EP2877732A1

EP2877732A1 - Flap-driving device, especially for an adaptive nozzle

Info

Publication number: EP2877732A1
Application number: EP13756587.5A
Authority: EP
Inventors: Olivier Kerbler; Olivier Gilo; Pierre Caruel
Original assignee: Aircelle SA
Current assignee: Safran Nacelles SAS
Priority date: 2012-07-27
Filing date: 2013-07-23
Publication date: 2015-06-03
Also published as: CA2877068A1; WO2014016512A1; CN104520568A; US20150152811A1; FR2993932B1; FR2993932A1; RU2015106353A; BR112014032860A2

Abstract

The invention relates to a flap-driving device for the nozzle of a turbojet nacelle, said nozzle comprising at least one rotatably movable flap, said device comprising at least one control ring (311) that is rotatably movable along the circumference of said nacelle during the activation of driving means (39, 41), and comprising at least one flap-driving connecting rod (2) connected to said control ring and to a flap, the activation of said means for driving the control ring (311) triggering a movement of said connecting rods (21) in translation. The device according to the invention is characterised in that the means for driving the control ring (311) comprise at least one longitudinal driving cylinder comprising at least one pin (39) connected to at least one lever-forming assembly (41, 71), said assembly being directly or indirectly secured to said ring.

Description

Flap drive device in particular for adaptive nozzle

The present invention relates to a flap drive device in particular for an aircraft jet engine nacelle adaptive nozzle. The invention also relates to a thrust reverser incorporating such an adaptive nozzle flap driving device. Finally, the present invention relates to a turbojet engine nacelle comprising at least one thrust reverser according to the invention.

An aircraft is moved by several turbojets housed each in a nacel. The nacel generally has a tubular structure comprising an air inlet upstream of the turbojet engine, a median section intended to surround a fan of the turbojet engine, a downstream section housing the thrust reverser means and intended to surround the combustion chamber of the engine. turbojet engine and generally terminated by an ejection nozzle located downstream of the turbojet engine.

This nacelle is intended to house a turbofan engine capable of generating through the blades of the rotating fan a flow of hot air from the combustion chamber of the turbojet engine, and a cold air flow circulating at the outside of the turbojet engine through an annular channel called vein.

The thrust reversal device is, during landing of the aircraft, intended 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 thrust reverser device obstructs the stream of cold air flow and directs the latter towards the front of the nacelle, thereby generating a counter-thrust which is added to the braking of the wheels of the aircraft, the means implemented to achieve this reorientation of the cold air flow vary depending on the type of inverter.

The means implemented to achieve this reorientation of the cold flow vary according to the type of inverter. However, the structure of an inverter generally comprises movable covers movable between, on the one hand, an extended position in which they open in the nacelle a passage intended for the deflected flow, and on the other hand, a retracted position in which they close this passage. These covers can perform a deflection function or simply activation other means of deflection. Furthermore, in addition to its thrust reversal function, the reverser cowl belongs to the rear section of the nacelle and has a downstream part forming the ejection nozzle for channeling the ejection of the air flows.

The optimum section of the ejection nozzle can be adapted according to the different flight phases, namely the take-off, climb, cruise, descent and landing phases of the aircraft. The already well-known advantages of such adaptive nozzles are in particular the reduction of noise or the reduction of fuel consumption.

The variation of this section, illustrating the section variation of the cold air flow vein, can be performed by a partial translation of the inverter cover.

The variation of the outlet section of the cold air flow duct can also be achieved through a plurality of flaps, also called deflectors, rotatably mounted at a downstream end of the hood, and adapted to pivot between a retracted position wherein they are in the continu ity of the aerodynamic line of the secondary air flow vein, an extended position causing a sectional variation of the nozzle, and a plurality of intermediate positions at said retracted and deployed positions.

It is known from the prior art to connect each of the flaps to a driving ring, located on the circumference of the nacelle, by a system of connecting rods. The ring is rotatable about the longitudinal axis of the nacelle, and the rotation of the ring causes the rotation and synchronization of the nozzle panels through the connecting rod systems.

By way of example, mention may be made of the prior art document US 2008/0000235, which describes such a device for rotating rotary flaps of an adaptive nozzle.

