CN217864701U - Control surface and aircraft - Google Patents

Abstract

The utility model relates to a control rudder face, this control rudder face includes: a fixing surface fixed to a wing portion of an aircraft; a telescoping control surface attached to the stationary surface and pivotable about a pivot axis; a first actuator having a first end pivotally secured to the stationary surface and a second end pivotally secured to the telescoping control surface, actuation of the first actuator causing the telescoping control surface to pivot about a pivot axis; wherein the telescopic rudder surface comprises a fixed part, a movable part and a second actuator attached between the fixed part and the movable part, the actuation of the second actuator changing the position of the movable part relative to the fixed part. The control surface is a control surface which can be stretched along with the movement of the stretching control surface, and can be stretched in the chord length direction of the control surface, so that the aim of increasing the chord length of the control surface along with the increase of the deflection angle of the control surface is fulfilled. Additionally, the utility model discloses still relate to an aircraft.

Description

Control surface and aircraft

Technical Field

The utility model relates to a control rudder face can be applied to control rudder faces such as the elevator and the rudder of aircraft, belongs to increase control rudder face deflection efficiency, improve the change linearity of rudder effect along with deflection angle and can reduce the device of aircraft resistance. Additionally, the utility model discloses still relate to an aircraft.

Background

During the deflection of the control surfaces, such as elevators and rudders of aircraft such as commercial passenger aircraft, the rear section of the control surface may project an additional area during the increase of the control surface with the angle of deflection and be able to fully retract the area increasing with the deflection after the control surface has returned to a neutral position.

In order to improve the rudder effect of the rudder, increasing the area and the tail force arm is an effective means, but the following technical difficulties exist:

(1) For the way to increase rudder effect by increasing area: if the area of the control surfaces is directly increased, this would mean a greater cruising resistance, which reduces the economy and competitiveness of an aircraft, for example a large passenger aircraft.

(2) For the mode of increasing the tail force arm to improve the rudder effect of the rudder: the efficiency of improving the rudder effect is lower, and can change aircraft overall design by a wide margin, have the potential risk of taking place unknown problem.

Therefore, it is very important to design a form of control surface that does not increase the cruise resistance while effectively increasing the steering effect.

In an invention patent entitled "an elevator" and publication number CN107512384, which is filed by seian airplane design research institute of china airline industry group company on 8.1.2017, the invention discloses an elevator, wherein the elevator deflects to realize longitudinal trim and operation of an airplane, thereby avoiding a series of problems of structural arrangement, weight, fatigue load, reliability and the like caused by the arrangement of a horizontal tail installation angle adjusting mechanism. However, the elevator cannot increase the control surface area when deflecting.

In an invention patent entitled "lifting surface" and publication number CN108327895, which is filed by airbus operation limited liability company in 2018, 1, and 15, a lifting surface with vortex generators is provided, wherein the vortex generators are contracted by deflecting elevators through movable discontinuous parts, so that the effects of delaying airflow separation and stalling and improving the effectiveness of the lifting force/control surface are achieved. However, the invention mainly has the effect of increasing the rudder effect by slotting the stabilizing surface and contracting the vortex generators, and cannot increase the lifting rudder area.

There is therefore a significant need for a control surface that alleviates or overcomes one or more of the disadvantages of the prior art control surfaces.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing a control rudder face, the motion of mechanism when this control rudder face relies on the rudder face to deflect makes the actuator actuate to the deflection of accompanying control rudder face realizes the increase of rudder face area, thereby realizes the purpose of promotion control rudder effect. In addition, the linearity of the aircraft control effect changing along with the deflection of the control surface can be adjusted by adjusting the proportional relation between the deflection angle of the control surface and the extension amount of the control surface.

According to an aspect of the utility model, a control rudder face is provided, this control rudder face can include:

a fixing surface fixed to a wing portion of an aircraft;

a telescoping control surface attached to the stationary surface and pivotable about a pivot axis;

a first actuator having a first end pivotally secured to the stationary surface and a second end pivotally secured to the telescoping control surface, actuation of the first actuator causing the telescoping control surface to pivot about a pivot axis;

wherein the telescopic rudder surface may comprise a fixed part, a movable part and a second actuator attached between the fixed part and the movable part, actuation (e.g. extension or retraction, etc.) of the second actuator being capable of changing the position of the movable part relative to the fixed part.

