• 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 an actuator (4) of flight control surface (3) of an aircraft, comprising: - a fixed ring (9, 10) adapted to be fixed to a fuselage (2) of the aircraft; a ring gear (11) movable in rotation with respect to the fixed ring gear (9, 10) about an axis of rotation (X), - an output ring (12) adapted to be fixed to the flight control rudder ( 3), and - a coupling mechanism (30) comprising a disk (31, 32) movable in translation relative to the mobile ring (11) in a direction parallel to the axis of rotation (X), the disk ( 31, 32) being movable between an engaged position in which the disc (31, 32) is in engagement with both the movable ring (11) and the output ring (12) so as to make the ring (12) ) secured to the movable ring (11), and a disengaged position in which the disc (31, 32) is disengaged from the movable ring (11), so as to separate the output ring (12). ) of the movable ring (11), a retaining piece (47, 48) adapted to hold the disc (31, 32) in the engaged position, and a rupture member (34) adapted to be activated to break the retaining piece (47, 48), so as to allow movement of the disc (31, 32) in the disengaged position.
    公开号:FR3028836A1
    申请号:FR1461246
    申请日:2014-11-20
    公开日:2016-05-27
    发明作者:Severin Viennot；Thierry Cartry；Marc Lebrun
    申请人:Sagem Defense Securite SA；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The invention relates to a flight control actuator actuator of an aircraft, and an actuation assembly comprising such an actuator. STATE OF THE ART In aircraft, the control surfaces (flaps or movable fins) make it possible to modify the flow of the surrounding air over the surface of the aircraft, in order to control the position of the aircraft in space. The control surfaces include, for example, the primary flight control surfaces which are actuated in the flight phase, and the secondary flight control surfaces (leading edge flaps, high lift flaps) which are actuated only during certain low speed phases, in particular the takeoff and landing phases. Among the primary flight controls, the fins located at the ends of the wings of the aircraft, to control the rolling motion of the aircraft. These control surfaces are pivotally mounted relative to the fuselage of the aircraft. Each rudder can be actuated mechanically by several control actuators housed in the wing of the aircraft, so that in case of failure of one of the actuators, another actuator takes the relay. The actuators may be hydraulic actuators or electromechanical, linear or rotary actuators. However, electromechanical actuators present risks of seizure that can cause a blockage of the rudder. In case of seizure of the actuator, it is therefore necessary to decouple the seized actuator from the rudder to allow actuation of the rudder by the other actuator (s), to avoid damage to the actuator. governor or the actuators. For this purpose, there are known decoupling devices comprising a clean part to break when subjected to a torque greater than a predetermined limit torque. EP 0 826 902 describes for example a rotary actuator 5 comprising a shearing piece providing a connection between an input shaft and a sun gear. In case of seizing of the actuator, the shear piece is subjected to a shear stress between the input shaft and the sun gear. When the shear stress exceeds a certain threshold, the shear piece is broken. The rotation of the input shaft relative to the sun gear then causes a displacement in translation of a decoupling nut by means of a screw-nut connection, the displacement of the decoupling nut having the effect of actuating a decoupling mechanism to separate an output ring of the actuator from a movable ring. A disadvantage of this device is that the shear piece must be able to break reliably when subjected to a shear stress greater than a predefined threshold, while being able to both transmit high torque. close to the breaking point, and to withstand fatigue stresses. This becomes particularly problematic when the fatigue failure mode becomes predominant. However, the threshold of rupture of the shearing part depends on the dimensions and characteristics of the material forming the part, this threshold being able to vary according to the operating conditions of the actuator. In addition, the predefined break point is not necessarily compatible with all flight control applications. However it is not possible to adjust the threshold according to these applications. Finally, the rotary actuator has a large footprint due to the presence of the decoupling mechanism, and the decoupling mechanism itself has a risk of seizure. SUMMARY OF THE INVENTION An object of the invention is to provide an actuator adapted to be decoupled from the rudder reliably in case of seizure while having a small footprint.