According to this document of the prior art, the control ring comprises a plurality of guide lights within which is inserted a finger integral with a flap. The rotation of the crown causes a translation of the finger in the light and simultaneously the rotation of each flap.

A disadvantage associated with this type of training is that the finger flexes, which can create fatigue in the finger, may eventually cause the rupture of the finger and tearing of the flaps. The present invention also aims to overcome the drawbacks of the prior art, and relates for this purpose to a flap drive device in particular for an aircraft jet engine nacelle adaptive nozzle, said nozzle comprising at least one movable flap in rotation adapted to pivot at least towards a position causing a variation of the section of the nozzle, said device comprising at least one control ring rotatable along the circumference of said nacelle during the activation of drive means of the control ring, said driving device comprising at least one shutter drive rod connected, on the one hand, directly or indirectly, to said control ring and, on the other hand, directly or indirectly, to at least one flap, the activation of said driving means of the control ring causing a displacement in translation of said rods, said device being remarkable in that the driving means of the control ring comprise at least one longitudinal drive cylinder comprising at least one rod connected to at least one lever assembly, said at least one lever assembly being integral directly or indirectly with said crown.

Thus, by providing a control ring driven in rotation by means of a lever assembly, the forces experienced by the cylinder rod during the rotational drive of the crown ring are substantially reduced.

In addition, the lever assembly makes it possible to increase the precision of displacement of the drive rod, which makes it possible to adapt in a particularly precise manner the outlet section of the ejection nozzle as a function of the flight phases in the engine. which is the aircraft.

According to all the optional features of the present invention:

- The lever assembly is connected to the control ring by means of at least one carriage shaped to translate in an oblong hole of said control ring;

at least one flap drive rod is connected to at least one of said lever assemblies;

at least one of said lever assemblies is an L-shaped assembly;

- alternatively, at least one of said lever assemblies is a T-assembly; the connection between said longitudinal drive cylinder rod and said lever assembly is a slide connection;

alternatively, the connection between said longitudinal drive cylinder rod and said lever assembly is a vertical axis pivot connection;

the connection between said shutter drive rod and the lever assembly is a slide link;

alternatively, the connection between said flap drive rod and said lever assembly is a vertical axis pivot connection;

the longitudinal drive shaft may be connected to the lever assembly via at least one carriage;

the flap drive bell can be connected to the lever assembly via at least one carriage;

- The control ring extends substantially over the entire circumference of the nacelle;

- In turn, the control ring comprises a plurality of independent sections rotatable along the circumference of said nacelle during activation of the drive means.

The present invention also relates to a thrust reverser for an aircraft turbojet engine nacelle comprising at least one downstream cover comprising in its downstream part at least one adaptive nozzle comprising at least one flap alternately at least between a retracted position and a deployed position. , remarkable in that said cover comprises at least one flap drive device of said nozzle according to the invention.

Finally, the invention relates to an aircraft turbojet engine nacelle comprising at least one thrust reverser according to the invention.

Other characteristics, objects and advantages of the present invention will appear on reading the detailed description which follows and on examining the appended figures, in which: FIG. 1 represents a nacelle for a turbojet engine equipped with an adaptive nozzle with rotating flaps activated thanks to the training device according to the invention;

Figure 2 defines the trihedron (L, T, V);

FIG. 3 illustrates a first embodiment of the training device according to the invention;

FIGS. 4a to 4c illustrate, in plan view, the training device according to the first embodiment in the neutral, advanced and retracted positions;

Figure 5 is a top view of a portion of the control ring connected to the drive rod by a carriage; FIG. 6 illustrates a second embodiment of the training device according to the invention;

FIGS. 7a to 7c illustrate, in plan view, the drive device according to the second embodiment in the neutral, advanced and retracted positions;

Figure 8 illustrates a variant of the drive in rotation of the crown;

FIGS. 9 to 11 correspond respectively to FIGS. 6 to 8, the drive device being made according to a first variant of a third embodiment;

Figures 12 to 14 correspond to the figures respectively

9 to 1 1, the drive device being made according to a second variant of the third embodiment;

Figure 15 shows a common alternative to both variants of the third embodiment;

Figure 16 illustrates an example of connection between the drive rod and a flap. In addition to the figures, identical or similar references denote identical or similar organs or sets of members.