The control surface is a control surface which can stretch along with the movement of the telescopic control surface. During the pivoting of the telescopic control surface and the movement of the movable part relative to the fixed part (such as during the deflection), the telescopic control surface can extend in the chord length direction of the control surface, so that the aim of increasing the chord length of the control surface along with the increase of the deflection angle of the control surface is fulfilled.

According to the above aspect of the present invention, preferably, the fixed part may include a guide groove, and the movable part may have a guide portion, and a shape of the guide portion may match a shape of the guide groove to be accommodated in the guide groove.

In this way, after the control surfaces are controlled to return to the neutral position (initially not extended), the area that increases with deflection can be fully retracted, thereby allowing the control surface area to be reduced when not needed, to reduce drag on the aircraft, and to improve fuel economy.

According to the above aspect of the present invention, preferably, the second actuator may be a linear actuator, and the extension of the second actuator may move the movable portion away from the fixed portion. By moving the movable portion away from the fixed portion, the area of the telescopic control surface can be increased conveniently and reliably.

According to the above aspect of the present invention, preferably, the second actuator may further include a return spring that is attached between the fixed portion and the movable portion and applies a pre-tightening force toward each other between the fixed portion and the movable portion.

Thus, when the control surface is in the neutral position, the telescopic part (telescopic control surface) of the control surface is in a folding state under the action of the pretension force of the spring, and the movable part can be prevented from being extended accidentally, so that the safety of the control surface is ensured, and the area of the telescopic control surface is reduced.

According to the above aspect of the present invention, preferably, the control surface may further comprise a linkage mechanism pivotally connected between the fixed surface and the fixed portion of the telescopic control surface for cooperating with actuation of the second actuator to support/assist pivoting of the telescopic control surface about the pivot axis. In this way, the linkage can follow the passive movement of the second actuator and assist the second actuator in supporting the telescoping control surface, thereby ensuring control surface stability in flight.

According to the above aspect of the present invention, preferably, the link mechanism may include a first link and a second link hinged together, wherein an end of the first link remote from the second link is hinged to the fixed portion of the telescopic rudder surface, and an end of the second link remote from the first link is fixedly connected to the fixed surface. In this way, the design of the link mechanism is simplified and reliability is improved.

According to the above aspect of the present invention, preferably, the pivot axis may be positioned at a middle position of the fixed portion, and the second end of the first actuator is pivotally fixed to the telescopic control surface above the pivot axis, so that the extension of the first actuator causes the free end of the telescopic control surface to deflect downwards. This arrangement may provide a compromise between increasing the degree of yaw and maintaining the stability of the telescopic control surface.

According to the above aspect of the present invention, preferably, the control surface may further comprise a third actuator arranged symmetrically to the first actuator about the pivot axis, wherein a first end of the third actuator is pivotally fixed to the fixed surface and a second end of the third actuator is pivotally fixed to the telescopic control surface below the pivot axis.

The third actuator can actively act to cooperate with the first actuator to control the deflection of the telescopic rudder surface, for example, when the first actuator pushes the telescopic rudder surface, the third actuator can pull the telescopic rudder surface, so that more stable and larger actuating force can be provided to control the deflection of the telescopic rudder surface and more stably maintain the telescopic rudder surface at the deflected position.

The control surface may further include a signal transfer device communicating the first actuator and the second actuator for transferring signals between the first actuator and the second actuator. The signal transmission device can coordinate the actuation of the first actuator and the second actuator, so that the movable part of the telescopic control surface moves away from the fixed part after the fixed part is deflected, and the expected increase of the area of the control surface and the deflection of the control surface are realized, namely, the control surface which can be stretched along with the movement is realized.

According to another aspect of the present invention, an aircraft is provided, wherein the aircraft may comprise a control surface according to the above aspect.

It can thus be seen that: under the condition of the same control surface neutral position area, the control surface of the utility model has higher control surface efficiency; through the corresponding relation between the increased control surface area and the deflection angle of the control surface, the control surface of the utility model can adjust the corresponding relation between the control effect and the deflection of the control surface, and can improve the linearity of the deflection of the control effect along with the control surface; in addition, with the same rudder effect, the control rudder surface according to the invention has a smaller neutral position area and a lower aircraft cruising resistance. Because every reducing 1 count's resistance of large-scale passenger plane, can carry about 2500 ~ 3700 people respectively more/frame/year, the fuel income is about 50 ~ 260 ten thousand yuan/frame/year respectively, consequently, according to the utility model discloses a control surface has higher economic benefits.

