EP0715084A1 - A conical rotary actuator and its application to control an aircraft hinge - Google Patents

Abstract

The cylinder consists of coaxially inner (32) and outer (34) housings enclosing at least one annular space containing two sets of vanes (40,44) one fixed to each housing and located alternately inside the space(s) to form variable-volume control chambers. At least one of the two housings has a variable cross-section, so that the vanes' width decreases from one end to the other. The other housing has a constant cross-section, while the inner one has truncated conical and cylindrical sections (38a,38b), meeting at the smaller end of the truncated conical section. The inner and outer housings form, respectively, a rotor and stator, with the inner housing linked to a heating fluid circuit.

Description

The invention relates to a rotary actuator comprising an inner body and at least one outer body mounted coaxially one inside the other so as to be able to be driven in a relative rotational movement, each of the bodies of the actuator carrying pallets arranged alternately to define two series of sealed variable volume control chambers.

The invention also relates to an aircraft control surface comprising at least one hinged panel whose pivoting is controlled by such a rotary actuator.

Usually, the inner body and the outer body of the rotary actuators both have a cylindrical configuration and the height of the pallets carried by each of these bodies is uniform from one end to the other of these pallets. The number of pallets fitted to the actuator depends mainly on the amplitude of the pivoting movement that one wishes to control.

Given this constraint, rotary cylinders are used to control pivoting movements of limited amplitude between two parts. They then have the advantage of having a very small footprint since they can be placed along the relative pivot axis between the parts. By comparison, controlling the same movement using a linear cylinder requires mounting the cylinder on one of the parts, perpendicular to the pivot axis and connecting it to the other part using 'a mechanism including at least one articulated link.

In a rotary actuator, the pressure applied alternately in each of the two series of chambers of the actuator tends to deform the interior and exterior bodies of the actuator in opposite directions. Consequently, the sealing of the chambers essential for the operation of the jack can only be ensured when the latter does not exceed a certain length, for a given control pressure. A rotary cylinder of conventional cylindrical design cannot therefore be used to control the relative rotation of two parts when the hinge moment which it is desired to apply between these parts exceeds a certain value.

When the hinge moment which one wishes to be able to apply between the parts is too high, it is possible to place end to end two rotary jacks, each of which is capable of exerting half of the required hinge moment. However, this leads to a very significant increase in the cost of the installation, in particular due to the multiplication of the bearings serving to transmit the forces between the jacks and each of the parts. Indeed, a conventional cylindrical rotary actuator is normally engaged by two bearings on each of the two parts of which it controls a relative rotational movement. The use of two rotary actuators to control this movement would therefore require eight bearings.

The advantages of space presented by the rotary actuators make particularly attractive the use of such actuators to control the control surfaces of the aircraft and in particular the elevons equipping the supersonic airplanes.

Indeed, the housing of such jacks in the leading edge of the control surfaces would eliminate all the aerodynamic disturbances usually caused by the presence of the linear jacks controlling the control surfaces, despite the possible presence of fairings on these jacks.

Because the control surfaces have different stiffnesses from those of the airfoil, there are differences between the deformations in flight of the control surfaces and of the airfoil. For aerodynamic reasons, the maximum values of these differences should be as small as possible. This can lead to making each control surface in the form of several panels, which must then be ordered independently of each other. In the event that two cylindrical cylinders are used per panel, the installation of the cylinders in the control surface would require the presence of sixteen or twenty-four bearings depending on whether the control surface was cut into two or three panels.

In addition, the redundancy imposed by safety rules generally requires controlling the control surfaces of aircraft using three separate hydraulic circuits. Taking this imperative into account combined with the production of control surfaces in the form of several panels naturally leads to cutting each control surface into three panels. The use of cylindrical rotary jacks would then imply the use of six jacks for each control surface, which would result in the presence of twenty four bearings. This makes this solution too expensive and practically unacceptable.

The invention mainly relates to a rotary cylinder of original design, having in particular, for a given diametrical size, a power substantially greater than that of a conventional cylindrical rotary cylinder.