    [0002] This object is achieved within the framework of the present invention by means of an actuator for the flight control surface of an aircraft, comprising: at least one fixed crown adapted to be fixed to the fuselage of the aircraft, at least one crown movable in rotation relative to the fixed ring about an axis of rotation, - an output ring adapted to be fixed to the flight control rudder, and - a coupling mechanism comprising a mobile disk in translation relative to to the movable ring in a direction parallel to the axis of rotation, the disc being movable between an engaged position in which the disc is in engagement with both the movable ring and the outlet ring so as to make the ring integral. of the movable crown, and a disengaged position in which the disc is disengaged from the movable ring, so as to separate the output ring of the movable ring, a clean retaining piece to retain the disk in the engaged position, and a rupture member adapted to be activated to break the retaining piece, so as to allow movement of the movable disk in the disengaged position. In this way, in normal operating mode, it is the moving disk, and not the retaining piece, which provides torque transmission between the movable ring and the output ring. The only purpose of the retaining piece is to hold the mobile disk in the engaged position. Furthermore, the retaining piece can be broken to order by activating the rupture member, which makes it possible to control with precision the conditions of transition from the normal operating mode to a decoupled mode of operation. These conditions may vary depending on flight control applications.
    [0003] Finally, because of its simplicity, the proposed device is compact. The proposed actuator may furthermore have the following features: in a first possibility, the rupture member comprises a block formed of a shape memory material, the block being able to change shape when subjected to an electric or magnetic field so as to apply a tensile stress on the retaining piece, causing the rupture of the retaining piece, - according to a second possibility, the rupture member comprises a pyrotechnic composition suitable for exploding when subjected to to an electric current, resulting in the rupture of the retaining piece, - the retaining piece has a zone of lesser resistance to break in case of activation of the rupture member, - the zone of least resistance is a zone thinning of the retaining piece, - the coupling mechanism comprises an elastic return member capable of biasing the movable disk towards the disengaged position, - the crown m and the output ring each comprise a toothing, and the movable disk comprises a clean toothing to come into engagement simultaneously with the teeth of the movable ring and the output ring, the teeth of the ring gear, the ring the output and the movable disc have a geometry such that the application of a torque 25 between the movable ring and the output ring produces a spreading force which urges the movable disk towards the disengaged position, - the movable ring comprises a first crown portion and a second crown portion, the coupling mechanism comprising a first movable disc and a second movable disc, the first movable disc being engaged with the first portion of the movable crown and the output ring so as to to make the ring integral with the first part of the mobile ring when the first disk is in the engaged position, and the second mobile disk being in 3028 836 5 engagement with the second portion of the movable ring and the output ring so as to make the ring integral with the second portion of the ring gear when the second disk is in the engaged position, - the retaining piece is adapted to retain the first disc and the second disc in the engaged position, the rupture of the retaining piece allowing a separation of the output ring, the first part of the mobile ring and the second part of the mobile ring, the actuator comprises in addition, an input shaft capable of being rotated by a motor along the axis of rotation, a planet carrier, a plurality of satellites, each satellite being rotatably mounted on the planet carrier and being adapted to mesh. on the one hand with the input shaft, and on the other hand with the fixed crown and the movable ring, and the fixed ring and the mobile ring have a different number of teeth from each other than rte a rotation of the input shaft relative to the fixed ring 15, causes a rotation of the ring gear relative to the fixed ring. The invention also relates to an actuating assembly