From this, through the utility model discloses a control surface can satisfy the operation requirement, has realized predetermined purpose.

Drawings

For a further clear description of the control surface according to the invention, the invention will be explained in detail below with reference to the drawings and a specific embodiment, in which:

FIG. 1 is a schematic illustration of a control surface in an undeflected state in accordance with a first non-limiting embodiment of the present invention;

FIG. 2 is a schematic illustration of a control surface in a post-deflection state in accordance with a first non-limiting embodiment of the present invention;

FIG. 3 is a comparison of the state of the control surfaces shown in FIGS. 1 and 2;

FIG. 4 is a schematic illustration of a control surface in an undeflected state in accordance with a second non-limiting embodiment of the present invention;

FIG. 5 is a comparison of an undeflected state and a deflected state of a control surface according to a second non-limiting embodiment of the present invention;

FIG. 6 is a schematic view of a control surface in an undeflected state in accordance with a third non-limiting embodiment of the present invention;

FIG. 7 is a schematic view of a control surface in an undeflected state in accordance with a fourth non-limiting embodiment of the present invention;

FIG. 8 is a schematic illustration of a control surface in a post-deflection state in accordance with a fourth non-limiting embodiment of the present invention; and

fig. 9 is a comparison of the states of the control surfaces shown in fig. 7 and 8.

The figures are purely diagrammatic and not drawn true to scale.

List of reference numbers in the figures and embodiments:

100-control surface comprising:

10-a fixed surface;

20-telescoping rudder surface comprising:

21-a stationary part comprising:

21A-a guide groove;

22-an active part comprising:

22A-a guide;

22B-free end;

23-a second actuator;

30-a first actuator comprising:

31-a first end;

32-a second end;

40-a linkage mechanism comprising:

41-a first link;

42-a second link;

50-a third actuator comprising:

51-a first end;

52-second end;

60-a signal transmission device;

a-the pivot axis.

Detailed Description

It is to be understood that the invention may assume various alternative orientations and step sequences, except where expressly specified to the contrary. It is also to be understood that the specific devices illustrated in the attached drawings, and described in the specification are simply exemplary embodiments of the inventive concepts disclosed and defined herein. Thus, specific orientations, directions or other physical characteristics relating to the various embodiments disclosed should not be considered limiting unless expressly stated otherwise.

The elevator is the steerable part of the horizontal tail of the aircraft and mainly functions to control the pitching motion of the aircraft, and the strength of the pitching motion is determined by the distance between the center of gravity and the horizontal tail surface (the size of the moment arm) and the aerodynamic effectiveness on the horizontal tail surface. A rudder is a movable airfoil portion on a vertical tail for effecting directional control of an aircraft. Typically hinged to the rear of the vertical stabilizer. The pilot can control the aircraft course by controlling the left and right deflection of the pilot through the pedals. The utility model discloses in the control surface of mentioning can be the control surface of being applied to the elevator, also can be the control surface of being applied to the rudder.

The control surface 100 according to a non-limiting embodiment of the present invention will be described in detail with reference to the accompanying drawings.

Fig. 1 is a schematic illustration of a control surface 100 in an undeflected state in accordance with a first non-limiting embodiment of the present invention.

As shown and by way of non-limiting example, the control surface 100 of this first embodiment may include: a fixed surface 10, a telescopic rudder surface 20 and a first actuator 30.

The fixing surface 10 may be fixed to or be part of a wing of an aircraft. As used herein, the term "wing" may refer to, for example, a wing, a tail (including horizontal tails, vertical tails, etc.), or similar structure of an aircraft. For example, the fixed surface 10 may be fixed to or be part of, i.e., integral with, a horizontal tail or a vertical tail. The fixed surface 10 is mainly used for carrying the telescopic rudder surface 20 and for mounting a corresponding actuating device.