Furthermore, the terms "upstream" and "downstream" are used in the description, with reference to the direction of flow of air in the nacelle, the upstream of the nacelle corresponding to an air intake zone while that the downstream corresponds to an exhaust zone of the air. Referring to Figure 1, schematically showing a nacelle 1 comprising a thrust reverser cover 3 equipped in its downstream portion of a nozzle 5 for ejection of the secondary air flow.

The nozzle 5 is adaptive, that is to say that the section of the ejection nozzle can be adapted according to the different phases of flight to vary the section of the secondary air flow stream.

The section variation of the ejection nozzle is achieved thanks to a plurality of flaps 7, also called deflectors, rotatable about an axis substantially transverse to the longitudinal axis 9 of said nacelle 1.

These flaps are connected to a control ring 1 1 mounted on the periphery of the nacelle 1.

In the present application, and as shown in Figure 2 partially illustrating the control ring January 1 view from above, the term "longitudinal" represents any axis collinear with the longitudinal axis L of the nacelle, while the term "transverse" represents any axis collinear with the axis T tangent to the crown of control. Finally, the term "vertical" is understood as any axis collinear with the axis V forming the direct trihedron (L, T, V).

The flap drive device according to the invention comprises a control ring made according to the various embodiments that will be described, rotatable about the longitudinal axis of the nacelle, the drive means of the invention. said ring, and at least one nozzle flap driving rod.

In this application, the term "control ring" means a ring of substantially annular shape, extending substantially over the entire circumference of the nacelle.

Referring to FIG. 3, illustrating the drive means of a control ring 11 January 1 made according to a first embodiment.

The control ring 1 1 1 has an inner face 13 comprising teeth 15 shaped to mesh with teeth 1 7 of a pinion 19 rotated by a motor, for example electric, not shown.

The control ring January 1 is notched on the whole of the inner face 1 3 or, alternatively, on one or more portions of said inner face. Fig u res 4a to 4c illustrate the control ring 11 January partially shown in top view.

The coupling channel 1 1 1 is connected to a drive rod 21, one end 23 of which is connected to the flap (not shown) of the nozzle.

The drive rod 21 is integral at its end 25 with a vertical guide pin 27 shaped to translate in a guide hole 29 formed on the outer face 31 of the control ring 11 January.

The outer face represents the face of the crown farthest from the longitudinal axis of the nacelle, while the inner face is the face of the crown the closer us dud it long axis itud inal. Lateral walls transverse to the longitudinal axis of the nacelle connect said inner and outer faces of the ring.

According to a variant not shown in the figures, the guide light can be made on the inner face of the control ring January 1, or can still cross radially said ring.

The guiding light 29 is oblique and allows the rod 21 to move to an "advanced" position shown in FIG. 4b, a position obtained when the control ring is rotated in a clockwise direction when the crown is viewed. from upstream of the nacelle downstream. The guide light also allows a displacement in the so-called "retracted" position of the connecting rod 21, a position obtained for a rotation of the crown in the counterclockwise direction when the crown is viewed from the upstream of the nacelle towards the downstream, and shown in Figure 4c.

For a so-called "neutral" position shown in FIG. 4a, the longitudinal axis 32 of the driving rod 21 is substantially in the middle of the guide light 29.

However, when the desired amplitude of the displacement of the bielle in the posit ion preceded it is d isti ncte the desired amplitude of the displacement of the connecting rod in retracted position, the longitudinal axis of the connecting rod in neutral position does not It is of course more in the middle of the guiding light, but shifted close to one or the other end of the guiding light.

Alternatively, as shown in Fig 5, the guide pin 27 is sol idaire of a carriage 33 translating in the guiding light 29. Typically, the connection between the guide pin 27 and the light The guiding method can be modeled by means of a "plane-plane" and "cylinder-cylinder" type, which avoids having a point contact between the guiding finger and the guiding light.

Referring now to Figures 6 to 8, showing a second embodiment of the flap drive device according to the invention.

