法国专利FR3044635A1 ABSORPTION OF ENERGY ABSORPTION OF AIRCRAFT ACTUATOR LIMITER WITH DETABLE DESTRUCTIBLE RACK, ACTUATO

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专利摘要:
The invention relates to an end-of-travel stop of an aircraft actuator, at least one of whose scopes, said scope (19) destructible, has at least one destructible portion adapted to and arranged to be irreversibly deformed. under the effect of the end-of-travel contacting cooperation between the driving member (19) and the driven member (20) surfaces, each destructible portion of each destructible range being removably mounted relative to the abutment of way to be replaced. It extends to an actuator comprising at least one such limit stop and to an aircraft comprising at least one actuator provided with at least one such end stop and / or at least one such actuator.
公开号:FR3044635A1
申请号:FR1561882
申请日:2015-12-04
公开日:2017-06-09
发明作者:Nicolas Tilloy；Olivier Brucelle
申请人:Ratier Figeac SAS；
IPC主号:

专利说明:

AIRCRAFT ACTUATOR LIMITER ENERGY ABSORPTION STOP WITH DETACHABLE DESTRUCTIBLE RANGE, ACTUATOR AND
The invention relates to an end-of-travel stop of an aircraft actuator with braking energy absorption. It extends to an aircraft actuator - in particular a steering actuator - provided with at least one limit stop with brake energy absorption - in particular two end stops with energy absorption. braking-. It also extends to an aircraft comprising at least one actuator provided with at least one limit stop with brake energy absorption-in particular two end stops with brake energy absorption-and in particular to an aircraft comprising at least one actuator - in particular at least one steering actuator - provided with at least one limit stop with brake energy absorption - in particular two end stops with absorption of energy. braking energy.
Known aircraft comprise various actuators, in particular screws (ball screws, roller screws, screws with trapezoidal screws, etc.), for example actuators for control surfaces, doors, landing gear, etc. such actuator may be a hydromechanical actuator, electromechanical, hydro-electromechanical, pneumatic or using any other source (s) of energy. It can be linear and / or rotary, using gears or not, and comprises, in addition to a mechanical transmission, at least one motor device (electric motor (especially for electromechanical actuators (EMA) such as those used in aircraft modern electric flight controls) and / or hydraulic motor and / or pneumatic motor) coupled to the mechanical transmission for driving a driven member moving relative to the chassis of the aircraft. For security reasons in particular, the known actuators, such as ball or roller screws, embarked on board an aircraft are generally provided with two end stops limiting the travel path of the driven member, for example example limiting the displacement stroke in relative translation of a nut relative to a screw. Such known limit stops are advantageously provided with washers or elastic buffers for absorbing braking energy (see, for example, US Pat. No. 2,497,424). Indeed, the absorption of the braking energy makes it possible to protect the actuator and the various organs situated upstream (in particular the driving device) or downstream (that is to say the member of the aircraft whose the movement is controlled by the driver) shocks resulting from an end-of-travel contact of the stop. It also possibly makes it possible to restore this energy to drive the driver in the opposite direction after an end-of-stroke contact. Nevertheless, it turns out that such elastic or rubbery pads have a relatively low energy absorption capacity, are subject to aging, are highly sensitive to environmental conditions (temperature variations, humidity, solvents, fluids, etc.) , and have features that can be modified after one (or more) end-of-travel contact (s) of the stop. However, degraded characteristics of such an end-of-travel stop may result, in the event of end-of-travel contact, of damage to the driver and / or to the driver motor device and / or to an aircraft member, such as a rudder, whose movement is controlled by factioneur. Furthermore, in aeronautics, it is important that such parts can be certified with regard to their performance and characteristics. The invention therefore aims in general to solve this problem by proposing an end-of-travel limit stop for actuator-in particular for an aircraft screw actuator having a greater capacity for absorbing braking energy at the end of the race. , and whose characteristics can be predetermined (and certified), remain constant over a longer life, and are independent of the various environmental conditions encountered by the driver during its use on board the aircraft.
To do this, the invention relates to a limit stop of an aircraft actuator, said actuator comprising a driving member and a driven member cooperating to form a guide relative displacement of the driven member relative to the driving member, said limit stop comprising at least one operating member surface integral with the driving member according to at least one component (in translation and / or in rotation) of said relative movement, and at least one organ reach conducted at least one of the driven member according to at least one component (in translation and / or in rotation) of said relative movement, said bearing surfaces of the driving member and of the driven member being arranged to be able to cooperate by contact at the end of the stroke so as to forming a device for limiting the stroke of the driven member with respect to the driving member with absorption of braking energy, characterized in that: it comprises at least one apt destructible portion; e and arranged to be irreversibly deformed under the effect of the end-of-travel contact cooperation of said driving member and driven member surfaces, - each destructible portion is removably mounted relative to the actuator particularly with respect to the abutment so that it can be replaced.
More particularly, the invention relates to an end stop of an actuator with an aircraft screw, said screw actuator comprising a screw and a nut cooperating (in particular by means of balls or rollers) to form a rotation guide. and in relative translation of the nut along the screw, said stop comprising at least one screw seat fixed at least in translation of the screw and at least one nut bearing integral at least in translation of the nut, said screw and nut seats being arranged to be able to cooperate by contact at the end of stroke to form a device for limiting the stroke of the nut relative to the screw with absorption of braking energy, characterized in that: - it comprises at least one destructible portion adapted to and arranged to be deformed irreversibly under the effect of the cooperation by end-of-travel contact of said screw and nut seats, - each a destructible portion is removably mounted relative to the actuator-particularly with respect to the stopper-so that it can be replaced.
