法国专利FR3045743A1 HYDRAULIC ROTO-LINEAR PUSH-INVERTER AND VARIABLE SECTION TUBE ACTUATOR

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专利摘要:
The present invention relates to a hydraulic actuator (1) for alternately sequenced actuation of an aircraft turbojet engine nacelle thrust reverser cowl (5) and alternatively of variable-section secondary nozzle panels or (3) flaps of said nacelle, comprising: - a body (100) adapted to be mounted on a fixed structure (7) of a thrust reverser; - A rod (300), mounted in said body and adapted to be connected, on the one hand, to a cover (5) of said inverter and, on the other hand, to a panel (3) or secondary nozzle flap; said actuator being remarkable in that the body (100) comprises means for moving the rod (300) alternately in translation relative to said body (100), so as to cause the translation of a cover (5) of the thrust, or rotation relative to said body (100), so as to cause rotation of a panel (3) or secondary nozzle flap.
公开号:FR3045743A1
申请号:FR1562676
申请日:2015-12-17
公开日:2017-06-23
发明作者:Coq Vincent Le
申请人:Aircelle SA；
IPC主号:

专利说明:

The present invention relates to the field of thrust reverser hood actuator actuators for aircraft turbojet nacelle, and movable nacelle variable section secondary nozzle movable panel actuators, and more specifically relates to a mutualized hydraulic actuator permitting a sequential actuation of such inverter covers and nozzle panels. The invention also relates to an assembly comprising an actuator and a hydraulic control device of said actuator, as well as a nacelle for an aircraft turbojet engine comprising such an assembly.
An aircraft is driven by several turbojet engines each housed in a nacelle also housing a set of ancillary actuating devices related to its operation and providing various functions when the turbojet engine is in operation or stopped.
These auxiliary actuation devices include, in particular, a mechanical thrust reversal system and a variable nozzle system.
The role of a thrust reverser is, during the landing of an aircraft, to improve the braking capacity thereof by redirecting forward at least a portion of the thrust generated by the turbojet engine. In this phase, the inverter makes it possible to return to the front of the nacelle all or part of the gas flows ejected by the turbojet engine, thereby generating a counter-thrust which is added to the braking of the wheels of the aircraft. . To do this, a thrust reverser comprises on either side of the nacelle a movable cover movable between, on the one hand, an extended position which opens in the nacelle a passage for the deflected flow during a braking phase and, on the other hand, a retraction position which closes this passage during normal operation of the turbojet or when the aircraft is at a standstill.
The movable hoods can perform a deflection function or simply activate other means of deflection.
In the case of an inverter with deflection grids, the reorientation of the air flow is carried out by deflection grids, associated with inversion flaps which block a part of the air circulation duct, the hood having a simple sliding function to discover or cover these deflection grids.
Moreover, in addition to its thrust reversal function, the sliding cowl belongs to the rear section and has a downstream side forming the ejection nozzle for channeling the ejection of the air flows. In the case of a toggle switch, the sliding cowls are moved by actuators synchronized with each other and equipped with locks for holding position closed in flight. In the case of such a hydraulically operated inverter, the hydraulic actuators incorporate internal screws which rotate as their hydraulic rod is translated. The rods are locked in rotation by connecting yokes to the movable cowl, and the displacement is effected by a pure translation of the jack rods. A return device and connection by flexible cables with multiple winding ply connect the actuator screws together at the fixed structure. The translational movement of the actuators is thus synchronized, with the stiffness near the flexible cables which enslave a homogeneous rotation of the screws. The optimal section of the ejection nozzle can be adapted according to the different flight phases, namely the take-off, climb, cruise, descent phases.
It should be noted that the operating phases of the variable nozzle and the thrust reverser are distinct, the variable nozzle not being actuated when the inverter is activated on landing.
Among the different embodiments of ejection nozzles known from the prior art, it is in particular known to achieve the variation of outlet section of the nozzle from one or more movable elements, such as pivoting flaps.
In order to actuate the adaptive nozzle independently of the thrust reversal means, in particular during take-off, each moving part (inverter cover / nozzle flaps) is moved by a set of separate actuators for these two movements. This is particularly the case of the actuation system described in document GB 2 449 281, in which the actuation of the nozzle is carried out by an actuator having a telescopic rod displaceable in translation through a screw system. nut and whose screw is rotated by a motor secured to a fixed part of the nacelle, the inverter cover being driven in translation by a set of independent actuators. A disadvantage of this embodiment is to have duplicate activation control means between the movement of the inverter and the movement of the nozzle actuation. In addition, the provision of energy and measurements of the hood or the variable nozzle flaps is made difficult because it travels through the inverter cover, which will itself move the landing.
In order to lighten the mass of the nacelle, it has been proposed to use a single actuator comprising appropriate locking / unlocking means of the adaptive nozzle on the sliding inverter cover, thus allowing a sequential displacement of the inverter cover. and the nozzle, with a single actuator.
The document GB 2,446,441 describes such a control architecture for operating both a thrust reverser device associated with a variable nozzle device, and to provide an actuator comprising two concentric pistons movable in translation, the first piston. being engaged with the inverter cover, and the second piston being connected to the nozzle, each piston being hydraulically controlled independently of one another.
This solution is particularly complex to achieve. Moreover, in this double translation solution, the guiding of two mobile elements poses problems of retrofitting radial degrees of freedom because of the relative play of the inverter cover vis-à-vis its guide rails and because of aerodynamic deformations.
The present invention aims at solving the drawbacks of the prior art, and for this purpose concerns a hydraulic actuator for alternately sequenced actuation of an aircraft turbojet engine nacelle thrust reverser cowl and alternatively nozzle panels or shutters. variable-section secondary section of said nacelle, comprising: - a body adapted to be mounted on a fixed structure of a thrust reverser; a rod, mounted in said body and adapted to be connected, on the one hand, to a hood of said inverter and, on the other hand, to a secondary nozzle panel or flap; said actuator being remarkable in that the body comprises means for moving the rod alternately in translation relative to said body, so as to cause the translation of a thrust reverser cover, or in rotation relative to said body, so as to to cause the rotation of a secondary nozzle panel or flap.