The invention also relates to a rotary actuator whose original design allows to reduce the number of bearings necessary for the transmission of forces between the cylinder and the parts and, consequently, the cost of an installation using such cylinders.

The invention also relates to a rotary actuator whose original design makes it possible to reduce the torsional deformations of at least one of the internal and external bodies of the actuator, compared to conventional rotary actuators.

According to the invention, these results are achieved by means of a rotary actuator, comprising an inner body and at least one outer body mounted coaxially one inside the other so as to define between them at least one annular space, first pallets and second pallets secured respectively to the inner body and the outer body and arranged alternately in said annular space, to define therein alternately first and second sealed control chambers with variable volume, of which alternating pressurization controls a relative rotation between the interior and exterior bodies, characterized in that at least one of the interior and exterior bodies has a progressive section, so that the first and second pallets have a height which decreases from one end to the another of these palettes.

A rotary actuator meeting this definition will be called hereinafter "conical rotary actuator". This designation, which follows from the evolving nature of the section of the annular space formed between the inner and outer bodies of the jack, should not be considered as limiting the configuration of this annular space to a precise geometric shape.

In a preferred embodiment of the invention, the outer body is cylindrical and has a constant section while the inner body has an evolving section.

In this case, the inner body may in particular have a substantially frustoconical part and a substantially cylindrical part extending an end of relatively small diameter of the substantially frustoconical part.

The relatively large diameter end of the substantially frustoconical part of the inner body then has an outer diameter substantially equal to the inner diameter of the outer body.

In the preferred embodiment of the invention, the inner body constitutes the rotor of the jack while the outer body constitutes the stator. A reverse arrangement can however be adopted in certain applications.

The internal body of the jack is advantageously a tubular body. This characteristic makes it possible to connect the inner body to a temperature conditioning circuit, ensuring the circulation, inside the jack, of a heat transfer fluid capable of heating or cooling the jack according to the conditions of use.

In the preferred embodiment of the invention, the rotary actuator comprises two external bodies mounted coaxially on two parts of the internal body, each of these two parts carrying second pallets arranged alternately with the first pallets carried by each of the external bodies .

The rotary actuator then advantageously has symmetry with respect to a median plane cutting the inner body in its middle.

In addition, the heights of the first and second pallets decrease from the median plane of the jack towards its ends.

Preferably, the inner body comprises, between the two parts carrying the second pallets, a central force transmission part. Likewise, each of the external bodies comprises a terminal force transmission part, near each of the ends of the jack.

The invention also relates to an aircraft control surface, comprising at least one panel articulated on a rear spar of an aircraft wing element, around an articulation axis substantially parallel to this rear spar, and means for controlling the pivoting of the panel around this axis of articulation, characterized in that the pivoting control means comprise at least one conical rotary actuator according to the invention, housed in the panel along its axis of articulation.

The end force transmission parts of the rotary actuator are then mounted in first bearings carried by the rear spar and the central force transmission part of the rotary actuator is mounted in a second bearing carried by the panel. Thanks to this characteristic, it can be seen that the control of a control surface formed by three separate panels requires only nine bearings. The number of bearings is therefore reduced by almost two thirds compared to a control surface which would use conventional cylindrical rotary actuators.

So that the deformations of the airfoil due to its bending are not transmitted to the jack, each of the first bearings is carried by the rear spar so as to be able to turn around a first axis perpendicular to the spar and passing through the axis of articulation of the panel.

To ensure the transmission of forces between the airfoil and the external body of the jack, each of the first bearings is engaged on the end portions of force transmission of the jack by first connecting means in rotation around the hinge axis. of the panel. Likewise, the transmission of forces between the inner tube of the jack and the panel is ensured by second means of connection in rotation about the articulation axis, by which the second bearing is engaged on the central transmission part d 'cylinder forces. These first and second rotational connection means are constituted by grooves or by any equivalent mechanism making it possible to directly transmit the forces near the covering panels of the wing.