In this embodiment of the invention, the control ring 21 1 is similar to the control ring 11 January described with reference to the first embodiment of realism except that the inner face has more teeth .

The control ring 21 1 is mounted on a plurality of fixed rails 34 (a single rail 34 is visible in Figure 6) and integral with the nacelle. By way of example, there are as many rails as there are driving rods connected to the control crown.

Typically, a rail 34 adopts a T shape and has an aperture 35 shaped to allow the passage of the control part 21 1, and ends with a plate 36 shaped to allow the movement of the driving rod 21. There are as many rails 34 as there are shutter drive rods 21.

Alternatively, the control ring is mounted on a single guide rail (not shown) comprising a circumferential ring integral with the nacelle and having a plurality of plates all integral with the circumferential ring and each allowing the movement of the driving rod. corresponding.

The drive means of the ring 21 1 comprise a transverse drive, comprising a transverse rod 37 secured to said ring.

Alternatively, the rod 37 has an angle of between +/- 45 ° with respect to the transverse axis T.

The control ring 21 1 is connected to the drive rod 21 whose end 23 is connected to the flap (not shown) of the nozzle.

The drive rod 21 is secured at its end 25 of the vertical guide pin 27 translating in the guide hole 29 formed on the outer face 31 of the control ring 21 1.

As previously, according to a variant not shown in the figures, the guide light can be made on the inner face of the ring 21 1, or can still cross radially said ring. Referring to Figs 7a to 7c, illustrating the control ring 21 1 partially shown in plan view.

In the same way as has been described with reference to FIGS. 4a to 4c, the guiding light 29 is oblique and allows the link 21 to move towards the advanced position as represented in FIG. 7b, position reached when the check is made. The drive has been activated so as to allow rotation of the control ring 21 1 in the clockwise direction.

When the drive cylinder is activated so as to allow a rotation in the counterclockwise direction of the control ring 21 1, the shutter drive rod is in the retracted position as shown in Figure 7c.

In the neutral position, the longitudinal axis 32 of the driving rod 21 is substantially in the middle of the guide light 29.

However, as before, when the desired amplitude of the displacement of the rod in the advanced position is different from the desired amplitude of the displacement of the rod in the retracted position, the longitudinal axis of the connecting rod in the neutral position is of course no longer in the middle of the guide lumen, but shifted close to either end of the guide lumen.

The control ring 21 1 can be rotated by the activation of a plurality of drive cylinders whose end of each rod is integral with the ring and is substantially aligned with each drive rod.

Alternatively, and as shown in FIG. 8, the control ring 21 1 is rotated by a single drive cylinder comprising a single rod 37. Activation of the drive cylinder causes rotation of the neck Control 21 1, which leads together the movement of all the drive rods 21 flap.

Alternatively, the control ring is rotated by two drive cylinders whose activation causes the rotation of the control ring, causing in combination the movement of all the drive rods.

According to a variant not shown and already explained with reference to Fig ure 5, guiding finger 27 can be secured to a carriage 33 translating into the guide slot 29, and the connection between the guide pin 27 and the guide light can be modeled by a connection of the "plane-plane" and "cylinder-cylinder" type.

Referring now to Figures 9 to 15, illustrating a third embodiment flap drive device according to the invention.

In this embodiment of the invention, the driving means of the control ring 311 comprise a longitudinal drive cylinder comprising a longitudinal rod 39 connected to said ring by a lever assembly 41.

According to an alternative not shown, the rod 39 has an angle of between +/- 45 ° with respect to the longitudinal axis L.

The rod 39 of the longitudinal drive cylinder is preferably connected to the end portion of the lever assembly 41, which allows on the one hand to reduce the forces that apply to the cylinder rod and secondly to allow movement of the drive rod with good accuracy.

However, it is obviously not excluded to switch the location of the drive rod with the location of the cylinder rod if the skilled person finds a particular interest.

The rod 39 is integral at its end 43 with a guiding pin 45 shaped to translate in a first oblong hole 47 of the lever assembly 41.

The mechanical connection between the guiding pin 45 and the oblong hole 47 can be modeled by a sliding connection having a direction along a longitudinal axis 48 of the lever assembly 41.