Thus, thanks to the present invention, the movements and locking members are similar to a conventional inverter system when the inverter is controlled.
Moreover, the remote rotation of the screws to orient the panels or shutters of the secondary nozzle does not require a slide connection external to the actuator.
Again, the hydraulic supply for the rotation and the measuring means are directly returned to the fixed body of the cylinder, stationary relative to the fixed structure of the nacelle. It is therefore not necessary to use complex storage devices race or over-length, as is the case in the prior art.
Finally, the kinematic connection between the rod of the actuator and the reverser cowl consists, on the one hand, in locking in translation and, on the other hand, in a fixed rotational movement apart from this point. It is therefore not necessary to use additional backlash recovery device during movements of the inverter hood in flight induced by the variation of the turbojet engine flow pressure.
According to optional features of the actuator according to the invention: the actuator comprises means adapted to return the translation and rotation movement of the rod of said actuator to an actuator external to said actuator, in a synchronized manner; the means for moving the rod in rotation comprise: a longitudinal groove arranged inside the rod; a rotating internal shaft, locked in translation relative to the body, and comprising a slide engaging said groove; o means for rotating said internal axis; the means for rotating the internal axis comprise: a rotary piston, engaged with said internal axis; o means for rotating said piston. the means for rotating the piston comprise: a first set of teeth arranged outside the piston; o a set of teeth, arranged inside the body, and engaged with the teeth of the piston; a plurality of orifices CW and CCW for introducing a fluid, arranged in said body, on either side of said piston, the piston being engaged with said internal axis by means of a second set of toothings, arranged at the interior of the piston, and engaged with a set of teeth, arranged outside the internal axis; the teeth are helical gears with single or multiple pitches; - The teeth are helical gears with reverse pitch. the actuator further comprises a spring arranged to oppose the displacement of the piston in one of the directions of displacement of said piston; the means for returning the translation and rotation movement of the actuator rod to an actuator external to said actuator comprise: a synchronization screw, comprising a set of teeth, arranged outside said screw; a nut, mounted inside the rod, and engaged with the set of teeth of said screw; a worm and worm system adapted to receive a flexible shaft system for connecting the wheel and worm system of the actuator to a wheel and worm system of said device external to said actuator; o a set of rotary bearings, supporting said screw, said bearings being arranged on either side of said wheel and worm system, so as to lock in translation the synchronization screw relative to the actuator body.
The present invention also relates to an actuating system comprising at least one actuator according to the invention, and a hydraulic control device of said at least one actuator, remarkable in that the hydraulic control device is adapted to control the movement of the rod. the actuator alternately in translation relative to said body, so as to cause the translation of a thrust reverser cover, or in rotation relative to said body, so as to cause the rotation of a nozzle panel or flap secondary.
According to optional features of the actuation system of the invention: the actuation system comprises a hydraulic supply doubled by hydraulic supply circuits and control units supplying actuators adjacent to an inverter cover, for rotate the actuator stem; the control units comprise a three-way servovalve supplying the actuator body via the orifice CW and an isolation valve supplying the actuator body via the orifice CCW; - alternatively, the control units are equipped with four-way servo valves; the control units can be equipped with "all or nothing" solenoid valves able to pressurize the actuator via the orifice CW or the orifice CCW; - The actuating system comprises at least one shockproof safety valve, for discharging the pressures induced by undesirable forces nozzle panels or flaps; Finally, the invention relates to a nacelle for an aircraft turbojet, comprising a thrust reverser and a variable section secondary nozzle comprising a plurality of panels or flaps movable in rotation, comprising at least one actuating system according to the invention, said actuating system supplying a plurality of actuators, the nacelle being remarkable in that: the body of the actuator is mounted on a fixed structure of the thrust reverser; the rod of the actuator is connected, on the one hand, to a hood of the said inverter and, on the other hand, to a panel or flap of the said secondary nozzle, via a device for returning the movement of the actuator to the panel or nozzle flap.
According to the invention, the nacelle comprises a flexible shaft connected between a first actuator of the inverter cover, and a second actuator of said cover, adjacent to said first actuator, arranged to synchronize the translation and rotation movement of the rod of the first actuator. with that of the second actuator.
Finally, the nacelle according to the invention advantageously comprises a complementary flexible shaft connecting: - the movement of the first actuator movement device to the nozzle panel, and - the movement of the second actuator movement device to the nozzle panel, said flexible shaft complementary arrangement being arranged to synchronize the movement of the movement-returning device with that of the movement-returning device. Other features, objects and advantages of the present invention will appear on reading the following description and on examining the appended figures in which: FIG. 1 illustrates the actuator according to the invention shown in position retracted, connected to a nozzle panel of variable section of a turbojet engine nacelle; FIGS. 2 to 4 illustrate the operation of the actuator of FIG. 1, FIG. 2 showing the actuator in a position identical to that represented in FIG. 1, FIG. 3 being a view similar to that of FIG. in a position in which the rod has been rotated and Fig. 4 is a view similar to that of Fig. 1, in a position in which the actuator rod has been stretched; - Figure 5 shows a hydraulic control device supplying a set of actuators of the invention.
Throughout the figures, identical or similar references represent identical or similar organs or sets of members.