In order to ensure the connection between the external body of the jack and the wing in the direction of the axis of articulation of the panel, while allowing a differential deformation of the wing relative to the jack, one of the first bearings is in taken on one of the end portions of transmission of forces from the jack by first means of connection in translation along the aforementioned articulation axis. On the contrary, the other first bearing is free to move parallel to this axis of articulation relative to the other end portion of the force transmission of the jack. In a comparable manner, the second bearing is engaged on the central force transmission part of the jack by second means of connection in translation along the axis of articulation.

In a preferred embodiment of the control surface according to the invention, this control surface comprises at least two panels interconnected by at minus a shackle, a rotary actuator being housed in each of the panels.

• la figure 1 est une vue de dessus d'un avion supersonique, représentant notamment l'implantation des élevons dont la commande peut être assurée à l'aide de vérins rotatifs coniques conformes à l'invention ;
• la figure 2 est une vue de dessus, avec arrachement partiel, représentant à plus grande échelle l'implantation des vérins de commande de l'un des élevons interne de l'avion illustré sur la figure 1 ;
• la figure 3 est une vue de dessus, à plus grande échelle et en coupe longitudinale partielle représentant à plus grande échelle l'un des vérins coniques de commande de l'élevon interne de la figure 2 ;
• la figure 4 est une vue en perspective éclatée d'une partie du vérin de la figure 3 ;
• la figure 5 est une vue en coupe selon la ligne V-V de la figure 3, représentant à plus grande échelle l'un des paliers par lesquels les vérins sont reliés au longeron arrière de la demi-voilure correspondante ; et
• la figure 6 est une vue en coupe selon la ligne VI-VI de la figure 3 représentant le palier par lequel le vérin est relié au panneau correspondant de l'élevon interne.

A preferred embodiment of the invention will now be described, by way of nonlimiting example, with reference to the appended drawings, in which:

• Figure 1 is a top view of a supersonic aircraft, representing in particular the location of the elevons whose control can be ensured using conical rotary cylinders according to the invention;
• Figure 2 is a top view, partially broken away, showing on a larger scale the location of the control jacks of one of the internal elevations of the aircraft illustrated in Figure 1;
• Figure 3 is a top view, on a larger scale and in partial longitudinal section showing on a larger scale one of the conical cylinders for controlling the internal elevon of Figure 2;
• Figure 4 is an exploded perspective view of part of the jack of Figure 3;
• Figure 5 is a sectional view along the line VV of Figure 3, showing on a larger scale one of the bearings by which the cylinders are connected to the rear spar of the corresponding half-wing; and
• Figure 6 is a sectional view along line VI-VI of Figure 3 showing the bearing by which the cylinder is connected to the corresponding panel of the internal elevon.

A preferred embodiment of the conical rotary actuator according to the invention will now be described in its application to the control of the elevons of a supersonic aircraft. It is pointed out that the advantages provided by the conical rotary actuator according to the invention can lead to the use of one or more actuators of this type in many other applications.

In FIG. 1, each of the half-wings of a supersonic aircraft has been designated by the reference 10. Each half-wing 10 has on its trailing edge an inner elevon 12, a middle elevon 14 and an outer elevon 16. These elevons constitute control surfaces fulfilling different functions, in particular of roll and depth.

Each of the elevons 12, 14 and 16 is pivotally mounted on the rear spar 18 (FIG. 2) of the corresponding half-wing, about an axis xx 'substantially parallel to this spar. Each elevon has a limited travel, for example plus or minus 25 ° relative to its middle position where it is aligned with the half-wing.

To take into account both the different rigidity of the elevons 12 and 14 and the half-wings 10, as well as the need to control each of the elevons by three separate hydraulic circuits in order to ensure the redundancy necessary for safety, each of the elevons 12 and 14 is cut into three adjacent articulated panels, of substantially equal dimensions, in the direction defined by the rear spar 18. These three panels are designated by the references 12a, 12b and 12c for the internal elevons 12 and 14a, 14b and 14c for the middle elevons 14. According to the invention, each of the panels 12a, 1b and 12c and 14a, 14b and 14c is controlled by a conical rotary actuator 16. More specifically, the three conical rotary actuators 16 associated with each of the elevations 12 and 14 are identical.