According to a variant not shown, the guide pin 45 is secured to a carriage translatable in the oblong hole 47, taking the principle of the variant illustrated with reference to Figure 5. The connection between the guide pin 45 and the hole oblong 47 can then be modeled by a connection of the "plane-plane" and "cylinder-cylinder" type.

The lever assembly 41 has an "L" shape, one end 49 of which is integral with a guide pin 51 shaped to translate in an oblong hole 53 inscribed on the outer face 55 of the control ring 311.

Of course, such an assembly can adopt any other geometric shape since it allows a reduction of the forces exerted on the rod 39 of the drive cylinder. The lever assembly 41 comprises a second oblong hole 57 shaped to receive a guide pin 59 integral with an end 61 of the shutter drive rod 21.

The mechanical connection between the guiding pin 59 and the oblong hole 57 can be modeled by a sliding connection having the direction of the longitudinal axis 48 of the lever assembly 41.

As previously, according to a variant not shown, the guide pin 59 can be secured to a carriage translatable in the oblong hole 57 incorporating the principle of the variant illustrated with reference to Figure 5. The connection between the guide pin 59 and the oblong hole 57 can then be modeled by a connection of the "plane-plane" and "cylinder-cylinder" type.

The control ring 31 1 is mounted on a plurality of rails 63 fixed (a single rail being shown in Figure 9) and integral with the nacelle.

Typically, a rail 63 has an opening 65 provided for the passage of the control ring 31 1 and ends with a plate 66 supporting the lever assembly 41. There are as many rails 63 as there are shutter drive rods 21.

Alternatively, the control ring is mounted on a single guide rail (not shown) comprising a circumferential ring integral with the nacelle and having a plurality of plates all integral with the circumferential ring and each supporting a lever assembly.

The lever assembly 41 is connected to the plate 66 by a vertical axis pivot connection 67 positioned substantially on a longitudinal axis 68 of the oblong hole 53 when said assembly is in a position corresponding to a neutral position of the driving rod. 21.

The rod 39 of the drive cylinder and the drive rod 21 are on the same side of said axis 68.

Referring to Figures 10a to 10c, illustrating the control ring 31 1 partially shown in top view.

Figure 10a illustrates a neutral position of the drive link 21, in which position the axis 48 of the lever assembly 41 is substantially transverse.

FIG. 10b illustrates an advanced position of the driving rod 21. This position is obtained for a displacement of the rod 39 of the longitudinal cylinder in a direction such that the lever assembly pivots in a clockwise direction, causing the guiding finger 51 of the lever assembly 41 to translate into the oblong hole 53. of the control ring 31 1 so as to rotate said ring counterclockwise.

FIG. 10c illustrates a retracted position of the driving rod 21, a position obtained for a displacement of the rod 39 of the longitudinal cylinder in a direction such that the lever assembly pivots in the counterclockwise direction, causing a translation of the finger guide 51 of the lever assembly 41 in the oblong hole 53 of the control neck 31 1 so as to rotate said crown clockwise.

The control ring 31 1 can be rotated by the activation of a plurality of drive cylinders, the end of each rod is integral with a lever assembly.

Alternatively, and as shown in FIG. 11, the control ring 31 1 is rotated by a single drive comprising a single rod 39. The activation of the single drive cylinder causes the rotation of the drive. control ring 31 1 by the kinematics d written with reference to FIGS 1 0a to 1 0c, causing con cert the movement of all the driving rods 21. In this case, the control ring 31 1 comprises a single lever assembly 41 and a plurality of lever assemblies 69 distributed on the periphery of the crown and each relié on the one hand to a flap drive rod and on the other hand to a plate 70 shaped to support the lever assembly 69.

Referring to Figures 1-24, illustrating a second alternative embodiment of the lever assembly.

According to this variant, the control ring 31 1 is connected to a lever assembly 71 having a substantially "T" shape.

The lever assembly 71 is identical to the assembly forming the "L" sink 41, except that the oblong holes 47 and 57 receiving respectively the rod 39 of the drive cylinder and the drive rod 21 are on either side of the longitudinal axis 68 of the oblong hole 53 when said assembly is in a position corresponding to the neutral position of the connecting rod 21 training.