While a removable destructible portion, thus removable, could be considered as having unacceptable disadvantages compared to washers or elastic buffers, the inventors have on the contrary determined that such a destructible portion has in fact preponderant advantages for a stop of aircraft actuator limit switch.
Firstly, an irreversible deformation (plastic deformation and / or rupture), that is to say a destruction, of a destructible portion results in a high energy dissipation and has a capacity for absorbing energy from braking much more important than elastic deformation (that is to say reversible).
In addition, a destructible portion may be formed of a rigid material of low elasticity, having mechanical characteristics constant in time, insensitive to aging and environmental conditions.
Moreover and above all, an aircraft actuator end stop is a safety device which, under normal conditions of use of the aircraft, should never be used. In particular, the ranges of such an aircraft actuator limit stop never come into end-of-travel contact during the flight of the aircraft. Indeed, an aircraft-mounted actuator is always dimensioned such that the positions of the driven member corresponding to the end stops can never be reached in the flight envelope of the aircraft. As a result, these end stops are mainly useful when the aircraft is on the ground, in construction or maintenance operations. In particular, they make it possible to avoid inadvertent movements of the members whose movement is controlled by the actuator that could result from errors of assembly or adjustment, and would be likely to cause damage or breakage. Now, in this context, not only a destructible range avoids said damage or breakage, but it also has the decisive advantage of being designed so that the destruction of at least a destructible portion is visible from the outside, or provided with a device for viewing such destruction. Considering also the scarcity of accidental abutment of these end stops, the fact of having to dismantle and replace a limit stop having been destroyed is not a real drawback.
An actuator comprises two movable members relative to each other: for example the screw and the nut in the case of a screw actuator such as a ball screw or roller. One of these movable members is a driving member, rotated by a motor device to which it is coupled and fixed (in particular in translation) relative to the chassis of the aircraft, and the other movable member is a driven member, mobile (in particular in translation) relative to the chassis of the aircraft.
Advantageously and according to the invention, at least one of said carried organ and lead member scopes is a destructible scope comprising at least one destructible portion. A limit stop according to the invention may comprise one or more scope (s) destructible (s) -in particular several destructible surfaces integral with the same movable member and / or integral with the two movable members. In addition, the same destructible range (including screw or nut) of a limit stop of the invention may include one or more portion (s) destructible (s).
In a limit stop according to the invention, at least one destructible portion is removably mounted relative to the actuator and relative to the stop, that is to say can be disassembled to be replaced. Such a removable portion may be removable in isolation, or in one piece with a set of parts to which it is integrated, said assembly being itself removably mounted relative to the actuator. Thus at least one destructible portion is removably mounted relative to the driving member and / or relative to the scope of the driving member and / or relative to the driven member and / or relative to the scope of the driven member and / or relative to the span of the screw and / or relative to the nut span.
In particular, advantageously and according to the invention, at least one driving member scope is a destructible scope comprising at least one removable destructible portion relative to the lead member scope. As a variant or in combination, advantageously and according to the invention, at least one driven organ range is a destructible scope comprising at least one removable destructible portion relative to the driven organ range. Also, in a limit stop according to the invention, at least one destructible range is mounted integral with the driving member and / or at least one destructible range is mounted integral with the driven member and / or at least one range destructible is mounted integral with the nut and / or at least one destructible range is mounted integral with the screw, the destructible range being removably mounted relative to the driving member and / or the driven member and / or the nut and / or the screw, respectively.
In particular, advantageously and according to the invention at least one driving member scope is a destructible range removably mounted relative to the drive member. As a variant or in combination, advantageously and according to the invention, at least one driven body reach is a destructible bearing mounted removably with respect to the driven member.
Furthermore, in certain advantageous embodiments, a destructible portion of a stopper according to the invention can be adapted to be plastically deformed under the effect of the end-of-travel contacting engagement between said driving member surfaces and the led organ. For example, such a destructible portion may be formed of at least one block of material adapted to undergo plastic deformation under the effect of stresses resulting from a contact and an end-of-stroke impact between the body reaches leading and led organ. Such a block of plastic deformation material may be incorporated in said destructible scope, removably mounted therein to be disassembled and replaced by a new block.
As a variant or in combination, in certain advantageous embodiments of an abutment according to the invention, at least one destructible portion is adapted to be broken under the effect during cooperation by end-of-stroke contact between the organ reaches leading and led organ.
A destructible portion capable of being broken by an abutment according to the invention can be subjected to any mode of rupture: cutting, stamping, shearing, penetration, deformation at break in torsion and / or compression and / or bending and / or traction ... This destructible portion is likely to be broken by at least one integral member of another scope. In certain advantageous embodiments of the invention, at least one destructible scope comprises at least one destructible portion adapted to be cut by at least one knife integral with another span under the effect of a relative movement of the organ. conducted relative to the driving member and between these bearing surfaces during the end-of-travel contact cooperation between the driving member and driven member surfaces.