Referring to Figure 1, illustrating an actuator 1 according to the invention, shown in the retracted position. The actuator shown in FIG. 1 is connected in its downstream part to a variable-section nozzle panel 3 of a turbojet engine nacelle, via a device for returning motion 4. The actuator 1 is intended to be connected on the one hand to the nozzle panel 3, and on the other hand to an inverter cover 5 (visible in FIG. 5). Note that in the present application, upstream and downstream are defined with respect to the direction of flow of air in the propulsion unit in direct jet operation, the air inlet being located upstream relative to at the ejection nozzle, located downstream of the nacelle. The actuator 1 comprises a typically cylindrical body 100. The body 100 is connected to a fixed structure 7 of a thrust reverser. The fixed structure 7 of the thrust reverser may designate a front frame of the thrust reverser or any other fixed part of the inverter relative to the moving cowl of the thrust reverser. The connection between the body 100 and the front frame can in particular be achieved by means of a cardan (not shown).
The body 100 may be constituted by a unitary assembly, as shown in FIG. 1, or may furthermore contain a cylinder fixedly attached to the body, for example by virtue of a ring / nut system, the seal between the cylinder and the body 100. being made for example by means of a static seal.
The body 100 defines in its internal part a first cavity 105 and a second cavity 107 hermetically closed to each other for example by means of a dynamic seal 103 located in downstream part of the first cavity 105. The seal 103 may be mounted on an axis internal rotating 400 which will be discussed in the following description.
The upstream portion of the first cavity 105 is delimited by a stop 110. The first cavity 105 has two orifices CW and CCW for entering a fluid under pressure when the actuator 1 is connected to a hydraulic control device, for example the hydraulic control device 9 shown in Figure 5 which will be described in the following description. The cavity 105 is provided with a set of teeth 101. The teeth 101 are arranged inside the cavity 105, that is to say on an inner wall 106 of the cavity 105, over a length that can correspond substantially at half the length of this cavity. The teeth 101 may be trapezoidal teeth.
The second cavity 107 has a first chamber 107a and a second chamber 107b hermetically closed to each other by means of a flange 311 sealed on a rod 300 substantially concentric with the cavity 107 and adapted to be driven in translation or in rotation according to the invention, as will be seen in the following description. The second cavity 107 of the body 100 has an opening 109 arranged in an axial return 112 provided at a downstream end of said body 100. The opening 109 is intended for the passage of the rod 300. The axial return 112 comprises a dynamic seal 113 which seals at the downstream portion of the second cavity 107 when the rod 300 moves relative to the cavity 107. The second cavity 107 has three orifices B, D and S inlet of a fluid under pressure when the actuator 1 is connected to the hydraulic control device 9.
According to the invention, the rod 300 of the actuator is adapted to be driven alternately both in translation and in rotation relative to the body 100, by means adapted to be described in the following description.
The rod 300 of the actuator 1 is partially housed in the second cavity 107 of the body 100, the end of this rod 300 passing through the opening 109 of the body 100. The rod 300 of the actuator 1 comprises a downstream end 307 comprising connecting means on the one hand to the inverter cover 5 (shown in FIG. 5) and on the other hand to the nozzle panel 3. The end 307 of the rod 300 comprises for this purpose a rotary bearing 302 intended to be fixed on the inverter cover 5 in order to allow a displacement in translation of the cover when the rod 300 is translated relative to the body 100 of the actuator. The end 307 of the rod 300 also has a terminal toothing 309 intended to be engaged with a wheel 11 tangent to the rod 300 and belonging to the motion-deflecting device 4, the wheel 11 being able to be engaged with a transmission system. connecting rods arranged to allow a rotational movement of the panel 3 about an axis of rotation 13 when the rod 300 is rotated about its longitudinal axis.
As previously mentioned, the rod 300 comprises a tight flange 311 fixed on the rod 300, for example at an upstream end of the rod 300. The flange 300 is shaped to delimit the first and second chambers 107a and 107b of the second cavity 107 of the body 100, and is adapted to seal these first and second chambers 107a and 107b. The flange 311 is sealed for this purpose for example by means of a dynamic seal 305. The flange further comprises a ramp 306 arranged so that a segment locking assembly 700, stopped in translation on the body 100 of the actuator, but able to move radially, which allows or prevents the translation of the rod 300.
The segment locking system 700 includes a guiding cap 707. The segment locking system 700 includes a spring 706 for automatically pre-positioning segments 709 so as to automatically arm a locking sequence in translation of the shaft 300. For this purpose, the guiding cap 707 comprises a set of stepped linear dynamic joints 701, 702 so that the cap can move under pressure against the spring 706.
The rod 300 also has at its inner part one or more grooves 301 (two are shown in Figure 1). The grooves 301 are for example profiled from the downstream end of a nut 303 also mounted inside the rod, to an upstream portion of the end 307 of the rod 300.
The grooves 301 receive sliders 405 rigidly connected to the internal axis 400, for example by means of a screw (not shown) operating in each groove 301 of the rod 300. The sliders 405 are shaped to allow movement of the rod 300 in translation relative to the internal axis 400. The internal axis 400 passes through the entire body 100 of the actuator 1. The inner axis 400 is locked in translation against rotary bearings 411 abutting against the stop 110 of the body 100. The internal axis 400 comprises a rod 401 extending substantially from the slides 405 to a portion of the axis 400 having a set of teeth 402 arranged outside the internal axis 400. The axis internal 400 is adapted to be rotated relative to the body 100 of the actuator by means of the teeth 402 preferably trapezoidal which engage with teeth 902 of a rotary piston 900. Of course, any other system adapted to turn the rod 400 can be considered instead of the teeth 402 which engage with the teeth 902 of the rotary piston 900. When the internal axis 400 is rotated, the sliders 405 of the internal axis 400 which engage the grooves 301 profiled in the inner part of the rod 300 cause a rotational movement of the rod 300. Similarly, as long as the internal axis 400 is not driven in rotation by the piston 900, which can be held in abutment with the body 100, either by springs 906, or by the pressurization of the first cavity 105 by the orifice CW, the axis internal 400 remains locked in rotation and the slides 405 of the inner shaft 400 thus prevent any rotation of the rod 300. As regards the rotary piston 900, this piston is housed in the first cavity 105 of the body 100 of the actuator 1 The piston 900 has an opening 905 arranged in an axial return 909 provided at an upstream end of the piston 900. The opening 905 is intended for the passage of the internal axis 400, to both allow a connection to the bearing. rotary 411, and also allow a measurement of rotation of the internal rotational axis, therefore the movement of the panels or flaps of secondary nozzle, necessary for the control system.