As previously described, the control crown 31 1 is mounted on a plurality of fixed rails 63 (a single rail being shown in FIG. 1 2) and integral with the nacelle, said rails 63 each having an opening 65 provided for the passage of said ring and terminating in a plate 66 shaped to support the lever assembly 71. There are as many rails as there are shutter drive rods 21.

According to this second variant, the movement kinematics of the driving bell 21 are reversed with respect to the first variant, as illustrated in FIGS. 13a to 13c.

Referring to these figures, the control ring 31 1 is rotated under the action of the rod 39 of the longitudinal cylinder. A rotation of the control ring 31 1 in the clockwise direction causes a displacement of the driving rod 21 in an advanced position, and a rotation of said crown in the counterclockwise direction causes a displacement of said rod in a retracted position. .

In addition, as for the first variant of this third embodiment, the control ring 31 1 can be rotated by the activation of a plurality of drive cylinders whose end of each rod is secured to a lever assembly.

Alternatively, and as shown in Figure 14, the control ring 31 1 is rotated by a single drive cylinder comprising a single rod 39, causing the movement of all the drive rods 21 together. In this case, the control ring 31 1 comprises a single lever assembly 71 "T" and a plurality of lever assemblies 73 distributed on the periphery of said ring. Each of said lever assemblies 73 is connected, as previously described with reference to the lever assembly 69, to a single rod. flight train and on the other hand to a plate 75 shaped to support said lever assembly 73.

Referring now to FIG. 15 illustrating an alternative embodiment of the lever assembly 71. According to this variant, the oblong holes 47 and 57 are replaced by circular holes 77, 79 and the mechanical links between the rod 39 of the drive cylinder and the assembly 71, and the driving rod 21 and the assembly 71 can be modeled by a pivot connection of vertical axis.

In addition, this variant applies to the oblong holes of the lever assembly 41, and also to each of the lever assemblies that comprises the control ring 31 1.

Referring to Figure 16, schematically illustrating a non-limiting example of the connection between the drive rod 21 and the flap 7 adaptive nozzle.

The translation of the rod during the rotation of the control ring has the effect of creating a moment allowing the pivoting of the flap 7 about its axis of rotation 81.

The axis of rotation of the flap may alternatively be positioned upstream or downstream of the position shown in FIG.

According to a variant, the flap 7 can be connected to the crown by means of two connecting rods placed on either side of said flap.

In addition, if the skilled person finds a particular interest, a plurality of connecting rods can connect the control ring to each component.

Thanks to the present invention, the rotation of a single peripheral ring allows simultaneous control and synchronization of a plurality of flap drive rods.

According to the first embodiment, the flap drive device is particularly suitable for reduced torque master nacelles, for which the space requirement must be reduced.

The flap drive device made according to the second and third embodiments is more particularly intended to be integrated into nacelles larger size, because of the presence of cylinders for driving in rotation of the control ring.

In addition, the second and third embodiments advantageously make it possible to substantially reduce the forces exerted on the rod of the drive cylinder and on the drive rod of the flaps.

Furthermore, it should be understood that the drive device according to the invention is preferably applied to adaptive nozzle flaps, but it is of course not excluded to adapt this device for training any other rotatable movable part of the nacelle, such as thrust reverser flaps, door thrust reverser doors, etc.

In addition, the description has been made with reference to a control ring of substantially annular shape, extending substantially over the entire circumference of the nacelle. Of course, an alternative to this design choice is not excluded. In particular, the control ring can quite include a plurality of independent sections, each being rotated by at least one previously described drive means.

Finally, as goes without saying, the invention is not limited to the embodiments of this flap drive device, described above only as illustrative examples, but it embraces all variants.

For this purpose, it is important to note that the drive device according to the invention is not limited to the description which has been made and to the figures which refer to it.

In particular, and as an example, there is shown in Figures 9 to 1 1 a lever assembly 41, called "L", mounted downstream of the ring. It is quite possible to position this lever assembly not downstream of the ring but upstream, substantially symmetrically to the plane formed by the transverse and vertical axes. It is also possible to position the lever assembly 41 symmetrically with respect to the longitudinal axis 68 passing through the oblong hole 53 of the control ring.