of an aircraft flight control rudder, comprising an actuator as defined above and a motor capable of driving the rotating input shaft. PRESENTATION OF THE DRAWINGS Other features and advantages will become apparent from the description which follows, which is purely illustrative and nonlimiting, and should be read in conjunction with the appended figures, among which: FIG. 1 schematically represents an aircraft, FIG. 2 schematically represents an actuating assembly of a flight control rudder; FIG. 3 schematically shows in perspective an actuator according to one embodiment of the invention; FIG. FIG. 5 is a sectional view of the actuator along a longitudinal sectional plane AA; FIG. 6 is a detailed view of the coupling mechanism as shown in FIG. in zone B of FIG. 5; FIG. 7 is a perspective view of the coupling mechanism; FIG. 8 is a cutaway perspective view of the coupling mechanism. DETAILED DESCRIPTION OF AN EMBODIMENT In FIG. 1, the aircraft 1 represented is an aircraft comprising a fuselage 2 and control surfaces 3 mounted mobile with respect to the fuselage 2. The control surfaces 3 are fins located at the ends of the wings of the aircraft. the plane. These fins 3 control the rolling motion of the aircraft, that is to say the rotational movement of the aircraft around the longitudinal axis of the aircraft. Each fin 3 is rotatably mounted relative to the fuselage 2, about an axis of rotation extending substantially parallel to a trailing edge of the wing. The adjustment of the position of each fin 3 is provided by an actuating assembly comprising one or more actuator (s) associated with the fin 3. In Figure 2, the actuating assembly 60 shown comprises an electronic control unit 61 (ECU), two actuators 4 and two electric motors 62. The actuators 4 are rotary actuators. Each actuator 4 is connected on the one hand to the fuselage 2 and on the other hand to the rudder 3 and is able to cause the rudder to rotate relative to the fuselage 2 around an axis X. Each actuator 4 is adapted to be driven by an associated electric motor 62, to adjust the position of the fin 3 relative to the fuselage 2. The electric motors 62 are controlled in parallel by the electronic control unit 61.
    [0004] In FIGS. 3 to 5, the actuator 4 represented comprises an input shaft 5, a planet carrier 6, a plurality of satellites 7 and 8, two fixed rings 9 and 10, a mobile ring 11 and a ring of FIG. exit 12.
    [0005] The fixed crowns are fixed to the fuselage 2 of the aircraft, while the output ring 12 is fixed to the rudder 3. The input shaft 5 is rotatably mounted relative to the fixed crowns 9 and 10 around the The axis of rotation X. The input shaft 5 is adapted to be connected to an electric motor 62 (or to a geared motor) for driving the input shaft 5 in rotation with respect to the fixed rings 9 and 10. For this purpose, the input shaft 5 has an end 13 provided with splines 14 connection. On the other hand, the input shaft 5 includes an outer cylindrical surface 15 having a toothed portion 16. The planet carrier 6 is also rotatably mounted about the axis X. The planet carrier 6 supports the satellites 7 and 8, each satellite being rotatably mounted relative to the planet carrier 6 about an axis of rotation X1 to X6 , parallel to the X axis.
    [0006] Each fixed ring 9, 10 comprises an inner cylindrical surface 17, 18 toothed, have a first number of teeth. The movable ring 11 is disposed between the two fixed rings 9 and 10. The movable ring 11 is rotatably mounted relative to the fixed rings 9 and 10 around the axis X. The movable ring 11 comprises an inner cylindrical surface 19 toothed, having a second number of teeth, different from the first number of teeth. More specifically, the movable ring 11 comprises a first portion 21 and a second portion 22. The first portion 21 of the movable ring 11 comprises a first inner surface 23 having first teeth. The second portion 22 includes a second inner surface 24 having second teeth. The first portion 21 and the second portion 22 comprise a number of identical teeth. However, the teeth of the second portion 22 are out of phase with the teeth of the first portion 21 with a phase shift equal to half a tooth. Each satellite 7 and 8 comprises an outer surface 25 having teeth, the teeth of each satellite being adapted to mesh on the one hand with the teeth of the input shaft 5, and on the other hand with the teeth of the teeth. fixed rings 9 and 10 and the mobile ring 11. More specifically, the actuator 4 comprises first satellites 7 and second satellites 8.