There is shown in more detail in FIG. 2 the layout of the three jacks 16 used to control the three panels 12a, 12b and 12c of one of the internal elevons 12. The layout of the jacks controlling the other elevons is carried out according to the same principle. It will therefore not be described.

As illustrated in particular in FIG. 2, the three jacks 16 ensuring the control of elevons 12 have a symmetry of revolution about an axis coincident with the pivot axis xx 'of the elevon. Each cylinder 16 is housed in the trailing edge of the corresponding panel 12a, 12b or 12c.

More specifically, each of the conical rotary cylinders 16 comprises a central force transmission part connected by a bearing 20 to the front spar 22 and to the strong central rib 24 of the corresponding panel.

Furthermore, each of the conical rotary actuators 16 comprises two end force transmission parts which are connected by two bearings 26 to the rear spar 18 of the corresponding half-wing 10.

Each of the conical rotary actuators 16 is supplied with pressurized hydraulic fluid by a hydraulic block 30. In the case of internal elevations 12, the hydraulic blocks 30 are mounted on the rear spar 18 of the airfoil, so as to provide space between this spar and the leading edge of each of the elevon panels a space allowing in particular the passage of a certain number of pipes connecting the engines to the fuselage of the aircraft. In the case of control surfaces installed differently such as the intermediate elevations 14 in FIG. 1, the hydraulic blocks can be mounted directly on the jacks 16.

The structure of one of the conical rotary cylinders 16 according to the invention will now be described in detail with particular reference to Figures 3 and 4.

As illustrated in these figures, in the embodiment shown, the conical rotary actuator 16 according to the invention comprises a tubular inner body 32 forming a rotor and two tubular outer bodies 34 forming a stator, mounted coaxially.

More specifically, the tubular inner body 32 includes a central force transmission part 36, intended to be engaged on the bearing 20 in a manner which will be described in more detail later. On either side of this central force transmission part 36, the internal body 32 comprises two tubular parts 38, symmetrical with respect to the median plane of the jack, coincident with the cutting plane VI-VI in FIG. 3.

The two outer bodies 34 are identical and each of them is received on one of the tubular parts 38 of the internal body 32, so as to delimit between this part 38 and the external body 34 corresponding a sealed annular space with respect to screw from the outside. Near the ends of the jack, each outer body 34 has on its outer surface an end portion 62 for transmitting forces, designed to be engaged on the corresponding bearing 26, in a manner which will be described in more detail later.

Each of the tubular parts 38 of the inner body 32 carries on its outer surface vanes 40 oriented radially outward (Figure 5). These pallets 40 are regularly distributed over the periphery of the tubular part 38. They are by example four in number in the embodiment shown. The edges of the pallets 40 facing the corresponding external body 34 carry seals 42 ensuring the tightness of the contact between these two parts.

In a comparable manner, each of the external bodies 34 carries on its internal surface pallets 44 oriented radially inwards. The pallets 44 are regularly distributed around the axis of the cylinder and their number is the same as that of the pallets 40, so that the pallets 40 and 44 are arranged alternately around the axis of the cylinder. In the embodiment shown, each of the external bodies 34 therefore also comprises four pallets 44. The edges of the pallets 44 facing the internal body 32 carry seals 46 which are in leaktight contact with the external surface of the tubular part 38 corresponding to the inner body 32.

Due to the arrangement which has just been described and according to a conventional configuration in rotary actuators, the annular space delimited between each external body 34 and the tubular part 38 of the internal body 32 is divided by the alternating pallets 40 and 44 in two series of variable volume chambers, designated by the references 48 and 50 in FIG. 5.