It should be noted in this regard that the energy absorbed by a break in a destructible portion is, for a given abutment force, greater than that absorbed by a deformation in the plastic field.
In certain embodiments of an abutment according to the invention, the contact cooperation between the driving member bearing and the driven member bearing is carried out by relative movement in translation at least, and preferably in translation and in translation. rotation of these two litters relative to each other. According to various alternative embodiments of the invention that can be envisaged, the irreversible deformation of each destructible portion can therefore result from the relative movement in translation and / or rotation of the driving member and driven member surfaces relative to each other. to the other.
In certain advantageous embodiments an end stop according to the invention is also characterized in that the driven member and the driving member being guided relative to each other at least in relative rotation, each span. of driving member is integral in rotation with the driving member, each led body surface is integral in rotation with the driven member, and at least one destructible portion is arranged to be deformed irreversibly by relative rotation at the end of stroke of said driving member and driven member surfaces.
In particular, the invention applies to a limit stop for an actuator in which the driving member and the driven member of the actuator are guided in a helical motion about an axis, that is, that is to say a screw actuator such as a ball screw, a roller screw, a trapezoidal screw screw ... Advantageously and according to the invention each led body surface cooperates by contact with a range of driving member according to at least one radial contact plane, preferably in a plurality of contact planes uniformly distributed around the axis of the helical movement.
In certain possible embodiments, at least one destructible portion may be mounted integral with a first driving member or driven member surface, and arranged to be directly impacted by a second driving member or organ bearing surface. led, respectively, that is to say by being directly interposed between the first range and the second range at the end of the race. Such a destructible portion attached to said first scope is removably assembled to this first scope to be replaced.
In other preferred embodiments, at least one-in particular each range of driving member or driven member, said destructible scope, comprising at least a destructible portion, comprises an impact armature arranged to receive at the end of stroke the impact of the other scope, driven member or driving member, the impact armature being arranged to be able to: - be driven in movement with respect to each destructible portion under the effect of said impact and the end-of-travel contact cooperation of said driving member and driven member surfaces, - causing the irreversible deformation of each destructible portion under the effect of said movement.
Moreover, in certain advantageous embodiments, an end stop according to the invention is adapted so that the destruction of at least one part of each destructible portion is visible.
To do this, according to a first variant of the invention, said destructible portion is advantageously positioned so as to be visible from outside the abutment and the actuator. This first variant is particularly advantageous in the case of a destructible portion capable of being broken, the visualization of a rupture being generally immediate, for example in the form of a shearing chip.
According to a second possible variant of the invention, the abutment comprises a device indicating the deformation of at least one of each destructible portion. This second variant is particularly advantageous in the case of a destructible portion adapted to be plastically deformed. The invention also extends to an actuator -in particular an aircraft steering actuator having at least one limit stop with absorption of braking energy, characterized in that it comprises at least one stop according to the invention. In some embodiments, an actuator according to the invention is characterized in that the driving member and the driven member are guided in a helical motion about an axis. It is therefore a screw actuator.
An aircraft actuator according to the invention furthermore comprises at least one driving device coupled to one, driving, movable members -particularly chosen from the screw and the nut of an actuator with screw-actuator for the drive on the move - especially rotating -. This engine device comprises at least one engine selected from an electric motor, a hydraulic motor and a pneumatic motor. The other movable member of the actuator is a driven member coupled to a moving part of the aircraft-in particular a rudder, for example a elevator - to drive it in motion. The invention also extends to an aircraft comprising at least one actuator provided with at least one end stop with brake energy absorption, characterized in that it comprises at least one stop according to the invention. It also extends to an aircraft comprising at least one actuator -in particular at least one steering actuator, for example a elevator actuator- provided with at least one end stop with brake energy absorption, characterized in that it comprises at least one actuator -particularly at least one steering actuator- according to the invention. The invention also relates to an end stop, an actuator and an aircraft characterized in combination by all or some of the features mentioned above or below. Other objects, features and advantages of the invention will become apparent on reading the following non-limiting description which refers to the appended figures in which: FIG. 1 is a partial diagrammatic elevational view illustrating a portion of tail of an aircraft according to the invention provided with an adjustable actuator according to the invention having an actuator provided with limit stops according to the invention, - Figure 2 is a schematic elevational view of an actuator with FIG. 3 is a schematic perspective view of a screw bearing of an end stop according to a first embodiment of the invention comprising destructible portions. capable of being broken, the screw span being represented before deformation and breaking of the destructible portions, FIG. 4 is a diagrammatic elevational view of an armature in dull section with destructible portions of the screw range of the end stop of Figure 3, - Figure 5 is a schematic axial sectional view of the screw bearing of the end stop of Figure 3, - FIG. 6 is a diagrammatic cross-sectional view of the screw bearing surface of the limit stop of FIG. 3; FIG. 7 is a schematic perspective view of the screw bearing surface of the end stop of FIG. 3 is a diagrammatic elevational view of a screw bearing of an end stop according to a second embodiment of the invention comprising destructible portions; FIG. 9 is a schematic cross-sectional view of the screw bearing surface of the limit stop of FIG. 8; FIG. 10 is a partial schematic view in perspective of destructible portions of the port; FIG. Fig. 11 is a schematic cross-sectional view of a screw seat of an end stop in accordance with a third embodiment of the invention. comprising destructible portions with plastic deformation, - Figure 12 is a schematic axial sectional view of the screw bearing of the limit stop of Figure 11.