    [0007] The satellites 7 and 8 are identical to each other. However, the first satellites 7 are arranged to mesh with the first part 21 of the mobile ring 11 (but not with the second part 22) while the second satellites 8 are arranged to mesh with the second part 22 of the movable ring 11 (but not with the first part 21). For this purpose, the satellites 7 are arranged head to tail relative to the satellites 8. The rotation of the input shaft 5 relative to the fixed rings 9 and 10 has the effect of causing a rotation of the satellites 7 and 8 by relative to the fixed crowns 9 and 10. Due to the difference in the number of teeth between the fixed crowns 9, 10 on the one hand and the mobile crown 11, on the other hand, the rotation of the satellites 7 and 8 causes a rotation of the movable ring 11 relative to the fixed rings 9 and 10. The input shaft 5, the planet carrier 6, the satellites 7 and 8, the fixed rings 9 and 10 and the mobile ring 11 together form an epicyclic reduction gear, for converting the rotation of the input shaft 5 with respect to the fixed rings 9 and 10 in a rotation of the movable ring 11 relative to the fixed rings 9 and 10 at a speed lower than that of the input shaft 5. The phase shift between the teeth of the first part 21 and the teeth 25 of the second part 22 of the movable ring 11 makes it possible to have satellites 7 and 8 with a single tooth configuration. The outlet ring 12 extends around the movable ring 11. The outlet ring 12 comprises orifices 26 and 27, the orifices being formed in diametrically opposite positions of the outlet ring 30. Furthermore, the actuator 4 comprises a coupling mechanism 30 allowing, in normal operating mode, to make the output ring 12 integral with the movable ring 11, and in decoupled operation mode, to separate the output ring 12 from the movable ring 11. The coupling mechanism 30 is shown in more detail in FIGS. 6 to 8.
    [0008] The coupling mechanism 30 comprises a first coupling disc 31, a second coupling disc 32, a retaining assembly 33, a rupture member 34 and resilient return members 35 and 36. The first coupling disc 31 extends around the first portion 21 of the movable ring 11. Likewise, the second coupling disk 32 extends around the second portion 22 of the movable ring gear 11. Each coupling disk 31 and 32 comprises a set of teeth 41. and 42 in the form of an edge having teeth. Furthermore, the first portion 21 of the movable ring 11 comprises a toothing 43, also in the form of an edge having teeth. Similarly, the second portion 22 of the movable ring 11 comprises a toothing 44, in the form of an edge having teeth. The output ring 12 of the actuator 4 also comprises a first toothing 45 (in the form of a first edge having teeth) and a second toothing 46 (in the form of an edge having teeth).
    [0009] The first coupling disk 31 is mounted to move in translation relative to the first portion 21 of the mobile ring 11 in a direction parallel to the axis of rotation X of the actuator. In addition, the first coupling disc 31 is movable between an engaged position (illustrated in the figures) in which the toothing 41 of the first disc 31 is engaged both with the toothing 43 of the first part 21 of the movable ring 11 and with the first toothing 45 the output ring 12, and a disengaged position (not shown) in which the toothing 41 of the first disc 31 is disengaged from the toothing 43 of the first portion 21 of the movable ring 5 and from the first toothing 45 of the output ring 12. In a symmetrical manner, the second coupling disk 32 is mounted to move in translation relative to the second portion 22 of the mobile ring 11 in a direction parallel to the axis of rotation X of 3028836 the actuator. In addition, the second coupling disc 32 is movable between an engaged position (illustrated in the figures) in which the toothing 42 of the second disc 32 is engaged both with the toothing 44 of the second part 22 of the mobile crown 11 and with the second toothing 46 the outlet ring 12, and a disengaged position (not shown) in which the toothing 42 of the second disc 32 is disengaged from the toothing 44 of the second part 22 of the movable ring 5 and with the second toothing 46 of the output ring 12. In this way, when the coupling discs 31 and 32 are in the engaged position, the coupling discs 31 and 32 join the output ring 12 to the two parts 21 and 22 together. of the mobile ring gear 11. Thus, in normal operation, the output ring 12 is integral in rotation with the movable ring gear 11. Because they are engaged with the movable ring 11 and the outlet ring 12, the discs coupling 31 and 32 provide a transmission of torque between the ring gear 11 and the output ring 12. The teeth 41 to 46 of the movable ring 11, the output ring 12 and coupling discs 31 and 32 have a geometry such that the application of a torque between the movable ring 11 and the outlet ring 12 produces a spreading force which urges the coupling discs 31 and 32 towards their disengaged position (arrows A and B). However, the coupling discs 31 and 32 abut against the retaining assembly 33 which prevents the displacement of the coupling discs 31 and 32 to the decoupled position.