The mounting of each of the outer bodies 34 on the inner body 32 of the jack is carried out so that a relative rotation between these two parts is possible. For this, the end of each of the outer bodies 34 cooperates with the ends of the corresponding tubular part 38 of the inner body 32 by two bearings 52 and 54 such as needle bearings.

The hydraulic block 30 (FIG. 2) associated with each of the jacks 16 is connected to the two external bodies 34 of the latter by pipes 56. More specifically, a first group of pipes 56 opens into the chambers 48, while a second group of piping 56 opens into the chambers 50.

Thanks to this arrangement, it is possible to pressurize the chambers 48 while venting the chambers 50, or vice versa, so as to control the rotation of the internal body 32 in the external bodies 34 in one or the other. 'other way.

According to the invention, the section of at least one of the inner 32 and outer 34 bodies is scalable, so that the pallets 40 and 44 have a height which decreases from one end to the other of these pallets.

In the embodiment illustrated in the figures, this characteristic is obtained by giving the external tubular body 34 a uniform section, that is to say a cylindrical shape and by giving each of the tubular parts 38 of the internal body 32 a section scalable.

In the embodiment shown in FIGS. 3 and 4, the evolving section of each of the tubular parts 38 of the inner body 32 is obtained by forming in each part 38 a substantially frustoconical part 38a, the diameter of which decreases from the central force transmission part 36, and a substantially cylindrical part 38b, extending the relatively small diameter end of the substantially frustoconical part 38a, to the corresponding end of the jack 16.

As already indicated, this form is given only by way of example, the generator of each of the tubular parts 38 can take a different shape, for example straight or curved.

In this configuration, the relatively large diameter end of the substantially tapered portion 38a of each of the tubular portions 38 has an outer diameter substantially equal to the diameter of the interior body 34 received on this tubular portion 38. Each of the pallets 40 and 44 has a approximately triangular in shape. A simple calculation makes it possible to show that, for the same active surface of the pallets and for a cylinder having the same external diameter, the shape given to the pallets 40 and 44 in the conical rotary cylinder according to the invention makes it possible to increase by 16.7 % the cylinder efficiency compared to a traditional cylindrical rotary cylinder.

In addition, the shape of the internal body 32 constituting the cylinder rotor reduces the deformation of this torsional part by linear increase in its diameter. This characteristic makes the torsional deformations of the internal body 32 negligible compared to the deformations resulting from the pressurization of the chambers 48 or 50.

To allow the mounting and dismounting of each of the outer bodies 34 of the conical rotary actuator 16, the tubular inner body 32 is extended at each of its ends by a threaded part 39 (FIG. 4) onto which a locking nut 56 is screwed. A roller stop 58 is interposed between the nut 56 and an end face of the corresponding external body 34, so as to allow the internal body 32 to be locked in translation without preventing rotation. A hollow screw 60 is screwed into each of the ends of the inner body 32 so as to block the corresponding nut 56.

Each end portion 62 of force transmission is engaged on one of the bearings 26 according to an arrangement which will now be described with reference to FIG. 5.

Each of the bearings 26 is mounted on the rear spar 18 of the corresponding half-canopy 10 so as to be able to rotate about an axis yy 'perpendicular to the rear spar 18 and passing through the hinge axis xx' of the corresponding panel such that the panel 12a in FIG. 5.

To this end, each of the bearings 26 has a flat face 64 which is supported on the rear face of the rear spar 18 by means of a needle stop 68. A cylindrical part 70 of the bearing 26 projects from the flat face 64 along the axis yy ', crossing a circular passage formed in the rear spar 18. On the front face of the rear spar 18, a nut 72 is screwed onto a threaded part of the cylindrical part 70, so as to cooperate with this front face of the side member 18 by a second needle stop 74.