The telescopic control surface 20 may be attached to the stationary surface 10, e.g. the telescopic control surface 20 may be hinged to the stationary surface 10 by means of a pivot axis and may be pivotable about a pivot axis a. The pivot axis may for example be fixedly connected at both ends to the stationary surface 10 and in the middle pivotally connected to the telescopic rudder surface 20 via a sleeve or the like. The pivot axis a may be the central axis of the pivot shaft. For example, the telescopic rudder surface 20 can be pivoted about a pivot axis a by actuation of the first actuator 30.

In an alternative embodiment, there may be no pivot axis, for example, the telescopic control surface 20 is hinged to the fixing surface 10 at both ends in the forward and backward direction perpendicular to the up and down direction in the drawing. At this time, the pivot axis a may be an axis connecting between the centers of the two hinges.

As shown, the telescopic rudder surface 20 may include a fixed portion 21, a movable portion 22, and a second actuator 23.

The fixing portion 21 may include a guide groove 21A, and the guide groove 21A may be provided at a middle portion of the fixing portion 21 and open in a direction opposite to the fixing face 10, and the opening may be in the form of a rectangular opening.

The movable portion 22 may have a guide portion 22A and a free end 22B. The shape of the guide portion 22A matches the shape of the guide groove 21A to be accommodated in the guide groove 21A, for example, having a substantially rectangular cross section as shown in the drawings. The free end 22B is also the endmost of the telescopic rudder surface 20 and may have a generally triangular cross-section. Of course the telescopic rudder surface 20 can also have a substantially curved profile.

A second actuator 23 is attached between the fixed part 21 and the movable part 22, for example, the two ends of the second actuator 23 are fixedly connected to the fixed part 21 and the movable part 22, respectively, so that actuation of the second actuator 23 changes the position of the movable part 22 relative to the fixed part 21.

By way of non-limiting example, the second actuator 23 may be a linear actuator, such as a pneumatic cylinder, a linear motor, or the like, and extension of the second actuator 23 moves the movable portion 22 away from the fixed portion 21, while retraction of the second actuator 23 moves the movable portion 22 toward the fixed portion 21.

In addition, the second actuator 23 may preferably further include a return spring that is attached between the fixed portion 21 and the movable portion 22 and applies a biasing force between the fixed portion 21 and the movable portion 22 toward each other.

The return spring may be any type of linear spring or torsion spring or the like known in the art as long as it applies a pre-load between the fixed part 21 and the movable part 22, and therefore, for the sake of brevity, the present invention will not be described in detail herein.

As shown in fig. 1, a first end 31 of the first actuator 30 may be pivotally secured to the fixed surface 10 and a second end 32 of the first actuator may be pivotally secured to the telescopic rudder surface 20 to accommodate changes in the angle of connection therebetween during actuation.

As used herein, the description "pivotally secured" may include, for example, hinged, pivotally connected, and the like connections. For example, in order to pivotally secure the first end 31 of the first actuator 30 to the fixed surface 10, the first end 31 may be pivotally connected to a portion of the fixed surface 10 such that the angle between the first actuator 30 and the fixed surface 10 may be varied about the pivot.

Fig. 2 is a schematic diagram of a control surface 100 in a post-deflection state according to a first non-limiting embodiment of the present invention.

As shown in fig. 2, the first actuator 30 has been extended such that the telescopic rudder surface 20 is pivoted about the pivot axis a, i.e. rotated counter-clockwise. At this time, the free end 22B of the movable portion 22 is deflected downward. At the same time, the second actuator 23 is extended, so that the guide portion 22A moves along the guide groove 21A, and the movable portion 22 moves away from the fixed portion 21, i.e., remains in the position shown in fig. 2.

At this time, the extension of the telescopic control surface 20 along the chord length direction of the control surface 100 achieves the purpose that the chord length of the control surface 100 increases along with the increase of the deflection angle of the control surface, thereby increasing the area of the control surface 100 and further improving the control effect of the control surface 100.

Fig. 3 is a comparison of the states of the control surface 100 shown in fig. 1 and 2. As shown, the telescopic control surface 20 deflects downwards and elongates and the control surface 100 area increases, i.e. the area of the deflected and elongated telescopic control surface 20 shown by the dotted line is larger than the area of the non-deflected and retracted telescopic control surface 20 in neutral (initial position) shown by the solid line.

FIG. 4 is a schematic illustration of a control surface 100 in an undeflected state in accordance with a second non-limiting embodiment of the present invention; fig. 5 is a comparison of an undeflected state and a deflected state of the control surface 100 according to a second non-limiting embodiment of the present invention.