    [0010] The retainer 33 includes a first retainer 47 and a second retainer 48 (or pin). The first retaining piece 47 comprises a hollow cylindrical portion 49 and a flange 50. The second retaining piece 48 comprises a cylindrical rod 51 and a flange 52. The rod 51 of the second piece 30 is adapted to be inserted into the first orifice 26 of the output ring 12. In addition, the hollow cylindrical portion 49 of the first retaining piece 47 is adapted to be screwed or crimped onto the rod 51 of the second retaining piece 48 so that the collar 50 of the first retaining piece 47 3028836 11 retains the first disc 31 in the engaged position and the flange 52 of the second piece 48 holds the second disc 32 in the engaged position. In other words, the flange 50 of the first retaining piece 47 prevents the first disc 31 from moving to the disengaged position. Similarly, the flange 52 of the second retaining piece 48 prevents movement of the second disc 32 to the disengaged position. The rod 51 of the second retaining piece 48 has a zone 53 of least resistance. Zone 53 of least resistance is formed by a thinned portion of the shank 51 of the second retaining piece 48, i.e., a portion having a diameter smaller than the diameter of the remainder of the shank. This area 53 of least resistance constitutes a preferred breaking zone of the retaining assembly 33 when the latter is subjected to tensile stress in the direction of the axis X.
    [0011] The rupture member 34 is a member adapted to be activated by an electric or magnetic signal to break the second retaining piece 48. For this purpose, the rupture member 34 comprises two blocks 54 and 55, each block having a C. The blocks 54 and 55 are arranged on either side of the rod 51 of the second retaining piece 48. More specifically, the blocks 54 and 55 are arranged on either side of the area 53 of least resistance. Each block 54, 55 is formed of a shape memory material. Thus, each block 54, 55 is able to change its shape when it is subjected to an electric or magnetic activation field so as to exert a tensile stress on the second retaining piece 48, this constraint being sufficient to cause a break in the second retaining piece 48. The blocks 54, 55 are designed so that the tensile stress exerted on the second retaining piece 48 is directed parallel to the axis X. In an alternative embodiment, the rupture 34 may comprise a pyrotechnic composition capable of exploding when subjected to an activation electric current, causing the second retaining piece 48 to rupture.
    [0012] The elastic return members 35 and 36 consist of a first spring 35 disposed between the first portion 21 of the movable ring 11 and the first coupling disk 31, and a second spring 36 disposed between the second portion 22. of the movable ring 12 and the second coupling disk 32. The spring 35 and 36 may be compression spring. The first spring 35 is arranged to bias the first coupling disk 31 to the disengaged position. In other words, the first spring 35 exerts on the first coupling disc 31 a force 10 tending to move the first coupling disc 31 away from the output ring 12 (in the direction of the arrow A). Similarly, the second spring 36 is arranged to bias the second coupling disk 32 to the disengaged position. In other words, the second spring 36 exerts on the second coupling disc 32 15 a force tending to move the second coupling disc 32 away from the output ring 12 (in the direction of the arrow B, opposite to the direction of the arrow A). . In the embodiment illustrated in FIGS. 3 to 8, the coupling mechanism 30 also comprises a second retaining assembly 33 ', a second rupture member 34' and second elastic return members 35 'and 36'. which are identical to the retaining assembly 33, the rupture member 34 and the elastic return members 35 and 36 described above. The retainer 33 is inserted into the first port 26 of the output ring 12 while the retainer 33 'is inserted into the second port 27 of the output ring 12. The two retainer assemblies 33 and 33 'retain the coupling discs 31 and 32 in the engaged position. In normal operation of the actuator 4, the input shaft 5 of the actuator 4 is rotated about the X axis with respect to the fixed rings 9 and 10 by the electric motor. The rotation of the input shaft 5 causes a concomitant rotation of the satellites 7 and 8 with respect to the fixed rings 9 and 10. Due to the difference in the number of 3028836 13 teeth between the fixed rings 9, 10 and the movable ring 11, the rotation of the satellites 7, 8 causes a rotation of the movable ring 11 relative to the fixed rings 9 and 10. The output ring 