The piston 900 comprises a set of teeth 901 arranged outside the piston, that is to say at an outer wall 908 of the piston 900. These teeth 901 are engaged with the set of teeth 101 arranged inside the cavity 105 of the body 100. The teeth 901 may be helical gears with single or multiple steps.
The piston 900 further comprises a set of teeth 902 arranged inside the piston, at an inner wall 910 of the piston 900. The teeth 902 are engaged with the set of teeth 402 arranged outside the piston. the internal axis 400. The teeth 902 may be trapezoidal teeth. The teeth 902 ideally have a different pitch and reverse that provided for the teeth 901.
The piston 900 is shown in FIG. 1 against the upstream stop 101 of the body 100. As will be seen in the remainder of the description, the piston 900 is driven by a simultaneous movement of rotation and translation by the helical profile. teeth 901 when the piston 900 is subjected to a differential pressure between the inlet ports CW and CCW.
The displacement of the piston in the body 100 can be maintained in a balanced position by adjusting the differential pressure of the fluid which enters the cavity 105 of the body 100 through the orifices CW and CCW. In a complementary or alternative way to the blocking of the movement of the piston by adjustment of the differential pressure, the movement of the piston can be blocked as desired at the stop by the effect of the spring 906 and / or the pressurization only in the orifice CW, for press the piston 900 into abutment of the body 100 and thus immobilize its rotation. Other types of piston locking devices may be provided, such as translatant locking pins or electrically or hydraulically operated low pressure brakes (not shown here).
A rotary dynamic seal 903 is mounted between the piston 900 and the internal axis 400, at the opening 905 of the piston 900. A rotary dynamic seal 907 is mounted between the outer wall 908 of the piston 900 and the inner wall 106 of the cavity 105 of the body 100 to separate the two pressures connected to the orifices CW and CCW.
Similarly, a rotational dynamic seal 904 may be provided between the inner wall 910 of the piston and the inner axis 400 to create differential sections between the orifices CW and CCW for control.
According to the invention, the actuator 1 of the invention is furthermore equipped with means for returning the translation and rotation movement of the rod 300 of the actuator 1 to a device external to said actuator, for example an actuator 1 ' (Visible in Figure 5) adjacent to the actuator 1 and used to move the inverter cover 5. As known to those skilled in the art, actuators of the same inverter cover can be mechanically synchronized by flexible shafts 15 (visible in Figure 5) commonly referred to as "flexshaft" in English terminology.
In order to return the translation and rotation movement of the rod 300 of an actuator 1 to an actuator 1 '(visible in FIG. 5), the flexible shaft 15 is driven by a wheel and worm system comprising a wheel 600 engaged with a worm 504.
According to the invention, the wheel 600 is traversed by a synchronization screw 500 comprising a rod 505, borne on the one hand by a set of bearings 502 in downstream part of the rod 505, and on the other hand by a set of bearings rotating 503 in the upstream portion of the rod 505. The bearings 502 are preferably arranged inside the rod 300. The synchronizing screw 500 is locked in translation relative to the body 100 of the actuator 1 by means of the rotary bearings 503 , mounted on either side of the wheel 600. The rod 505 of the synchronizing screw 500 is also traversed by the internal axis 400, the internal axis 400 being able to rotate freely inside the synchronization screw 500.
The rod 505 of the synchronizing screw 500 comprises a set of teeth 501, arranged outside the rod 505 of said screw 500. The teeth 501 can be trapezoidal. The teeth 501 are engaged with the nut 303 mounted inside the rod 300, so that a translational movement of the rod 300 drives via the nut 303 and the teeth 501 a displacement of the synchronization screw 500 rotating about its longitudinal axis. Similarly, when the rod 300 is rotated, the synchronizing screw is also rotated.
Such a rotational movement of the synchronizing screw 500 causes a rotational movement of the wheel 600 thanks to the rotary bearings 503, the rotation of the wheel 600 causing a rotation of the worm 504 which meshes with the wheel 600.
Complementary flexible shafts 29 (visible in FIG. 5) may be provided to directly synchronize the rotation of the wheel 11 of the movement-redirecting device 4 in engagement with the actuator 1, with a wheel 11 of the movement-redirecting device 4 in engagement with an adjacent actuator 1 ', in order to allow a redundancy of the force passage in the event of a failure of the actuator 1, such a failure possibly occurring in particular during a rupture of the internal shaft 400 of the actuator.
The operation of the actuator 1 will now be described with reference to Figs. 2 to 4 referred to herein. The actuator 1 is at rest (FIG. 2), that is to say that the inlet ports for pressurized fluid do not receive pressurized fluid. The segments 709 are engaged with the ramp 306 of the flange 311 of the rod 300, which blocks the translation of the rod 300 relative to the body 100 of the actuator. The inverter cover (not shown) is thus locked in translation. The internal axis 400, which is locked in translation against the bearings 411 by the effect of the spring 906 and / or the pressurization of the cavity CW, these bearings abutting against the stop 110 of the body 100 of the actuator, is also locked in rotation due to the conjugate teeth 101, 901 and 402 and 902.
When the axis 400 is locked in rotation, the rotation of the rod 300 is also prevented by the sliders 405 of the internal axis 400 which engage the grooves 301 of the rod 300.
Referring now to Figure 3 showing the actuator 1 in a position in which the rod 300 has been rotated.
In order to drive the rod 300 in rotation and consequently to control the displacement of a panel 3 of the variable nozzle via the movement-returning device 4, the inlet pressure of the fluid in the cavity 105 is adjusted. of the body 100, through the orifices CW and CCW connected to the hydraulic control device 9 (shown in FIG. 5).
By introducing pressurized fluid through the orifice CCW, the piston 900 is set in translation and in simultaneous rotation in the body 100 thanks to the teeth 901 in engagement with the teeth 101 of the body 100. The translational movement of the piston 900 causes the internal axis 400 rotated relative to the piston 900 through the teeth 902 of the piston 900 meshing with the teeth 402 of the internal axis 400, the translation the rotary axis being blocked by the bearing 411. Thus the internal axis 400 rotates doubly relative to the body 100, because it rotates on the one hand relative to the piston 900 which itself rotates relative to the body 100, and the two rotations are summed algebraically. By reversing the pitch of the helical helical gears 101, 901 and 902, 402, the two rotations are added in the same direction, for a stroke of the rotated piston 900 minimized. The rotation of the internal axis 400 causes the rotation of the rod 300 by the slides 405 of the internal axis 400 which engage the grooves 301 of the rod 300. The rod 300 is in turn still locked in translation relative to the body 100 of the actuator through the segments 709 which engage the ramp 306 of the flange 311 of the rod. The rotation of the ramp 106 can either slide on the segments 709, or the segments 709 are rotated by friction and rotate on a rotary axial stop (not shown in the figure) relative to the body 100.