In the example shown in FIG. 1, an aircraft according to the invention comprises an adjustable actuator 11 making it possible to control the inclination of the elevator rudder 12 of the aircraft. The actuator 11 is articulated by its upper end to the chassis of the aircraft about a transverse horizontal axis by a hinge 13. It comprises a transmission comprising a ball screw formed of a worm 14 and a nut 15. The endless screw 14 is rotated at its upper end by a geared motor device 16 comprising for example an electric motor and / or hydraulic. The endless screw 14 is articulated at least in a pivot connection (which can incorporate a cardan function of a few degrees of freedom) by its upper end and fixed in translation relative to the chassis of the aircraft. The worm 14 cooperates with the nut 15 via a recirculating ball device, so that the nut 15 is driven in translation along the endless screw 14 when the latter is rotated in the nut 15. The nut 15 is coupled hinged at least in a pivot connection (which can incorporate a gimbal function of a few degrees of freedom) to the elevator 12, so that the translational position of the nut 15 along the endless screw 14 determines the inclination of this rudder 12 depth. The articulation of the nut 15 to the rudder 12 of depth prevents any rotation of the nut 15 around the axis of the worm 14 endless. The pivot connection of this articulation of the nut 15 to the elevator 12 and the pivot connection of the articulation of the endless screw 14 to the frame of the apparatus are pivotal connections along parallel axes, which are also parallel to the transverse pivot axis of the elevator 12 of the device relative to the chassis. The actuator 11 comprises an upper end stop 17 and a lower end stop 18.
Each of the end stops 17, 18 of the end of the race according to the invention comprises at least one span 19 of screw integral at least in translation with the endless screw 14 and at least one bearing surface 20 secured at least in translation with the nut 15, and at least one destructible portion which is adapted to be deformed irreversibly by plastic deformation and / or rupture under the effect of the end-of-travel contact cooperation of said screw and nut bearing surfaces 19.
FIG. 2 represents an exemplary possible embodiment of a lower limit stop 18 comprising a bearing surface 19 secured in translation and in rotation with the endless screw 14, and a bearing surface 20 integrally in translation and in translation. rotation of the nut 15. The screw seat 19 is in the general shape of a sleeve engaged at the end of the endless screw 14, locked in rotation relative to the latter by keying or by splines 24 conjugate the span 19 screw and endless screw 14 or by any other rotation locking means. The span 19 of the screw is also fixed in translation relative to the screw 14 endless. The nut bearing 20 can be formed by a specific part assembled to the nut 15, or simply by a transverse face of the nut 15.
Furthermore, these two bearing surfaces 19 of screws and 20 of nut have organs 22, 23 of interconnection of the type known as "dog teeth" or "teeth of wolf", of complementary shapes, forming a coupling in rotation of these bearing surfaces. translational limit switch.
In the position shown in FIG. 2, the nut 15 is at the end of translation travel along the endless screw 14, and the bearing surface 20 comes to cooperate by end-of-travel contact with the screw seat 19. The bearing surface 20 abuts in translation and in rotation against the bearing surface 19 of the screws, and the clutch interconnection members 22 of the screw seat 19 come to impact the clutch members 23 of the nut bearing surface 20 forming said coupling. rotation. Nevertheless, since the bearing surface 20 is locked relative to the chassis of the aircraft in rotation about the axis of rotation of the endless screw 14, this rotational coupling induces a shock in rotation with a resistant torque and constraints. in rotation within the span 19 of screws, between the interconnection members 22 and the splines 24 for locking in rotation of the span 19 of screws with respect to the endless screw 14.
Preferably these interconnection members 22, 23 are arranged so as to have at least one contact plane (between the dog teeth of the nut seat and those of the screw seat) which is radial and remains perpendicular to the relative movement. rotation between the two staves. In this way, a stop without progressive jamming after impact is obtained on impact, a certain backward movement remaining possible.
Another advantage of providing each radial contact plane which remains perpendicular to the relative rotational movement is that the axial component of the force generated during the impact is zero or negligible.
Furthermore, advantageously, the bearing surfaces 19 of screws and 20 of nuts each comprise a plurality of interconnection members 22, 23, and the interconnection members 22, 23, and therefore also the different corresponding contact planes, are uniformly distributed. around the axis of the endless screw 14. In this way, any component of shear force is avoided. In the example shown, the screw seat 19 comprises two diametrically opposed teeth 22 of interconnection and the bearing 20 has two diametrically opposed teeth interconnection teeth 23.
In the first embodiment of FIGS. 3 to 7, the screw surface 19 comprises portions 21 that are destructible by shear failure, resulting in a dissipation of the energy of the end-of-stroke impact and therefore an absorption of the braking energy of the movement at the end of the race.
To do this, the screw seat 19 comprises an internal frame 26 having the rotation locking grooves 24 relative to the endless screw 14 and an external impact frame 27 surrounding the internal frame 26, guided in rotation with respect to the latter around the axis of rotation of the endless screw 14, and having the organs 22 interconnection. The destructible portions 21 are interposed between these two armatures 26, 27 which are moreover adapted so that a rotational movement of the outer armature 27 around the inner armature 26 results in a rupture of these destructible portions 21.
