• 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:
    Telescopic actuator comprising: - an actuator body (9); - A sleeve (40) of longitudinal axis (Y) rotatably mounted and extending at least partially within the body, said sleeve being held in axial position in the body by fixing means; - A threaded rod mounted telescopically sliding along the longitudinal axis (X) inside the sleeve (40) and cooperating with the sleeve (40) via a helical link; - Rotating drive means adapted to rotate the sleeve (40) so as to selectively slide the threaded rod between an extended position and a retracted position; - Locking means adapted to render irreversible in retraction the helical connection, so that a retraction of the threaded rod caused by a compressive load is prohibited when such a retraction is not caused by the drive means. Aircraft engine comprising at least one such actuator.
    公开号:FR3014842A1
    申请号:FR1362839
    申请日:2013-12-17
    公开日:2015-06-19
    发明作者:Denis Dauvergne；Jean Lamarre；Louis Chavignier；Mickael Werquin
    申请人:Sagem Defense Securite SA；
    IPC主号:
    专利说明:

    [0001] The invention relates to a telescopic actuator and an aircraft engine. This engine comprises at least one cover of the type of fan cover or thrust reverser cover, and a telescopic actuator of the invention used to open or close the cover. BACKGROUND OF THE INVENTION Some modern aircraft are equipped with several turbojet engine propulsion engines each equipped with a nacelle comprising two fan cowls and two inverter covers. Each hood is articulated by an upper edge to a structure of the nacelle so as to allow an opening and closing of said hood when the aircraft is on the ground. An operator on the ground can thus access the inside of the engine to carry out maintenance operations. The opening and closing of a hood on the ground is carried out thanks to a certain number of engine equipment. Among these devices, there are electromechanical actuators and electrical control boxes adapted to control the electromechanical actuators. The design of such equipment must comply with requirements specified by the aircraft manufacturer which include, on the one hand, "common" requirements specific to any equipment on board the aircraft and, on the other hand, " particular 'relating to the particular use of such equipment and, in particular, to the fact that such equipment is intended to be used when the aircraft is on the ground by a ground operator for maintenance operations. Common requirements include electrical and mechanical interface requirements, reliability, safety, and resistance to various environmental conditions. Specific requirements include operational requirements. For example, an opening 35 of a hood must be able to be performed manually and without any particular tool, by exerting a force on a lower part of the hood to push this lower part of the structure of the nacelle. There are also requirements for the safety of a ground operator performing a maintenance operation. For example, it is important to ensure that a bonnet does not accidentally close, particularly when any compression load is unintentionally applied to the bonnet. In addition, there are requirements regarding the electrical consumption of the electromechanical actuators. Since these actuators are intended to be used when the aircraft is on the ground and its engines are extinguished, the power supply of the actuators comes from an internal or external energy source (fleet group) to the airplane that is suitable to save. The electromechanical actuators used to open or close a hood must therefore have a relatively low power consumption. OBJECT OF THE INVENTION The invention relates to a telescopic actuator 20 meeting the particular requirements mentioned above, as well as an aircraft engine comprising such an actuator. SUMMARY OF THE INVENTION In view of accomplishing this object, there is provided a telescopic actuator comprising: - an actuator body; - A sleeve of longitudinal axis rotatably mounted and extending at least partially within the body, said sleeve being held in axial position in the body by fixing means; A threaded rod mounted to telescopically slide along the longitudinal axis inside the sleeve and cooperating with the sleeve via a helical link; rotary drive means adapted to rotate the sleeve so as to selectively slide the threaded rod between an extended position and a retracted position; - Locking means adapted to render irreversible in retraction the helical connection, so that a retraction of the threaded rod caused by a compressive load is prohibited when such a retraction is not caused by the drive means. The use of the actuator of the invention is particularly advantageous for opening or closing a hood of a propulsion motor of an aircraft. The helical link allows a ground operator to open a hood manually, pushing the bottom of the hood of the structure of the engine nacelle. The locking means, which render the helical connection irreversible, nevertheless make it possible to ensure that the cover does not close accidentally when a