The rotation of the rod 300 of the actuator drives, via its end teeth 309 at its end 307, the wheel 11 of the movement return device 4, tangent to said rod and engaged with the linkage system arranged to allow the rotating movement of the panel 3 about its axis of rotation 13, so as to adjust the outlet section of the nacelle.
Of course, any other motion-diverting device may be used to transmit the rotational movement of the actuator stem to the variable nozzle panel to cause this panel to rotate.
The rotary piston stroke remains modest because of the differential pitch of the helical gears 901 and 902 of the piston 900, which makes it possible to obtain a small rotation of the nozzle panels 3 (90 to 300 ° for example). Furthermore, the wheel 11 of the movement of the device 4 and the terminal gear 309 of the screw 300 of the actuator allow slow rotation of the nozzle panels 3, under a significant torque. The rotating internal axis 400 can be equipped with a rotation detection system ("RVDT" or "resolver") to measure the precise rotation. In this way, the position measurement of the panels 3 or flaps can be used in an angular position control loop which continuously modulates the pressure in the cavity 105 at the orifices CW and CCW, controlling the movement of the rotary piston 900, therefore the rotations of the internal axis 400 and therefore the panels 3 or flaps of the nozzle, relative to a desired steering setpoint of the panels or flaps of the secondary nozzle according to the flight phase, as described below.
At the same time, while the rod 300 rotates and its translation remains blocked by the segments 709, it rotates the synchronizing internal screw 500 of the actuator, which rotates the wheel 600 and the tangent screw 504 The flexible shafts 15 thus rotate simultaneously during the rotation of the rod 300. As the actuators 1 and 1 '(visible in Figure 5) are controlled simultaneously, the rotations of their respective return screw 504 compare and synchronize through the flexible shaft 15, causing uniform rotations of all panels 3 or nozzle flaps.
As indicated above, the complementary flexible shafts 29 (visible in FIG. 5) can be provided to directly synchronize the rotation of the wheel 11 of the movement-redirecting device 4 in engagement with the actuator 1, with a wheel 11 of the 4 'movement forwarding in engagement with an adjacent actuator 1', in order to allow redundancy of the force passage in case of failure of the actuator 1, such a failure may occur especially during a rupture of the shaft internal 400 of the actuator.
Thus, if the actuator 1 is not powered, or the internal axis 400 of the actuator is broken, the flap 3 'of the adjacent actuator 1' is always rotated via the flexible shaft 29.
Referring now to Figure 4 showing the actuator 1 in a position in which the rod 300 has undergone a translation. On landing, the nozzle panels are positioned in a particular extreme retracted position which is no longer freely regulated in the intermediate position. The position of the nozzle panels in this extreme position is maintained by a predetermined adjustment of the pressure of the fluid which enters the cavity 105 of the body 100 via the orifice CW, and / or by the spring 906 acting in compression against the piston, and / or with a blocking pin and / or with a hydraulic brake with no pressure. The rotation of the piston 900 is thus blocked, causing a locking in translation of the internal axis 400.
When a translation of the rod 300 downstream of the actuator is desired, the guide cap 707 is moved in translation by the pressurization of the first chamber 107a by the orifice D. When the first chamber 107a is not pressurized, the segments 709, under the effect of the traction of the rod 300 tend to expand due to the reaction of the profile of the ramp 306. The presence of the guide cap 707 prevents the separation of the segments, and the rod 300 remains locked. During the pressurization of the first chamber 107a, the guide cap 707 is retracted and the pull of the rod 300 produces a tangential expulsion of the segments 709 which leave the contact with the ramp 306, and thus release the movement of the rod 300. In order to facilitate the retraction of the cap, the prior pressurization of the second chamber 107b through the orifice S makes it possible not to force the segments 709 along the guiding cap 707, thereby avoiding a phenomenon of unlocking "under load". The segment locking system can not, when in the locked position, prevent the rotation of the rod 300, either because the angles of friction and the reactions can not prevent it, or by means of a device complementary bearing (not shown), which allows free rotation of the guide segments in the body, while preventing its translation.
When the segments 709 have cleared the ramp 306 of the flange 311 of the rod 300, the fluid pressurized in the chamber 107a of the cavity 107 of the body 100 through the orifice D allows a displacement in translation of the rod 300 downstream of the actuator, so as to open the inverter cover. The displacement in translation of the rod 300 is authorized while the rotational movement of the rod 300 is blocked by the slides 405 of the internal axis 400 which engage the grooves 301 of the rod, the internal axis 400 being locked in rotation thanks to the fixed position of the piston 900.
The displacement in translation of the rod 300 causes, thanks to the nut 303 of the rod, engaged with the teeth 501 of the synchronizing screw 500, the rotation of the synchronization screw 500. The rotation of the screw of synchronization 500 allows, via the flexible shaft 15 driven by the wheel and worm system 600, 504, a synchronization of the actuators connected to this flexible shaft.
When it is desired to move the rod 300 upstream of the actuator, the movement of the piston 900 is blocked by the means described above, which makes it possible to prevent the rotation of the internal axis 400. 300 is displaced in translation by introducing a fluid under pressure into the chamber 107b, through the port S.
When the rod 300 returns to its closed position, it compresses a follower piston (not shown) which held the segments 709 in the raised position. The segments pushed by the cap 707 compressed by the spring 706 are now able to slide along the ramp 306 which are positioned vis-a-vis at the locking point during the closure of the rod 300. The cap 707 thrust by the springs 706 is then positioned radially so as to again block the expansion capacity of the segments 709, finalizing the mechanical locking phase of the segment lock assembly 700.