In the exemplary embodiment shown, the destructible portions 21 are formed by peripheral destructible ribs 21, in particular, in the example shown, two peripheral destructible ribs 21 spaced apart from each other radially projecting from each other. outwardly (flange portion) of a cylindrical peripheral wall 30 of revolution of the axial end of the inner armature 26 facing the nut 15. The external impact armature 27 is formed of two rings 28 , 29 respectively capping the two axial ends of the sleeve forming the internal frame 26 and assembled to each other by screws 31. A first ring 28, said ring 28 of shear, cap the axial end of the internal armature facing the bearing 20 of the nut and has two diametrically opposed teeth 22 of interconnection extending projecting in an axial direction (parallel to the axis of the screw 14) towards the 20 with a nut span, these teeth 22 interconnection being adapted to cooperate with two teeth 23 interconnection diametrically opposed to the bearing surface 20 extending protruding in an axial direction towards the span 19 screw.
The second ring, called retaining ring 29, covers the axial end of the internal armature 26 facing the end of the endless screw 14. The retaining ring 29 has lugs 36 extending in an axial direction outside the internal armature 26, uniformly distributed angularly around the latter, for the assembly of the retaining ring 29 to the ring 28. shearing by the screws 31 screwed into threaded tappings 36. The respective shapes and dimensions of the rings 28, 29 of the outer frame 27 and the inner frame 26, and the assembly of the two rings 28, 29 l to one another are adapted to allow rotation guidance of the outer armature 27 around the inner armature 26 along an axis of rotation corresponding to the axis of rotation of the endless screw 14. The retaining ring 29 and the internal armature 26 are locked in translation relative to the endless screw 14 by an elastic split ring 20 engaged in a peripheral groove of the end of the endless screw 14. and in grooves of the inner frame 26 and the retaining ring 29.
The shearing ring 28 also has an inner cylindrical face 33 extending around the destructible ribs 21, and shearing knives 32 projecting radially inwardly from the inner cylindrical face 33 between the destructible ribs 21, so as to be able to shear the latter when the outer frame 27 is rotated around the inner frame 26. In the example shown, the shearing ring 28 has two shearing knives 32.
In addition, the shearing ring 28 advantageously has a slot 34 arranged immediately upstream of each shearing knife 32 for radially outwardly disengaging the chip 35 resulting from the shearing of the rib 21 that can be destroyed by the shearing knife 32. . As shown in FIG. 7, this chip 35 rolls up on itself and leaves the light 34, thus making visible the fact that the destructible rib 21 has been sheared.
The respective constituent materials of the shear knives 32 and the destructible ribs 21 are chosen so as to promote the shearing of each rib 21 destructible by a shearing knife 32. For example, the shear ring 28 may be formed of rigid steel, while the destructible ribs 21 are formed of aluminum alloy. In addition, advantageously, the end portion of each rib 21 destructible shear knife side 32 is bevelled in width, so that the end impacted by the shearing knife 32 has a reduced width facilitating the beginning of this shear .
The destructible ribs 21 may be inserts attached to the internal frame 26 and removably mounted relative to the latter so that they can be replaced after destruction. As a variant, the destructible ribs 21 may be formed by the internal armature 26 itself (in one piece), this inner armature 26 being removably mounted relative to the endless screw 14 by virtue of the stop ring 25. removable elastic split in the manner of a "circlip". In this latter variant, it is possible to replace the entire span 19 of screws, or on the contrary only the internal armature 26, which is removable with respect to the external armature 27 through screws 31.
It should be noted that, in a variant not shown, the nut bearing 20 can be made in the form of a destructible bearing, similarly to the screw bearing 19 described above. To do this, it suffices to provide for the inner armature to be assembled integrally in rotation and in translation with the nut 15.
In the second embodiment shown in FIGS. 8 to 10, the destructible range comprises an internal frame 46 comprising a transverse ring 48 extended axially by a generally cylindrical sleeve 49 locked in rotation relative to the endless screw 14 by keying or splines or by any other rotational locking means. The sleeve 49 has an outer diameter smaller than that of the ring 48. The inner frame 46 also has radial fins 52 extending radially outwardly from the sleeve 49 to the peripheral edge of the ring 48 and in parallel to the axis of the sleeve 49 over a certain height. The radial fins 52 are uniformly angularly distributed so as to delimit between them angular sectors of the ring 48 adapted to accommodate the 51 destructible linings.
The destructible range also comprises an external impact armature 47 comprising a transverse ring 53 and radial fins 54 extending radially to the peripheral edge of the ring 53 and parallel to the crown axis 53 to a height corresponding to that radial fins 52 of the internal frame 46. The radial fins 54 are uniformly angularly distributed so as to delimit between them angular sectors of the ring 53 adapted to accommodate the 51 destructible liners. The ring 53 of the external impact armature 47 also has teeth 59 of interconnection projecting parallel to the axis from its outer face opposite the wings 54.
The ring 48 of the internal frame 46 and the ring 53 of the outer frame 47 have similar dimensions, and the radial fins 54 of the outer frame 47 are interposed between the radial fins 52 of the internal frame 46, each radial fin 54 of the outer armature 47 being placed against a radial fin 52 of the outer armature 46. A set of destructible pads 51 is housed between each radial fin 54 of the outer armature 47 and a radial fin 52 of the inner armature 46, and between the two crowns 48, 53.
Each destructible liner 51 is formed of a block of material with plastic deformation, at least in angular compression. This block is in the form of an angular sector of slightly lower height than that of the fins 52, 54, and advantageously has bosses 55 of axial spacing to provide an axial clearance between each lining 51 and 51 destructible crown 48, 53 for circulation and the drainage of the water. Preferably, each block also has a bar 56 forming the inner radial end of the block and extending parallel to the axis of the two rings 48, 53 so as to form protruding locking studs 57, 58, each pin 57 , 58 locking can be engaged in a groove (not shown in the figures) formed recess in the ring 48, 53 facing. The assembly of such a destructible reach is achieved by placing destructible gaskets 51 between the fins of one of the rings 48, 53 and then placing the other ring 53, 48 to cover these destructible gaskets 51 and lock them in place. place through the pins 57, 58 by bringing the two rings 48, 53 axially from each other.
