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1455726A|FR3022526B1|2014-06-20|2014-06-20|ELECTROMECHANICAL ACTUATOR WITH MAGNETIC TORQUE LIMITER|FR1455726A| FR3022526B1|2014-06-20|2014-06-20|ELECTROMECHANICAL ACTUATOR WITH MAGNETIC TORQUE LIMITER|
    US15/320,207| US9735647B2|2014-06-20|2015-06-12|Electromagnetic actuator with magnetic torque limiter|
    PCT/EP2015/063246| WO2015193207A1|2014-06-20|2015-06-12|Electromagnetic actuator with magnetic torque limiter|
    CN201580032268.6A| CN106464115B|2014-06-20|2015-06-12|Electromagnetic actuators|
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