FIG. 5 represents a hydraulic control device 9 of a set of inverter hood actuators 1 and 1 'and of variable section nozzle panels 3, 3'.
The cover 5 is adapted to be driven in translation by four actuators 1 and 1 'hydraulic according to the invention, and the panels 3, 3' or nozzle flaps are adapted to be rotated by the actuators 1 and 1 'respectively by via the movement return devices 4, 4 '. The actuators 1 'are mechanically synchronized to the actuators 1 by the flexible shafts 15. This allows the actuated actuators to transmit their movement to possibly faulty actuators. Likewise, the complementary flexible shafts 29 make it possible to synchronize the rotation of the wheel 11 of the motion-redirecting device 4 in engagement with the actuator 1, with the wheel 11 of the movement-returning device 4 'in engagement with the actuator adjacent 1 '. Thus, if the actuator 1 is not powered, or the internal axis 400 of the actuator is broken, the flap 3 'of the adjacent actuator 1' is rotated through the shaft flexible 29.
The inverter cover 5 designates two half-covers 5d, 5g, "d" and "g" respectively designating a half-hemicycle right and left of the nacelle. Alternatively, the inverter cover can also be a single cover substantially peripheral to the nacelle, the four actuators 1 and 1 'being then arranged in pairs on each side of a longitudinal axis of the nacelle.
The actuators 1 and 1 'are controlled by two control units 17d, 17g adapted to control the actuators 5 in a variable nozzle mode, and a set of control units 19a and 19b adapted to control the actuators 1 and 1 in a thrust reversal mode.
The control units 17d, 17g and the assembly 19a, 19b are connected to a supply 21 of pressurized fluid and a circuit 23 for returning the fluid under pressure. Ideally, the units 17d and 17g are powered by pressure sources separate from the aircraft, in order to keep at least one pair of actuator powered in the event of failure of one of the two power supply circuits of the aircraft. The unit assembly 19a and 19b may, however, be fed indifferently by one of these two circuits.
The control units 17d, 17g in a nozzle mode each supply hydraulic fluid with a pair of actuators 1 and 1 '. For reasons of safety, the actuators assigned to each control unit 17d, 17g are crossed, that is to say that the control unit 17d feeds an actuator 1 positioned in the right part of the nacelle and an actuator 1 positioned in the left part of the basket. The same goes for the 17g driving unit. The diagram of FIG. 5 represents a supply solution for two pairs of actuators, but can be extended in the same way to three actuators per cover, regulated by a power sharing, one of the actuators being driven by the actuator. 17d driving unit, and the other two actuators being controlled by the control unit 17g, and vice versa on the other inverter cover.
Each control unit 17d, 17g comprises a three-way servovalve 25 and an electrically powered supply isolating valve 27. Preferably, the isolation valve 27 is always energized while the servovalve 25 is regulated only in the nozzle supply mode. In the event of a "boarding" phenomenon following a drift of the servovalve 25, the pressurization of the CW and CCW ports of the actuator causes an impromptu rotation of the panels 3 or flaps, detected by the axis RVDT sensor. internal 400 rotary. The controller then cuts the pressurizing valve and the actuator is left in the free position, pushed by the spring 906 to its folded position. Nevertheless the regulation allows that the adjacent actuators powered by the other control unit 17g can drive the depressurized actuators through the main flexible shafts 15 and through the complementary flexible shafts 29 optional positioned at the device of the movement of the device 4. The unit control that performs this control is preferably the FADEC (acronym for "Full Authority Digital Engine Control"), not shown in the figures, provided for the engine control that has input and output RVDT measurement packages, pressure sensors, pressurizing solenoid valve supply, proportional torque motor, able to supply a similar servovalve for controlling the fuel supply or air supply geometry of the turbojet engine. The FADEC is traditionally partitioned into two separate channels fed and controlled separately in parallel or master-slave, and is therefore fully predisposed for this type of two-way regulation of such a system. The servovalve 25 is a three-way servovalve adapted when the piston 900 is of differential section between the orifices CW and CCW, as presented above. In this case, the reduced section fed by the orifice CW is directly supplied by the pressure downstream of the isolation valve 27, while the largest section fed by the port CCW is modulated by the servovalve 25, which recharges or discharges the pressure of the chamber according to the angular position of the panels or shutters 3, 3 ', with respect to a set point.
Alternatively, when the rotary piston 900 has identical sections, the servovalve 25 can be replaced by a four-way servovalve, making it possible to proportionally modulate the two chambers of the actuator, ie the pressure increases in one of the chambers. and decreases proportionally in the other, depending on the control current of the servovalve.
Alternatively, the servovalves supplying the CW and CCW ports of the actuators can be provided with actuators with safety shock-proof valves 31, which makes it possible to clip the pressure peaks induced by momentary aerodynamic force overloads in the panel 3, 3 .
Alternatively, if the fineness of the need for regulation is not demanding, and / or if the needs for displacement of the panels or shutters are intermittent and sequential, the servovalves 25 can be replaced by control solenoid valves and the actuator can be equipped with control systems. 900 rotary piston lock of a hydraulic brake with no pressure, a finger engagement or other immobilization devices known to those skilled in the art.
Alternatively, if it is desired to position the panels or flaps 3, 3 'in an open position or in a closed position, without any other intermediate position, the servo valves 25 can be replaced by solenoid valves "all or nothing" or "ON / OFF Known to those skilled in the art, which pressurize the cavity 105 of the actuator through the CW orifice or by the CCW orifice of the rotary piston 900.
In all the embodiments of the control panels or nozzle flaps that have just been described, the ability to synchronize the panels 3, 3 'or nozzle flaps between them and the capacity to cope with the loss is preserved. a hydraulic supply or a simple rupture of the transmission chain, such as a rupture of the rotary piston shaft 900, thanks to: a feed shared by two separate driving units 17d and 17g, and or - a power distribution of the pairs of actuators 1 and 1 'on a given cover 5, and / or - the mechanical drive feedback by the flexible synchronizing shafts 15 and the complementary flexible shafts 29.
It goes without saying that the present invention is not limited to the embodiments of this actuator, described above solely as illustrative examples, but it encompasses all variants involving the technical equivalents of the means described. as well as their combinations if they fall within the scope of the invention.