At the end of the stroke of the nut 15 with respect to the endless screw 14, the clutching teeth of the external impact armature 47 are impacted by the clutching teeth of the other end stop range. and the outer armature 47 is rotated relative to the inner armature 46, each radial wing 54 of the outer armature 47 angularly compressing the destructible liners 51 interposed between the radial wing 54 and a radial wing 52 of the internal frame 46. In doing so, the destructible liners 51 deform plastically with energy dissipation. It is possible to change the destructible linings 51 after deformation by moving the two rings 48, 53 away from each other axially and replacing new destructible liners 51 between the two rings 48, 53.
It is possible to provide (variant not shown) a visible mark at the periphery of the outer armature 47, facing a graduation or colored areas at the periphery of the internal armature 46, to visualize the fact that the outer armature 47 has been moved angularly with respect to the outer armature 46, forming an indicator of destruction of the destructible linings 51, thus requiring their replacement.
The material with plastic deformation constituting each destructible lining 51 may be arbitrary as soon as it is likely to deform in the plastic domain under the effect of the impact torque generated at the end of travel of the nut 15 with respect to the endless screw 14. It may be in particular a material chosen from a rigid polymeric foam (with open or closed cells), a rigid mesh structure (made of a material chosen from rigid metal alloys and rigid polymeric materials), for example nesting bees, or other. In particular, such a rigid mesh structure can be obtained by molding or by additive manufacturing (three-dimensional printing).
FIGS. 11 and 12 show a third embodiment of a destructible range of an end stop according to the invention which is a variant of the second embodiment of FIGS. 8 to 10 in which the destructible range is formed in one piece integrating the two internal and external armatures, this piece having areas of different densities of structural meshes so as to form destructible portions integrated in the heart of this piece. Such a part can also be manufactured by additive manufacturing (three-dimensional printing).
In the example shown, a first internal portion 66 of high mesh density serves as a rigid internal armature forming a central sleeve 69 and four radial fins 70 extending outwardly of the central sleeve. A second outer portion 67 of high mesh density extends radially outwardly of the first portion 66 and acts as a rigid outer armature having teeth radial peripheral clutch 71 and four radial fins 72 extending towards the internal, destructible portions 73, 74, of lower mesh density being angularly interposed between a radial fin 72 of the second outer portion 67 and a radial fin 70 of the first internal portion 66. In the example shown, a destructible portion 73 of medium mesh density is contiguous to the radial fin 72 of the second outer portion 67, and a destructible portion 74 of low mesh density is angularly interposed between this destructible portion 73 of average mesh density and the radial fin 70 of the first internal portion 66. Cutting areas 75 (free of material) are interposed between the destructible portions 73, 74 and the first and second inner and outer portions 67 and 67.
When an impact torque is applied on the teeth 71 of interconnection at the end of stroke of the nut 15 relative to the worm 14, each portion 74 destructible low density mesh is first deformed in the plastic field under the effect of the approximation of the fins 72, 70, then, if the impact energy is sufficient, each portion 73 destructible medium density is then deformed in the plastic field. A predetermined energy dissipation profile is thus obtained as a function of the mesh densities of the part forming this destructible range.
A limit stop according to the invention makes it possible to obtain a stop without progressive jamming, unlike an axial abutment of the state of the art with which a retrograde movement and sometimes impossible in view of a jamming occurring after the 'impact. In a limit stop according to the invention, the absence of jamming is in particular ensured by the fact that each plane of contact between the teeth of the dog's clutch and the teeth of interconnection of the worm is radial. . Another advantage of such a radial contact plane is that the axial component of the force generated during the impact is substantially zero, a small value possibly being able to be produced in the case where the member causing the destruction of a destructible portion has an angle to the axis of the worm to guide the direction of elections or the direction of deformation of the material during the absorption of energy. Since the clutch teeth are evenly distributed around the axis of the worm, the forces developed during the impact are exclusively composed of a torque, without any shear component that would be detrimental to the mechanical strength of the worm. actuator.
It goes without saying that the invention can be the subject of many different embodiments with respect to the embodiments shown in the figures and described above. In particular, destructible portions may be provided both at the nut span and the span of screws or at these two staves. Destructible portions may also be interposed between the two reaches of the limit stop according to the invention. Each destructible portion can be destructible by plastic deformation and / or fracture. Different modes of plastic deformation (in axial compression and / or in angular compression and / or in torsion and / or in flexion and / or in tension ...) and / or different modes of rupture (by cutting, stamping, shearing, penetration , deformation at break in torsion and / or compression and / or flexion and / or traction ...) can be envisaged, by using one (or more) portion (s) destructible (s). The destructible portions can be destroyed under the effect of the relative rotational movement of the nut 15 and the screw 14 (as in the embodiments shown, thanks to interconnection members) and / or under the effect of the movement. relative translation of the nut 15 and the screw 14. The same end stop may comprise several nut bearings (for example concentric and / or angularly juxtaposed) and / or several screw surfaces (for example concentric and / or angularly juxtaposed). A limit stop can comprise a single destructible portion or several destructible portions. The invention also applies to any other aircraft actuator that a ball screw: roller screw, trapezoidal screw (including ACME) screw, helical jack, rotary jack ...