In these cases, during a displacement of the connecting rod 39 of cylinder from upstream to downstream of the nacelle, the movement of the driving rod 21 is reversed compared to what has been described. This arrangement also applies to the lever assembly 71 called "T" shown in Figures 12 to 15.

Finally, the guiding light 29, provided on the control rings 1 1 1 and 21 1, is oblique, and extends, as shown in FIGS. 4a, 4b, 4c and 6 to 8, from the upstream to the downstream of the nacelle when looking at the outer face of the crown. Of course, according to another design choice, it is quite possible to extend the guide light from downstream to the upstream of the nacelle when looking at the outer face of the crown. The direction of rotation is then reversed, and a clockwise rotation of the crown causes a displacement of the drive rod to a retracted position.

Claims

1. Shutter drive device, in particular for an aircraft turbojet engine adaptive nacelle nozzle, said nozzle comprising at least one rotatable flap (7) adapted to pivot at least towards a position causing a variation of the section of the nozzle, said nozzle device comprising at least one control ring (31 1) movable in rotation along the circumference of said nacelle during the activation of drive means (39, 41, 71) of the control ring, said device a drive comprising at least one flap-drive connecting rod (21) connected, directly or indirectly, to the control collar and, on the other hand, directly or indirectly, to at least one shutter, the activation of said driving means of the control ring (31 1) causing a displacement in translation of said rods (21), said device being characterized in that the driving means of the control ring of (31 1) comprise at least one longitudinal drive cylinder comprising at least one rod (39) connected to at least one lever assembly (41, 71), said at least one lever assembly (41, 71) being integral directly or indirectly from said crown.

Flap drive device according to claim 1, characterized in that the lever assembly (41, 71) is connected to the control ring via at least one carriage (33) configured to translating in an oblong hole of said control ring (31 1).

Flap drive device according to one of claims 1 or 2, characterized in that at least one flap drive rod (21) is connected to at least one of said lever assemblies ( 41, 71).

4. flap drive device according to any one of claims 1 to 3, characterized in that at least one of said lever assemblies (41) is an assembly L.

A flap drive according to one of claims 1 to 3, characterized in that at least one of said lever assemblies (71) is a T-assembly.

Flap drive according to one of Claims 1 to 5, characterized in that said connection between said longitudinal drive cylinder rod (39) and said lever assembly (41, 71) is a connection slide.

Flap drive according to one of claims 1 to 5, characterized in that said connection between said longitudinal drive cylinder rod (39) and said lever assembly (41, 71) is a connection vertical axis pivot (V).

8. flap drive device according to any one of claims 1 to 7, characterized in that said connection between said drive rod (21) flap and said lever assembly (41, 71) is a slide connection .

9. flap drive device according to any one of claims 1 to 7, characterized in that said connection between said drive rod (21) flap and said lever assembly (41, 71) is a pivotal connection vertical axis (V).

Flap drive device according to one of claims 1 to 5, or 8, characterized in that the longitudinal drive cylinder rod (37) is connected to the lever assembly (41, 71). via at least one carriage (33).

11. Shutter drive device according to any one of claims 1 to 6, or 8 to 10, characterized in that the shutter drive rod (21) is connected to the lever assembly (41, 71). ) via at least one carriage (33).

12. Device for driving flaps according to any one of claims 1 to 11, characterized in that the control ring (111, 211, 311) extends substantially over the entire circumference of the nacelle.

13. Flap drive device according to any one of claims 1 to 11, characterized in that the control ring (111, 211, 311) comprises a plurality of independent sections movable in rotation along the circumference of said nacelle during activation of the drive means (13, 19, 37, 39, 41, 71).

14. Thrust reverser for an aircraft turbojet engine nacelle comprising at least one downstream hood comprising in its downstream portion at least one adaptive nozzle comprising at least one flap (7) movable alternately at least between a retracted position and an extended position, characterized in that said cover comprises at least one flap drive device of said nozzle according to any one of claims 1 to 13.

Aircraft turbojet engine nacelle comprising at least one thrust reverser according to claim 14.