权利要求:
Claims (18)
[1" id="c-fr-0001]
Hydraulic actuator (1, 1 ') for alternately sequencing actuation of an aircraft turbojet engine nacelle thrust reverser hood (5) and alternatively of panels (3, 3') or sectional secondary nozzle flaps variable of said nacelle, comprising: - a body (100) adapted to be mounted on a fixed structure (7) of a thrust reverser; - A rod (300), mounted in said body and adapted to be connected, on the one hand, to a cover (5) of said inverter and, on the other hand, to a panel (3) or secondary nozzle flap; said actuator being characterized in that the body (100) comprises means for displacing the rod (300) alternately in translation relative to said body (100), so as to cause the translation of a reversing cover (5) of thrust, or rotation relative to said body (100), so as to cause rotation of a panel (3) or secondary nozzle flap.
[2" id="c-fr-0002]
2. Actuator (1) according to claim 1, characterized in that it comprises means adapted to return the translational movement and rotation of the rod (300) of said actuator to an actuator external to said actuator (1), so synchronized.
[3" id="c-fr-0003]
3. Actuator (1) according to one of claims 1 or 2, characterized in that the means for moving the rod (300) in rotation comprise: - a groove (301) arranged longitudinally inside the rod (300) ); - an inner axis (400) rotatable, locked in translation relative to the body (100), and comprising a slider (405) engaging said groove (301); means for rotating said internal axis (400).
[4" id="c-fr-0004]
4. Actuator (1) according to claim 3, characterized in that the means for rotating the inner shaft (400) comprise: - a piston (900) rotating, engaged with said inner axis (400); means for rotating said piston (900).
[5" id="c-fr-0005]
5. Actuator (1) according to claim 4, characterized in that the means for rotating the piston (900) comprise: - a first set of teeth (901), arranged outside the piston (900); - a set of teeth (101), arranged inside the body (100), and engaged with the teeth (901) of the piston (900); a plurality of fluid introduction orifices (CW, CCW), arranged in said body (100), on either side of said piston (900); and in that the piston (900) is engaged with said internal axis (400) by a second set of teeth (902), arranged inside the piston (900), and engaged with a set of teeth ( 402), arranged outside the internal axis (400).
[6" id="c-fr-0006]
6. Actuator (1) according to claim 5, characterized in that the teeth (101, 402, 901, 902) are helical gears with single or multiple steps.
[7" id="c-fr-0007]
7. Actuator (1) according to claim 5, characterized in that the teeth (901, 902) are helical gears to reverse pitch.
[8" id="c-fr-0008]
8. Actuator (1) according to one of claims 5 or 6, characterized in that it further comprises a spring (906) arranged to oppose the displacement of the piston (900) in one of the directions of displacement of said piston .
[9" id="c-fr-0009]
9. Actuator (1) according to any one of claims 2 to 8, characterized in that the means for returning the translational movement and rotation of the rod (300) of the actuator, to an actuator external to said actuator, comprise: - a synchronization screw (500) comprising a set of teeth (501) arranged outside said screw (500); - a nut (303), mounted within the rod (300), and engaged with the set of teeth (501) of said screw (500); a wheel and worm system (504, 600) adapted to receive a flexible shaft system intended to connect the wheel and worm system (504, 600) of the actuator to a wheel and worm gear system of said device external to said actuator; a set of rotary bearings (503), supporting said screw, said bearings being arranged on either side of said wheel and worm gear system (504, 600), so as to lock in translation the synchronization screw (500) relative to the body (100) of the actuator.
[10" id="c-fr-0010]
Actuation system comprising at least one actuator (1, 1 ') according to any one of claims 1 to 9 and a hydraulic control device (9) of said at least one actuator, characterized in that the control device hydraulic is adapted to control the displacement of the rod (300) of the actuator alternately in translation relative to said body (100), so as to cause the translation of a cover (5) thrust reverser, or in rotation relative to said body (100), so as to cause the rotation of a panel (3) or secondary nozzle flap.
[11" id="c-fr-0011]
11. Actuating system according to claim 10 characterized in that it comprises a hydraulic supply (21) doubled by hydraulic supply circuits, and in that it comprises control units (17d, 17g) supplying power. adjacent actuators (1, 1 ') of an inverter cover (5) to cause rotation of the actuator rod (300) (1,1').
[12" id="c-fr-0012]
12. Actuating system according to claim 11 characterized in that the control units (17d, 17g) comprise a three-way servovalve (25) supplying the body of the actuator through the orifice (CW) and a control valve. insulation (27) supplying the actuator body through the orifice (CCW).
[13" id="c-fr-0013]
13. Actuating system according to claim 11 characterized in that the control units (17d, 17g) are equipped with four-way servovalve.
[14" id="c-fr-0014]
14. Actuating system according to claim 11 characterized in that the control units (17d, 17g) are equipped with solenoid valves "all or nothing" able to pressurize the actuator (1) via the orifice (CW) or the orifice (CCW).
[15" id="c-fr-0015]
15. Operating system according to any one of claims 10 to 14, characterized in that it comprises at least one shockproof safety valve (31), for discharging the pressures induced by undesirable forces of the panels or shutters of nozzle.
[16" id="c-fr-0016]
16. Nacelle for an aircraft turbojet, comprising a thrust reverser and a variable section secondary nozzle comprising a plurality of panels (3, 3 ') or flaps movable in rotation, comprising at least one actuating system according to one any of claims 10 to 15, said actuating system supplying a plurality of actuators (1), characterized in that: - the body (100) of the actuator (1) is mounted on a fixed structure (7) of the thrust reverser; the rod (300) of the actuator is connected, on the one hand, to a cover (5) of said inverter and, on the other hand, to a panel (3, 3 ') or flap of said secondary nozzle, by via a movement reversing device (4, 4 ') from the actuator (1, 1') to the panel (3, 3 ') or nozzle flap.
[17" id="c-fr-0017]
17. Nacelle according to claim 16, characterized in that it comprises a flexible shaft (15) connected between a first actuator (1) of the inverter cover, and a second actuator (1 ') of said cover, adjacent to said first actuator (1), arranged to synchronize the translational movement and rotation of the rod (300) of the first actuator (1) with that of the second actuator (1 ').
[18" id="c-fr-0018]
Platform according to claim 17, characterized in that it comprises a complementary flexible shaft (29) connecting: the movement return device (4) of the first actuator (1) to the nozzle panel (3), and the movement-returning device (4 ') of the second actuator (1') to the nozzle panel (3 '), said complementary flexible shaft being arranged to synchronize the movement of the movement-returning device (4) with that of the movement return (4 ').