The control rudder surface 100 of this embodiment differs from the first embodiment shown in fig. 1-3 in that in the embodiment shown in fig. 4 and 5 the control rudder surface 100 further comprises a linkage 40, the linkage 40 being pivotally connected between the fixed surface 10 and the fixed part 21 of the telescopic rudder surface 20 for cooperating with the actuation of the second actuator 23 for supporting the telescopic rudder surface 20 to pivot about the pivot axis a.

Preferably, the linkage 40 comprises a first link 41 and a second link 42 hinged together, wherein an end of the first link 41 remote from the second link 42 is hinged to the fixed portion 21 of the telescopic rudder surface 20, and an end of the second link 42 remote from the first link 41 is fixedly connected to the fixed surface 10.

In this way, the fixed portion 21 of the telescopic control surface 20 can pivot about the pivot axis upon actuation (e.g. extension or retraction) of the first actuator 30. At this time, the angle between the first link 41 and the second link 42 is changed accordingly to passively follow the deflecting movement of the fixed portion 21, thereby providing an auxiliary support to the fixed portion 21.

As shown and by way of non-limiting example, the pivot axis a may be positioned at a mid-position of the fixed portion 21, such as a mid-position that is symmetrical about the up-down direction, and the second end 32 of the first actuator 30 is pivotally secured to the telescoping control surface 20 above the pivot axis a such that extension of the first actuator 30 causes the free end 22B of the telescoping control surface 20 to deflect downwardly.

Fig. 6 is a schematic view of a control surface 100 in an undeflected state in accordance with a third non-limiting embodiment of the present invention.

The control surface 100 of this embodiment differs from the first embodiment shown in fig. 1-3 in that in the embodiment shown in fig. 6 the control surface 100 further comprises a third actuator 50, the third actuator 50 being arranged symmetrically to the first actuator 30 about the pivot axis a, wherein a first end 51 of the third actuator 50 is pivotally fixed to the fixed surface 10 and a second end 52 of the third actuator 50 is pivotally fixed to the telescopic control surface 20 below the pivot axis a.

It should be understood that although in the embodiment shown in the drawings the first actuator 30 and the third actuator 50 are pivotally fixed to the telescopic rudder surface 20 above and below the pivot axis a, respectively, a person skilled in the art may envisage other arrangements, such as an inverted arrangement, a parallel arrangement, etc.

FIG. 7 is a schematic illustration of a control surface 100 in an undeflected state in accordance with a fourth non-limiting embodiment of the present invention; FIG. 8 is a schematic illustration of a control surface 100 in a post-deflection state in accordance with a fourth non-limiting embodiment of the present invention; and fig. 9 is a comparison of the states of the control surface 100 shown in fig. 7 and 8.

The control rudder surface 100 of this embodiment differs from the second embodiment shown in figures 4 to 5 in that in the embodiment shown in figures 7 to 9 the control rudder surface 100 further comprises a signal transfer device 60 communicating the first actuator 30 and the second actuator 23 for transferring signals between the first actuator 30 and the second actuator 23.

The signal transmission means 60 is shown in the drawings as a wired connection, but may alternatively be a wireless connection, and may include a controller or the like, not shown, to coordinate the operation of the various actuators.

Additionally, in embodiments where the control surface 100 includes a third actuator 50 (e.g., the embodiment illustrated with reference to FIG. 6), the signal transmission device 60 may also be connected to the third actuator 50. The signal transmission 60 can be used to ensure that the movable part 22 of the telescopic rudder surface 20 moves away from the fixed part 21 following the yawing movement of the telescopic rudder surface 20 when the telescopic rudder surface 20 is yawing, thereby forming a control rudder surface 20 which can be telescoped with the movement.

At this time, the telescopic control surface 20 extends in the chord length direction of the control surface 100 along with the deflection of the fixing part 21, so that the purpose of increasing the chord length of the control surface 100 along with the increase of the deflection angle of the control surface is achieved, thereby increasing the area of the control surface 100 and further improving the control effect of the control surface 100.

In conclusion, according to the utility model discloses a control surface 100 can increase the control effect through the area that increases control surface, improves the linearity of control surface efficiency through the design of rudder deflection angle and control surface amount of protrusion proportional relation to through reducing control surface neutral position area, realize the target of aircraft drag reduction.