closure is not controlled, which makes it possible to ensure the safety of the ground operator. Finally, the helical connection can in particular be achieved by using a ball nut integral with the sleeve and cooperating with the threaded rod. Such a connection has a very low coefficient of friction and therefore a high efficiency: the power consumption of the actuator of the invention is optimized. The invention will be better understood in the light of the following description of a particular non-limiting embodiment of the invention. BRIEF DESCRIPTION OF THE DRAWINGS Reference will be made to the accompanying drawings, in which: - Figure 1 is a perspective view of the engine of the invention, the fan cowls and thrust reverser cowls being closed; FIG. 2 is a view similar to that of FIG. 1 on which the fan cowls and thrust reverser covers of the engine are partially open; - Figure 3 is a perspective view of the actuator of the invention, the threaded rod of the actuator being in an extended position; - Figure 4 is a view similar to that of Figure 3 in which the threaded rod of the actuator is in a retracted position; FIG. 5 is a perspective view of a motor control unit of the invention; FIG. 6 represents an electrical diagram of an electronic card of the actuator of the invention; - Figures 7 and 8 are perspective views of the body of the actuator of the invention; FIG. 9 is a simplified kinematic diagram of the actuator of the invention; - Figure 10 is a sectional view of a mechanical interface of the actuator of the invention; - Figure 11 and Figure 12 show locking means of the actuator of the invention; - Figure 13 is a sectional view of the free end of the threaded rod of the actuator of the invention; Figure 14 is a view similar to that of Figure 13 on which a compressive load exerted on the rod is shown; - Figure 15 is a view similar to that of Figure 13 in which a tensile load exerted on the rod is shown; - Figure 16 is a sectional view of a torque limiter which is equipped with the actuator of the invention. DETAILED DESCRIPTION OF THE INVENTION The aircraft engine 1 of the invention, visible in FIGS. 1 and 2, is an aircraft propulsion engine of the turbojet type. The engine 1 is conventionally provided with a nacelle 2 which comprises a nacelle structure 3, two fan covers 4a located on either side of a vertical plane passing through a longitudinal axis X of the engine and two inverter covers 4b also located on both sides of the vertical plane.
    [0002] Each of these covers 4 is articulated by an upper edge 5 to the structure of the nacelle 3 so as to allow an opening and closing of said hood 4 when the aircraft is on the ground, which allows a ground operator to access to the interior of the engine 1 to carry out maintenance operations. The opening and closing of each of the covers 4 are performed by a telescopic actuator 7 according to the invention. With reference to FIGS. 3 and 4, the telescopic actuator 7 of the invention comprises a threaded rod 8, a body 9 and drive means arranged in such a way that the threaded rod 8 is adapted to move along its longitudinal axis relative to the body 9 under the action of the drive means. This movement of the threaded rod 8 is called sliding in the present description. The body 9 of the actuator 7 is mounted on the structure of the nacelle 3 and the threaded rod 8 has a free end 12 secured to a cover 4, so that a sliding of the rod 8 to an extended position of the rod , visible in Figure 3, causes an opening of the cover 4 and a sliding of the rod to the retracted position, visible in Figure 4, causes a closing of the cover 4.
    [0003] The drive means of each actuator 7 comprise first electromechanical drive means comprising an electric motor 13 and second fully mechanical drive means. The first drive means are adapted to implement an electrical control of the opening and closing of the cover 4 and are connected for this purpose to the power supply devices of the aircraft, while the second means of The drive is adapted to implement a mechanical control available even when no power supply is available.
    [0004] The operation of the electrical control is first described. The electrical control of the actuator 7 is performed via a control unit 14 located in a lower part of the engine 1 so as to be easily accessible by the operator on the ground. The control unit 14 comprises interface means that allow the operator on the ground to control it. These interface means are two switches 16a and 16b of the "SPDT" type (for "Single Pole Double Throw", which can be translated as "two-way bipolar inverter"), including a first switch 16a controlling an opening of the cover 4 and a second switch 16b controlling closing of the cover 4. The control unit 14 provides the telescopic actuator 7 via an electrical connector 17 with a control signal resulting from the operation of the switch 16. It is noted that the switches 16 are electrically connected to each other so that in the case where an opening and closing are simultaneously controlled, the opening is performed in priority.