Furthermore, each of the bearings 26 is engaged with the end portion 62 for transmitting forces from the corresponding external body 34 of the jack, by means of connection means in rotation about the hinge axis xx 'of the panel. 12a. In the embodiment illustrated in FIG. 5, these rotational connection means consist of grooves 76 in the involute of a circle, formed on the end portions 62 of force transmission and by complementary grooves 77 formed in a ring 28 of the bearing 26, surrounding the aforementioned end part.

It should be noted that this arrangement makes it possible to transmit the forces between the jack and the corresponding half-wing near the covering panels of the wing. This reduces the size of the bearings 26 between the rear spar 18 and the actuator 16 itself. The space thus freed facilitates the routing of the pipes coming from the aircraft engines.

In addition, one of the bearings 26 (for example that which is not shown in FIG. 5) carries means for translational connection between this bearing and the corresponding external body 34, along the axis of articulation xx ' of panel 12a. These translational connection means may in particular be constituted by flanges integral with the bearing and coming to be placed on either side of the ends of the grooves 76 which project from the external surface of the corresponding external body 34. On the contrary, the other bearing 26 is free in translation on the end portion 62 of corresponding force transmission.

The arrangement which has just been described ensures the connection in translation of the jack 16 and the rear spar 18 of the corresponding half-canopy 10, while allowing a relative displacement necessary for the flexing of the half-canopy.

A description will now be given with reference to FIG. 6 of an embodiment of the bearing 20 connecting the internal body 32 of the jack 16 to the panel 12a, with reference to FIG. 6.

As illustrated in this figure, the bearing 20 is fixed on a force introduction fitting 78, itself fixed to the front spar 22 and to the strong central rib 24 (Figure 2) of the corresponding panel 12a.

This bearing 20 cooperates with the central part 36 for transmitting forces from the jack 16 by means of rotational connection. As for the bearings 26, these rotational connecting means comprise grooves 80 in the form of a circle, formed on the external surface of the central part 36 for transmitting forces, and complementary grooves 81 formed in a ring 82 of the bearing 20 surrounding this central part 36.

In addition, means are provided for ensuring the connection in translation between the bearing 20 and the central part 36 of force transmission of the jack 16, along the pivot axis xx 'of the panel 12a. These translational connection means comprise for example two flanges 84, integral with the bearing 20 and situated on either side of the ends of the grooves 81 which project from the external surface of the internal body 32.

As illustrated very schematically at 86 in FIG. 2, the hollow nature of the internal tubular body 32 of each of the jacks 16 makes it possible to connect the internal bodies 32 in series by a pipe 86 belonging to a temperature conditioning circuit d '' a heat transfer fluid. It is thus possible to circulate in the cylinders a heat transfer fluid allowing in particular to heat the latter to facilitate their actuation when the outside temperature is too low.

So that the failure of any of the three circuits fitted to the aircraft is without consequence on the simultaneous actuation of each of the three panels 12a, 12b and 12c of the elevon 12, at least one shackle 88 is preferably placed between each pair of adjacent elevon panels, substantially mid-chord of these panels. The shackles 88 also make it possible to avoid the rotation of each of the panels around its central rib 24, which could occur. due to its rotational drive by a single bearing 20.

In addition to the intrinsic advantages of the conical rotary actuators which have been stated previously, the application of these actuators to the control of the control surfaces of an aircraft provides numerous advantages.

Thus, the installation of the jacks in the leading edge of the control surfaces, usually unoccupied, frees up a space in an usually very congested area located near the rear of the rear spar of the wing.

Furthermore, the transfer of forces between the jacks and the wing takes place near the covering panels of the latter, which reduces the forces introduced into the structures. It is thus possible to hollow out the structure of the bearing 20 near its axis of symmetry.

As already pointed out, a conical rotary actuator according to the invention can be used in many industrial sectors, since an alternating rotation movement of relatively small amplitude must be controlled. Furthermore, depending on the effort to be exerted, this jack can be single or double, like the one which has just been described. The number of pallets is adapted to the amplitude of the movement to be controlled.