The terms "above," "below," "up-down," "front-to-back," and the like as used herein to denote orientation or direction, and the terms "first," "second," and the like are used merely to enable those of ordinary skill in the art to better understand the concepts of the invention as embodied in the preferred embodiments, and not to limit the invention. Unless otherwise specified, all sequences, orientations, or orientations are used for the purpose of distinguishing one element/component/structure from another element/component/structure only, and do not imply any particular order, sequence of operations, direction, or orientation, unless otherwise specified. For example, in an alternative embodiment, "first actuator" may alternatively be referred to as "third actuator".

In summary, the control surface 100 according to the embodiment of the present invention overcomes the disadvantages of the prior art, and achieves the intended utility model purpose.

While the control surface of the present invention has been described in connection with the preferred embodiment, it will be understood by those skilled in the art that the above examples are intended to be illustrative only and not as limiting. Therefore, various modifications and changes can be made to the present invention within the spirit and scope of the claims, and these modifications and changes will fall within the scope of the claims of the present invention.

Claims (10)

1. A control surface (100), characterized in that the control surface (100) comprises:

a fixing surface (10) fixed to a wing of an aircraft;

a telescopic rudder surface (20) attached to the stationary surface (10) and pivotable about a pivot axis (A);

a first actuator (30) having a first end (31) pivotally secured to the fixed surface (10) and a second end (32) pivotally secured to the telescopic control surface (20), actuation of the first actuator (30) causing the telescopic control surface (20) to pivot about the pivot axis (A);

wherein the telescopic control surface (20) comprises a fixed part (21), a movable part (22) and a second actuator (23) attached between the fixed part (21) and the movable part (22), actuation of the second actuator (23) changing the position of the movable part (22) relative to the fixed part (21).

2. Control surface (100) according to claim 1, characterized in that the fixed part (21) comprises a guide groove (21A) and the movable part (22) has a guide (22A), the shape of the guide (22A) matching the shape of the guide groove (21A) for accommodation in the guide groove (21A).

3. Control surface (100) according to claim 2, characterized in that the second actuator (23) is a linear actuator and that elongation of the second actuator (23) moves the movable part (22) away from the fixed part (21).

4. Control surface (100) according to claim 3, characterized in that the second actuator (23) further comprises a return spring which is attached between the fixed part (21) and the movable part (22) and which exerts a pretension force between the fixed part (21) and the movable part (22) towards each other.

5. Control surface (100) according to claim 1, characterized in that the control surface (100) further comprises a linkage mechanism (40), the linkage mechanism (40) being pivotally connected between the fixed surface (10) and the fixed part (21) of the telescopic control surface (20) for cooperating with the actuation of the second actuator (23) for supporting the telescopic control surface (20) to pivot about the pivot axis (a).

6. Control surface (100) according to claim 5, characterized in that the linkage (40) comprises a first link (41) and a second link (42) hinged together, wherein the end of the first link (41) remote from the second link (42) is hinged to the fixed part (21) of the telescopic control surface (20), while the end of the second link (42) remote from the first link (41) is fixedly connected to the fixed surface (10).

7. Control surface (100) according to claim 1, characterized in that the pivot axis (a) is positioned in a middle position of the fixed part (21) and the second end (32) of the first actuator (30) is pivotally fixed to the telescopic control surface (20) above the pivot axis (a) so that elongation of the first actuator (30) causes a downward deflection of the free end (22B) of the telescopic control surface (20).

8. Control surface (100) according to claim 7, characterized in that the control surface (100) further comprises a third actuator (50), the third actuator (50) being arranged symmetrically to the first actuator (30) with respect to the pivot axis (A), wherein a first end (51) of the third actuator (50) is pivotally fixed to the fixed surface (10) and a second end (52) of the third actuator (50) is pivotally fixed to the fixed part (21) of the telescopic control surface (20) below the pivot axis (A).

9. Control surface (100) according to any of claims 1-8, characterized in that the control surface (100) further comprises a signal transmission device (60) communicating the first actuator (30) and the second actuator (23) for transmitting signals between the first actuator (30) and the second actuator (23).

10. An aircraft, characterized in that it comprises a control surface (100) according to any one of claims 1-9.

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