12 being integral with the movable ring 11, the outlet ring 12 is also rotated. relative to the fixed crowns 9 and 10. The rotation of the output ring 12 has the effect of moving the flight control rudder 3 relative to the fuselage 2 of the aircraft. In case of detection of jamming of one of the parts of the actuator 4, the actuator 4 is controlled to switch from the normal operating mode to a decoupled operating mode. For this purpose, the rupture members 34 and 34 'are activated by an electrical or magnetic signal. Blocks 54 and 55 subjected to an electric or magnetic field change their shape, thereby exerting a tensile stress on the second retaining piece 48. The tensile stress exerted by the blocks 54 and 55 has the effect of breaking the retainer 48 in its zone 53 of least resistance. Once the second retaining piece 48 is broken, the first coupling disk 31 and the second coupling disk 32 are no longer retained in the engaged position. Under the effect of the restoring force exerted by the first return member 35 (respectively the second return member 36) on the first coupling disk 31 (respectively on the second coupling disk 32), each of the disks 31, 32 moves from the engaged position to the disengaged position. The disc 21 moves in the direction of the arrow A while the disc 22 moves in the direction of the arrow B, opposite. This movement towards the disengaged position is also favored by the geometry of the teeth 41 to 46 of the mobile ring 11, the outlet ring 12 and the coupling disks 31 and 32 which produces a spacer force which is added at the urging of the return members 35 and 36 to move the coupling disks 31 and 32 away from the outlet ring 12.
    [0013] Once the disks 31 and 32 in the disengaged positions, the output ring 12 is disengaged from the mobile ring 11. In addition, the two parts 21 and 22 of the movable ring 11 are disengaged from one another .
    [0014] The actuator 4 is then disconnected from the flight control rudder 3, and the flight control rudder 3 can thus be moved by other actuators. As the retaining assemblies 33 and 33 'are arranged at the output of the transmission chain of the actuator 4, the proposed device makes it possible to obtain a disconnection of the actuator irrespective of the coin seized in the transmission chain.
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. Flight control actuator (4) actuator (3) of an aircraft, comprising: - a fixed crown (9, 10) adapted to be fixed to a fuselage (2) of the aircraft, - a crown (11) movable in rotation with respect to the fixed ring gear (9, 10) about an axis of rotation (X), - an outlet ring (12) adapted to be fixed to the flight control rudder (3), and - a coupling mechanism (30) comprising a disc (31, 32) movable in translation relative to the movable ring (11) in a direction parallel to the axis of rotation (X), the disc (31, 32); being movable between an engaged position in which the disc (31, 32) is in engagement with both the movable ring (11) and the outlet ring (12) so as to make the outlet ring (12) integral with the movable ring (11), and a disengaged position in which the disc (31, 32) is disengaged from the movable ring (11), so as to separate the outlet ring (12) from the ring m obile (11), a retaining piece (47, 48) adapted to retain the disc (31, 32) in the engaged position, and a rupture member (34) adapted to be activated to break the retaining piece (47, 48), so as to allow movement of the disc (31, 32) in the disengaged position. 25
    [0002]
    2. An actuator according to claim 1, wherein the rupture member (34) comprises a block (54, 55) formed of a shape memory material, the block (54, 55) being adapted to change shape when it is subjected to an electric or magnetic field so as to apply a tensile stress to the retaining piece (47, 48), causing the retaining piece to break.
    [0003]
    An actuator according to claim 1, wherein the rupture member (34) comprises a pyrotechnic composition capable of exploding when subjected to an electric current, resulting in the rupture of the retaining piece.
    [0004]
    4. Actuator according to one of claims 1 to 3, wherein the retaining piece (47, 48) has a zone (53) of lesser resistance to rupture in case of activation of the rupture member ( 34).
    [0005]
    An actuator according to claim 4, wherein the area of (53) least resistance is a thinned area of the retaining piece (47, 48).
    [0006]
    6. An actuator according to one of claims 1 to 5, wherein the coupling mechanism (30) comprises an elastic return member (35, 36) adapted to bias the movable disc (31, 32) to the disengaged position.