Claims (16)

Rotary actuator, comprising an inner body (32) and at least one outer body (34) mounted coaxially one inside the other so as to define at least one annular space, first pallets (40) and second pallets (44) secured respectively to the inner body and the outer body and arranged alternately in said annular space, to define therein first (48) and second (50) sealed control chambers with variable volume, including pressurization alternating controls relative rotation between the interior (32) and exterior (34) bodies, characterized in that at least one of the interior (32) and exterior (34) bodies has an evolving section, so that the first (40) and the second pallets (44) have a height which decreases from one end to the other of these pallets. Rotary cylinder according to claim 1, characterized in that the outer body (34) has a constant section while the inner body (32) has an evolving section. Rotary cylinder according to claim 2, characterized in that the internal body (32) has a substantially frustoconical part (38a) and a substantially cylindrical part (38b) extending a relatively small end of the substantially frustoconical part. Rotary cylinder according to claim 3, characterized in that a relatively large diameter end of the substantially frustoconical part of the inner body (32) has an outer diameter substantially equal to the inner diameter of the outer body (34). Rotary cylinder according to any one of the preceding claims, characterized in that the internal body (32) and the external body (34) respectively constitute a rotor and a stator. Rotary cylinder according to any one of the preceding claims, characterized in that the internal body (32) is a tubular body capable of being connected to a circuit (86) for conditioning the temperature of a heat-transfer fluid. Rotary cylinder according to any one of the preceding claims, characterized in that it comprises two external bodies (34) mounted coaxially on two parts (38) of the internal body (32), each of these two parts carrying first pallets ( 40) arranged alternately with the second pallets (44) carried by each of the outer bodies (34). Rotary cylinder according to claim 7, characterized in that it has a symmetry with respect to a median plane cutting the inner body (32) in its middle. Rotary cylinder according to any one of claims 7 and 8, characterized in that the heights of the first and second pallets (40,44) decrease from the median plane of the cylinder towards its ends. Rotary cylinder according to any one of claims 7 to 9, characterized in that the internal body (32) comprises, between the parts (38) carrying the first pallets (40), a central part (36) for transmitting forces, each of the external bodies (34) comprising an end part (62) for transmitting forces, near each of the ends of the jack. Aircraft control surface, comprising at least one panel (12a, 12b, 12c), articulated on a rear spar (18) of an aircraft wing element (10), around an axis of articulation (xx ' ) substantially parallel to this rear spar, and means for controlling the pivoting of the panel about this articulation axis, characterized in that the pivoting control means comprise at least one jack (16) according to any one of previous claims, housed in the panel (12a, 12b, 12c) along said axis of articulation (xx '). Aircraft control surface according to claims 10 and 11 combined, characterized in that the force transmission end parts (62) of the rotary actuator (16) are mounted in first bearings (26) carried by the rear spar (18 ) and that the central part (36) of force transmission of the rotary actuator is mounted in a second bearing (20) carried by the panel (12a). Aircraft control surface - according to claim 12, characterized in that each of the first bearings (26) is carried by the rear spar (18) so as to be able to rotate around a first axis (yy ') perpendicular to the spar and passing through the hinge pin (xx ') of the panel. Aircraft control system according to any one of claims 12 and 13, characterized in that each of the first bearings (26) is engaged on the end portions (62) of transmission of forces from the jack by first means (76 ) of connection in rotation about the axis of articulation of the panel and that the second bearing (20) is engaged on the central part (36) of transmission of forces of the jack by second means (80) of connection in rotation around the axis of articulation. Aircraft control system according to any one of claims 12 to 14, characterized in that one of the first bearings (26) is engaged on one of the end portions (62) of force transmission of the jack by first connecting means in translation along the axis of articulation of the panel and that the second bearing (20) is engaged on the central part (36) of transmission of forces from the jack by second connecting means (84) in translation along the axis of articulation. Aircraft control surface according to any one of claims 11 to 15, characterized in that the control surface (12) comprises at least two panels (12a, 12b) interconnected by at least one shackle (88), a rotary actuator (16) being housed in each of the panels.

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