权利要求:
Claims (15)
[1" id="c-fr-0001]
1 / - End of stroke stop of an aircraft actuator, said actuator comprising a driving member (14) and a driven member (15) cooperating to form a guide relative displacement of the driven member relative to the driving member, said limit stop comprising at least one bearing surface (19) secured to the driving member in at least one component of said relative displacement, and at least one bearing member (20) integral integral member of the driven member according to at least one component of said relative displacement, said bearing surfaces of the driving member and of the driven member being arranged to be able to cooperate by end-of-stroke contact to form a device for limiting the stroke of the driven member ( 15) relative to the driving member (14) with absorption of braking energy, characterized in that: - it comprises at least a portion (21, 51, 73, 74) destructible adapted and arranged to be deformed from irr way eversible under the effect of the end-of-travel contact of said driving member and driven member surfaces, each destructible portion (21, 51, 73, 74) is removably mounted relative to the actuator so that it can be replaced.
[0002]
2 / - Stopper according to claim 1, characterized in that at least one bearing surface (19) of the driving member is a destructible bearing comprising at least a detachable removable portion relative to the scope (19) of the driving member.
[0003]
3 / - Stopper according to one of claims 1 or 2, characterized in that at least one scope (20) of the driven member is a destructible range comprising at least a removable removable portion relative to the scope (20) d led organ.
[0004]
4 / - Stop according to one of claims 1 to 3, characterized in that at least one bearing surface (19) of the driving member is a destructible bearing removably mounted relative to the driving member (14).
[0005]
5 / - Stop according to one of claims 1 to 4, characterized in that at least one bearing (20) of the driven member is a destructible bearing removably mounted relative to the driven member (15).
[0006]
6 / - Stopper according to one of claims 1 to 5, characterized in that at least one portion (51, 73, 74) destructible is adapted to be plastically deformed under the effect of the end contact contact between said driven body surfaces (20) and driving member (19).
[0007]
7 / - Stop according to one of claims 1 to 6, characterized in that at least one portion (21) destructible is adapted to be broken under the effect during the cooperation by end of travel contact between said litters (20) driven member and (19) driving member.
[0008]
8 / - Stopper according to one of claims 1 to 7, characterized in that the driven member and the driving member being guided relative to each other at least in relative rotation, each scope (19) d the driving member is integral in rotation with the driving member (14), each bearing surface (20) of the driven member is integral in rotation with the driven member (15), and at least one portion (21, 51, 73, 74) is arranged to be irreversibly deformed by relative end-of-stroke rotation of said driving member and driven member bearing surfaces.
[0009]
9 / - Stopper according to claim 8, characterized in that the drive member (14) and the driven member (15) of the actuator being guided in a helical movement about an axis, each scope (20) d the driven member cooperates by contact with a bearing member surface (19) in at least one radial contact plane.
[0010]
10 / - Stopper according to claim 9, characterized in that each bearing surface (20) of the driven member cooperates by contact with a bearing surface (19) of the driving member in a plurality of contact planes uniformly distributed around the axis of the helical motion.
[0011]
11 / - Stopper according to one of claims 1 to 10, characterized in that it is adapted so that the destruction of at least a portion (21, 51, 73, 74) destructible is visible.
[0012]
12 / - Aircraft actuator with at least one limit stop with absorption of braking energy, characterized in that it comprises at least one stop according to one of claims 1 to 11.
[0013]
13 / - actuator according to claim 12 characterized in that the drive member (14) and the driven member (15) are guided in a helical movement about an axis.
[0014]
14 / - Aircraft comprising at least one actuator having at least one limit stop with absorption of braking energy, characterized in that it comprises at least one stop according to one of claims 1 to 11.
[0015]
15 / - Aircraft comprising at least one actuator -in particular at least one steering actuator- provided with at least one end stop with brake energy absorption, characterized in that it comprises at least one actuator-notably at least one steering actuator according to one of claims 12 or 13.