    [0005] In addition to the electric motor 13, the actuator 7 comprises an electronic card 19 disposed inside the body 9 of the actuator 7 and electrically connected to the motor 13, as well as a first electrical connector 20 and a second electrical connector 21 which are mounted on the body 9 of the actuator 7 and which are electrically connected to the electronic card 19. With reference to FIG. 6, the first electrical connector 20 is intended to connect the electronic card 19 of the actuator 7 to a first power supply device D1 of the aircraft supplying a first supply voltage V1. The first supply voltage V1 is used in a power section of the electronic board 19 intended to generate phase currents of the electric motor 13. first supply voltage V1 is here a three-phase voltage of relatively high amplitude, in this case a voltage of 115 volts AC. The first power supply device Dal of the aircraft is for example a battery or any generator that does not require the propulsion engines of the aircraft to be active in order to generate a voltage and an electric current. The second electrical connector 21 is intended to connect the electronic card 19 of the actuator to a second power supply device Da2 of the aircraft supplying a second supply voltage V2. The second supply voltage V2 is here a relatively low DC voltage, in this case a voltage of 28 volts DC. The second supply voltage V2 is used in a signal portion of the electronic card 19 for processing low-level signals of the electronic card 19. The second electrical connector 21 is further intended to connect the electronic card 19 to the electrical connector 17 of the control unit 14. The electric motor 13 of the actuator 7 is a three-phase synchronous brushless motor with permanent magnets, the phase switching of which is ensured without the use of a position sensor. A rotor of the electric motor 13. The electric motor 13 requires to operate a three-phase sinusoidal supply voltage taken in its phases. The electronic card 19 comprises a first channel 24 connected to the first connector 20, a second channel 25 connected to the second connector 21, an interface module 26 also connected to the second connector 21, and an onverter 27 connected to the electric motor. . The first channel 24 is integrated in the power portion of the electrical board 19, while the second channel 25 is integrated in the signal portion of the electronic board 19. On the first channel 24 are successively connected in series from the first connector 20: a first filter 29 for filtering the first supply voltage V1 and a thermal switch 30 connected to each phase P1, P2, P3 of the first supply voltage V1, a voltage rectifier 31, a second filter 32 for to filter a DC rectified voltage at the output of the rectifier 31, and a current sensor 33. The first supply voltage V1 is received by the electronic card 19 of the actuator 7 via the first connector 20, and is then processed by the first channel 24 so that a rectified and filtered supply voltage Vdc is transformed by the inverter 27 to provide a three-phase voltage network of variable amplitude and frequency e on the motor 13. On the second channel 25, a filter 36 for filtering the second supply voltage V2, a DC voltage converter 37, a control module 38 and a control module, are successively connected in series. 39. The control module 38 is further connected to the current sensor 33 of the first channel 24. The second supply voltage V2 is received by the electronic card 19 of the actuator 7 via the second connector 21, and is then processed. by the second channel 25. The control signal supplied by the control unit 14 is received by the electronic card 19 via the second connector 21 and via the interface module 26. The control module 38 is powered by a voltage of Vc input provided by the second channel 25, and is adapted to control, according to signals provided by the interface module 26 and the current sensor 33, the control module 39. The control module 39 generates q The inverter 27 thus receives the DC supply voltage Vdc and the low level control signals, which enables it to generate voltages. The interface module 26 of the electronic card 19 of the actuator 7 is also used to power the control unit 14 via the second connector 21. the structure and the mechanical operation of the actuator 7 of the invention, in particular in order to better understand the operation of the mechanical control. With reference to FIGS. 3, 4, 7 and 8, the actuator 7 comprises a sleeve 40 with a longitudinal axis Y extending at least partially in the body 9 of the actuator 7. Here, in this case, the sleeve 40 has a reduced length 1, substantially less than the total length L of the sleeve 40, extending in the body 9 of the actuator 7. The sleeve 40 is held in axial position in the body 9 of the actuator 7 by fixing means comprising a fixing body 41 fixed to the body 9 of the actuator 7 by six screws not shown in the figures. The threaded rod 8 is mounted telescopically sliding along the longitudinal axis Y inside the sleeve 40. The threaded rod 8 has a length L 'substantially equal to the total length L of the sleeve 40, and is adapted to slide at the inside of the sleeve 40 between the retracted position, in which the threaded rod 8 extends in its entirety or almost inside the sleeve 40, and an extended position, in which the threaded rod 8 extends 30 in the major part outside the sleeve 40 protruding from an outer end 43 of the sleeve 40. The retracted position of the threaded rod 8 corresponds to a situation in which the cover 4 is completely closed, while the extended position of the threaded rod 8 corresponds to a position in which the cover 4 is fully open.