    [0007]
    7. Actuator according to one of the preceding claims, wherein the movable ring (11) and the output ring (12) each comprise a toothing (43-46), and the movable disc (31, 32) comprises a toothing. (41, 42) adapted to engage simultaneously with the teeth (43, 44, 45, 46) of the movable ring (11) and the output ring (12).
    [0008]
    8. An actuator according to claim 7, wherein the teeth (4146) of the movable ring (11), the output ring (12) and the movable disc (31, 32) have a geometry such that the application of a torque between the movable ring (11) and the output ring (12) produces a spreading force which biases the movable disk (31, 32) towards the disengaged position.
    [0009]
    9. Actuator according to one of claims 1 to 8, wherein the movable ring (11) comprises a first ring portion (21) and a second ring portion (22), the coupling mechanism (30) comprising a first movable disc (31) and a second movable disc 3028836 17 (32), the first movable disc (31) being in engagement with the first part (21) of the movable ring (11) and the output ring (12) of in order to make the ring (12) integral with the first part (21) of the mobile ring (11) when the first disk (31) is in the engaged position, and the second mobile disk (32) being in engagement with the second disk (31). part (22) of the movable ring (11) and the outlet ring (12) so as to make the ring (12) integral with the second part (22) of the mobile ring (12) when the second disk (32) is in the engaged position. 10
    [0010]
    An actuator according to claim 9, wherein the retaining piece (47, 48) is adapted to retain the first disk (31) and the second disk (32) in the engaged position, the rupture of the retaining piece (47, 48) allowing a separation of the output ring (12), the first part (21) of the movable ring (11) and the second part (22) of the mobile ring (11).
    [0011]
    11. An actuator according to one of claims 1 to 10, further comprising: - an input shaft (5) adapted to be rotated by a motor along the axis of rotation (X), - a carrier satellite (6), - a plurality of satellites (7, 8), each satellite (7, 8) being rotatably mounted on the planet carrier (6) and being able to mesh on the one hand with the planet shaft inlet (5), and secondly with the fixed ring (9, 10) and the movable ring (11), in which the fixed ring (9, 10) and the mobile ring (11) have a number of teeth. different from each other so that a rotation of the input shaft (5) relative to the fixed ring (9, 10), causes a rotation of the movable ring (11) relative to the fixed ring 30 (9, 10). 3028836 18
    [0012]
    12. An aircraft flight control rudder actuating assembly (60) comprising an actuator (4) according to claim 11 and a motor (62) for driving the input shaft (5). in rotation.
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    同族专利:
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    FR3066004B1|2017-05-04|2020-09-11|Safran Trans Systems|DECLUTABLE SPEED REDUCER|
    JP6779183B2|2017-07-18|2020-11-04|川崎重工業株式会社|Aircraft steering system with electromechanical actuators|
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    法律状态:
    2015-10-23| PLFP| Fee payment|Year of fee payment: 2 |
    2016-05-27| PLSC| Publication of the preliminary search report|Effective date: 20160527 |
    2016-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2017-01-13| CJ| Change in legal form|Effective date: 20161214 |
    2017-01-13| CD| Change of name or company name|Owner name: SAGEM DEFENSE SECURITE, FR Effective date: 20161214 |
    2017-10-20| PLFP| Fee payment|Year of fee payment: 4 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 5 |
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    2020-10-21| PLFP| Fee payment|Year of fee payment: 7 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1461246A|FR3028836B1|2014-11-20|2014-11-20|ACTUATOR FLIGHT CONTROL ACTUATOR OF AN AIRCRAFT|FR1461246A| FR3028836B1|2014-11-20|2014-11-20|ACTUATOR FLIGHT CONTROL ACTUATOR OF AN AIRCRAFT|
    US15/517,325| US10399669B2|2014-11-20|2015-11-19|Aircraft flight control surface actuator|
    CN201580056247.8A| CN107074346B|2014-11-20|2015-11-19|Aircraft flight control surface actuator|
    PCT/EP2015/077165| WO2016079270A1|2014-11-20|2015-11-19|Aircraft flight control surface actuator|
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