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同族专利:

公开号 | 公开日

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US20170158313A1|2017-06-08|

FR3044635B1|2018-08-17|

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法律状态:
2016-11-21| PLFP| Fee payment|Year of fee payment: 2 |

2017-06-09| PLSC| Publication of the preliminary search report|Effective date: 20170609 |

2017-12-20| PLFP| Fee payment|Year of fee payment: 3 |

2019-12-19| PLFP| Fee payment|Year of fee payment: 5 |

2020-12-23| PLFP| Fee payment|Year of fee payment: 6 |

2021-12-24| PLFP| Fee payment|Year of fee payment: 7 |

优先权:

申请号 | 申请日 | 专利标题

FR1561882|2015-12-04|

FR1561882A|FR3044635B1|2015-12-04|2015-12-04|ABSORPTION OF ENERGY ABSORPTION OF AIRCRAFT ACTUATOR LIMITER WITH DETABLE DESTRUCTIBLE RACK, ACTUATOR AND AIRCRAFT|FR1561882A| FR3044635B1|2015-12-04|2015-12-04|ABSORPTION OF ENERGY ABSORPTION OF AIRCRAFT ACTUATOR LIMITER WITH DETABLE DESTRUCTIBLE RACK, ACTUATOR AND AIRCRAFT|

US15/367,286| US10837530B2|2015-12-04|2016-12-02|Actuator of an aircraft with an energy-absorbing limit stop with a destructible and detachable bearing surface|

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