    [0006] The threaded rod 8 cooperates with the sleeve 40 via a helical link which is here of the ball screw type. The sleeve 40 comprises for this purpose a ball nut 44 located at the end of the outer end 43 of the sleeve 40. The electric motor 13 is adapted to rotate the sleeve 40 via a gearbox 45, visible in FIG. selectively slide the threaded rod 8 between the extended position and the retracted position. The mechanical control mentioned earlier is to act mechanically directly on the gearbox 45, via the second fully mechanical drive means, so as to rotate the sleeve 40 and thus to slide the threaded rod 8 without using the electric motor 13 The gearbox 45 comprises a first, a second, a third and a fourth gearwheel 46, 47, 48, 49 driven in rotation by an output gearwheel 50 of the electric motor 13 and intended to drive in rotation a toothed ring 51 rigidly secured. The first and second gearwheels 46, 47 are mounted around the same first axis A1, while the third and fourth gearwheels 48, 49 are mounted around the same second parallel axis A2. at the first axis A1. The output gear 50 of the motor 13 meshes with the first gear 46 and rotates the second gearwheel 47 via the first gear. Al axis. The second gear 47 meshes with the third gear 48 and rotates the fourth gear 49 via the second axis A2. The fourth gear 49 meshes with the ring gear 51 of the sleeve 40. The second gear 47 is directly mechanically connected to the second drive means which are adapted to drive the second gearwheel 47 in rotation. action on the second driving means rotates the second gearwheel 47 and thus the sleeve 40 via the third gear 48, the fourth gearwheel 49 and the ring gear 51, and thus causes the threaded rod 8 to slide towards the extended or retracted position according to the direction of rotation given to the second gear 47 by the second drive means. The second drive means of a telescopic actuator 7 of the invention used to open or close a fan cowl 4a comprise a flexible shaft 54 extending in a protective sheath 58 running from the rear of the actuator 7 down to the bottom of the engine 1 while walking on the structure of the nacelle 3. A first end 55 of the flexible shaft 54 is directly mechanically connected to the second gear 47, while a second end 56 of the flexible shaft 54 has a mechanical interface 57 adapted to be actuated by the operator on the ground with the aid of a maintenance tool for opening or closing the fan cover 4a.
    [0007] The mechanical interface 57, visible in FIG. 10, here comprises a bent body 59 inside which are arranged a female square end 60 "3/8" (three eighths of an inch), a first conical gear 61 integral with rotation of the female square end 60 and a second conical gear 62 rotatably connected to the flexible shaft 54 and having an axis perpendicular to the axis of the first bevel gear 61. Thus, when the operator drives in rotation With the square female end 60 using a tool with a complementary male square end, the first bevel gear 61 meshes with the second bevel gear 62 which rotates the flexible shaft 54, causing the opening or closing the fan cowl 4a according to the direction of rotation printed at the female square bit 60.