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同族专利:

公开号 | 公开日

EP3390800B1|2019-05-22|

WO2017103464A1|2017-06-22|

US10190605B2|2019-01-29|

US20180298924A1|2018-10-18|

FR3045743B1|2018-08-24|

EP3390800A1|2018-10-24|

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US9316112B2|2011-12-21|2016-04-19|Rohr, Inc.|Variable area fan nozzle with drive system health monitoring|US10393285B2|2017-10-02|2019-08-27|United Technologies Corporation|Multi-actuation control system with pressure balancing plumbing|

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法律状态:
2016-10-20| PLFP| Fee payment|Year of fee payment: 2 |

2017-06-23| PLSC| Search report ready|Effective date: 20170623 |

2017-11-23| PLFP| Fee payment|Year of fee payment: 3 |

2018-03-02| CD| Change of name or company name|Owner name: SAFRAN NACELLES, FR Effective date: 20180125 |

2019-11-20| PLFP| Fee payment|Year of fee payment: 5 |

2020-11-20| PLFP| Fee payment|Year of fee payment: 6 |

优先权:

申请号 | 申请日 | 专利标题

FR1562676A|FR3045743B1|2015-12-17|2015-12-17|HYDRAULIC ROTO-LINEAR PUSH-INVERTER AND VARIABLE SECTION TUBE ACTUATOR|

FR1562676|2015-12-17|FR1562676A| FR3045743B1|2015-12-17|2015-12-17|HYDRAULIC ROTO-LINEAR PUSH-INVERTER AND VARIABLE SECTION TUBE ACTUATOR|

EP16825506.5A| EP3390800B1|2015-12-17|2016-12-14|Nacelle for aircraft turbojet engine provided with a hydraulic roto-linear actuator of a thrust reverser and a variable-area nozzle|

PCT/FR2016/053408| WO2017103464A1|2015-12-17|2016-12-14|Nacelle for aircraft turbojet engine provided with a hydraulic roto-linear actuator of a thrust reverser and a variable-area nozzle|

US16/010,750| US10190605B2|2015-12-17|2018-06-18|Nacelle for an aircraft turbojet engine provided with a hydraulic roto-linear actuator of a thrust reverser and of a variable-section nozzle|

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