    [0008] The second drive means of a telescopic actuator 7 used to open or close an inverter cover 4b comprise, for their part, a female square end similar to the preceding one (visible in FIGS. 7 and 8), integral in rotation with the second gear wheel of the gearbox and mounted directly on the body 9 of the actuator 7. Thus, to open or close the inverter cover 4b, the operator acts directly with the maintenance tool on the female square end 60 located on the body 9 of the actuator 7. Note that since the helical connection between the sleeve 40 and the threaded rod 8 is a reversible connection, the operator can open one of the covers 4 by applying a force on a part lower cover 4 to push this lower part of the structure of the platform 3. It is however important for the safety of the operator to ensure that the cover 4 can not be closed accidentally, particularly when a compressive force quelc onque is applied involuntarily on the cover 4 open. For this purpose, the actuator 7 comprises locking means 65, visible in FIGS. 11 and 12, adapted to make the helical link irreversible in retraction, so that a retraction of the threaded rod 8 caused by a compressive load is prohibited when such retraction is not caused by the drive means. The locking means 65 are mounted around the sleeve 40 inside the body 9 of the actuator 7 and are located between the ring gear 51 rigidly secured to the sleeve 40 and a bottom 66 of the body 9 of the actuator 7. locking means 65 comprise an annular friction plate 67, an oblique axis roller stopper 68, a ratchet wheel 69 provided with teeth adapted to cooperate with two pawls 70 mounted on the body 9 to pivot, a cylindrical roller stopper 71 consists of a radial roller cage 72 and a thrust washer 73, and a needle bearing 74. The cylindrical roller stop 71 is arranged to transmit to the body 9 of the actuator 7 any axial load exerted on the threaded rod 8 and thus on the sleeve 40. The needle bearing 74 is arranged to transmit to the body 9 of the actuator 7 any radial load exerted on the threaded rod 8 and thus on the sleeve 40. The pawls 70 are arranged to block the ratchet wheel 69 when it rotates in a blocking direction. The friction plate 67 is in abutment with a lower surface 75 of the ring gear 51 and a first ring of the oblique axis roller thrust bearing 68 which comprises a second ring bearing against the ratchet wheel 69. ratchet wheel 69 is supported on the cylindrical roller stop 71 positioned against a first annular surface 76 of the bottom 66 of the body 9 of the actuator 7. The needle bearings 74, meanwhile, are located between the cylindrical roller thrust bearing 71 and a second surface 78 of the bottom 66 of the body 9 of the actuator 7 parallel to the first annular surface 76. When a compressive load is applied to the threaded rod 8 and the drive means are not actuated for to implement a closure of the cover 4 and therefore a retraction of the threaded rod 8, a substantially axial compression force is transmitted from the threaded rod 8 to the sleeve and to the ring gear 51 rigidly secured to the This compressive force is transmitted to the oblique-axis roller thrust 68 which cooperates with the ratchet wheel 69 by generating and applying a friction torque thereon. This friction torque tends to rotate the ratchet wheel 69 in the blocking direction, which is opposed by the pawls 70 which have the effect of blocking the rotation of the ratchet wheel 69 and the rings of the abutment. rollers oblique axes 68, and therefore the sleeve 40: the retraction of the threaded rod 8 is prohibited. When the drive means is controlled to effect retraction of the threaded rod 8 while the compressive load is applied thereto, the drive means must produce a driving torque greater than a driving torque. which is the difference between the friction torque and the reversibility torque generated by the action of the compression load on the helical link. The energy corresponding to the minimum driving torque and coming from the compression load and the drive means is dissipated in the oblique-axis roller thrust 68. On the other hand, when the drive means are controlled to perform an extension of the threaded rod 8 while the compression load is applied thereto, the drive means must produce a torque only greater than the reversibility torque, because the ratchet wheel 69 is not blocked by the pawls 70 and is therefore free to rotate in the corresponding direction of rotation. In this case, no energy is dissipated in the oblique-axis roller thrust 68. It is further noted that in this case, when the extension of the threaded rod 8 is stopped, the threaded rod 8 experiences a slight sliding of retraction resulting from a rotation of the ratchet wheel 69 by an angle equal to half an angle between two teeth of the ratchet wheel 69, the time that the pawls 70 abut against the teeth of the wheel to ratchet ratchet 69. With reference to FIGS. 13 to 15, the free end 12 of the threaded rod 8 which is fixed to the cover 4 associated with the actuator 7 is described. A sliding end 80 is positioned inside the the threaded rod 8 at its free end 12. This sliding tip 80 has a fastening eyelet 81 defining a shoulder 82 and intended to be fixed to the cover 4 and a longitudinal body 83 having a first through hole 84. The longitudinal body 83 is suitable for grout The pin 85, here clip-type, is positioned at the end of the free end of the threaded rod. This pin 85 comprises a ring pierced with a second through hole 86 opening at each of its ends facing the first through hole 84. A cylindrical axis 87 is fitted into the threaded rod 8 through the free end of the threaded rod 8, first through hole 84 and second through hole 86 and extends inside the endpiece perpendicular to the axis Y of the sleeve 40 and thus the threaded rod 8. The sliding end 80 can thus slide inside the threaded rod 8 while being held inside the threaded rod 8 by the cylindrical axis 87. When a compressive load is applied to the eyelet 81, said load of compression being represented by a thick arrow F1 in FIG. 14, the sliding end piece 80 slides inwardly of the threaded rod 8.
    [0009] The shoulder 82 abuts against the free end of the threaded rod 8, while a small space 89 remains between the cylindrical axis 87 of the pin 85 and the wall of the orifice 84 of the longitudinal body 83 of the The compression load is thus directly transferred to the threaded rod 8 and then to the sleeve 40 and to the body 9 of the actuator 7. When a tensile load is applied to the eyelet 81, said tensile load being represented by a thick arrow F2 in FIG. 15, the sliding end 80 slides outwardly from the threaded rod 8. The longitudinal body 83 of the end piece 80 abuts against the cylindrical axis 87. tensile load is transferred to the cylindrical axis 87, to the threaded rod 8 and then to the sleeve 40 and to the body 9 of the actuator 7.
    [0010] Advantageously, with reference to FIG. 16, the telescopic actuator of the invention 7 includes a torque limiter 90 intended to ensure that the actuator 7 can not exert a force greater than a predetermined maximum force. Torque limiter 90 is a slip clutch which cooperates directly with second gear 47 and with third gear 48 of gearbox 45 of telescopic actuator 7. Third gear 48 is positioned between an annular support plate 91 forming a first jaw rigidly secured to the second axis A2 and an annular support plate 92 forming a second sliding jaw on the first jaw. The torque limiter further comprises Belleville washers 93 forming a compression spring and an adjustment nut 94 tightened with a certain tightening torque to preload the compression spring. The compression spring tends to press the support plate 92 against the third gear 48 and thus to create a grip force between a first friction face 95 of the third gear 48 and the annular plate 91 and between a second face friction device 96 of the third gear wheel 48 and the plate 92. When the torque applied at the level of the second gear wheel 47 or the third gear wheel 48 is too large and exceeds a predetermined slip torque, the third gear wheel 48 slides. against the annular support plate 91 and therefore no longer causes the second axis A2 and thus the fourth gear 49 to rotate. The value of the predetermined slip torque, on which the value of the predetermined maximum force depends directly, can be adjusted by adjusting nut 94: the larger the spring clamping torque, the greater the predetermined slip torque. The invention is not limited to the particular embodiment which has just been described, but quite the contrary covers any variant within the scope of the invention as defined by the claims.
    权利要求:
    Claims (13)
    [0001]
    REVENDICATIONS1. Telescopic actuator comprising: - an actuator body (9); - A sleeve (40) of longitudinal axis (Y) rotatably mounted and extending at least partially within the body, said sleeve being held in axial position in the body by fixing means; a threaded rod (8) mounted telescopically sliding along the longitudinal axis (X) inside the sleeve (40) and cooperating with the sleeve (40) via a helical link; rotational drive means adapted to rotate the sleeve (40) so as to selectively slide the threaded rod (8) between an extended position and a retracted position; locking means adapted to make the helical connection irreversible, so that retraction of the threaded rod (8) caused by a compressive load is prohibited when such retraction is not caused by the means drive.
    [0002]
    2. telescopic actuator according to claim 1 wherein the helical connection is of the ball screw type.
    [0003]
    Telescopic actuator according to one of the preceding claims, wherein the drive means comprise an electric motor (13) located in the actuator body and adapted to rotate the sleeve via a gear (45).
    [0004]
    The telescopic actuator according to claim 3, wherein the drive means further comprises a flexible shaft (54) cooperating with the gearbox (45) and intended to be actuated manually to rotate the sleeve.
    [0005]
    5. telescopic actuator according to one of revendi35 cations 3 or 4 further comprising a torque limiter (90) cooperating with the gear (45).
    [0006]
    6. telescopic actuator according to one of the preceding claims, wherein the locking means comprise a ratchet wheel (69) cooperating with the sleeve and at least one pawl (70) adapted to lock the wheel when it rotates in a blocking direction.
    [0007]
    The telescopic actuator according to claim 6, wherein the locking means further comprises an oblique-axis roller stopper (68) cooperating with the ratchet wheel and generating frictional torque when a compressive load is applied. on the threaded rod (8), said frictional torque tending to rotate the ratchet wheel in the locking direction and thereby causing rotational locking of the sleeve. 15
    [0008]
    8. telescopic actuator according to one of the preceding claims, wherein the threaded rod (8) has a free end inside which is mounted a sliding end.
    [0009]
    Telescopic actuator according to claim 8, wherein the sliding end has an eyelet (81).
    [0010]
    The telescopic actuator according to one of claims 8 or 9, wherein the sliding tip is held within the threaded shank (8) so that when a compression load is applied to the nipple. endpiece, this compression load is directly transferred to the threaded rod (8) and the sleeve (40).
    [0011]
    11. A turbojet type aircraft engine comprising at least one hood (4) such as a fan cowl or a thrust reverser cowl, the engine further comprising a telescopic actuator according to one of the preceding claims and a control (14) for controlling the telescopic actuator, the threaded rod of the telescopic actuator cooperating with the hood so that a sliding of the rod towards the extended position causes an opening of the hood and a sliding from the rod to the retracted position causes ducapot closure.
    [0012]
    12. Aircraft engine according to claim 11, wherein the control unit comprises interface means adapted to be actuated manually by a ground operator to control the control unit so as to control an opening or closing hood.
    [0013]
    13. Aircraft engine according to one of claims 11 to 12, comprising two fan cowls (4a) and two thrust reverser cowls (4b), the engine further comprising a telescopic actuator according to one of the claims. 1 to 10 associated with each cover for controlling an opening or closing of the cover and a control unit associated with each telescopic actuator for controlling the telescopic actuator associated with said cover.
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    同族专利:
    公开号 | 公开日
    WO2015040170A2|2015-03-26|
    WO2015040170A3|2015-07-16|
    CN105555665A|2016-05-04|
    FR3014842B1|2017-12-01|
    US20160229546A1|2016-08-11|
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    FR3063532B1|2017-03-06|2019-04-05|Safran Electronics & Defense|ACTUATOR EQUIPPED WITH A NO BACK SYSTEM WITH INHIBITION AREA|
    US20180266530A1|2017-03-15|2018-09-20|Don Alfano|Electro-mechanical linear actuator|
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    法律状态:
    2015-11-23| PLFP| Fee payment|Year of fee payment: 3 |
    2016-11-21| PLFP| Fee payment|Year of fee payment: 4 |
    2017-02-17| CD| Change of name or company name|Owner name: SAFRAN ELECTRONICS & DEFENSE, FR Effective date: 20170111 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 5 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 8 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1362839A|FR3014842B1|2013-12-17|2013-12-17|TELESCOPIC ACTUATOR AND AIRCRAFT ENGINE COMPRISING SUCH ACTUATOR|FR1362839A| FR3014842B1|2013-12-17|2013-12-17|TELESCOPIC ACTUATOR AND AIRCRAFT ENGINE COMPRISING SUCH ACTUATOR|
    PCT/EP2014/070014| WO2015040170A2|2013-09-19|2014-09-19|Telescopic actuator and aircraft engine comprising such an actuator|
    CN201480051686.5A| CN105555665A|2013-09-19|2014-09-19|Telescopic actuator and aircraft engine comprising such an actuator|
    US15/022,833| US20160229546A1|2013-09-19|2014-09-19|Telescopic actuator and aircraft engine comprising such an actuator|
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