Rotary element to increase lift, particularly, deflecting wing tip with high aerodynamic characteristic

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Wing deflecting tip features profile of aircraft wing. Wing 10 comprises torsion 10a has first side with first skin 11 and second, opposite, side with second skin, and torsion box edge facing deflecting tip 20 with front skin that is a continuation of first skin 11. Wing deflecting tip 20 comprises main case 21 that allows transition from first side to second side, and first transition part 20a facing the first side, and second transition part 20b that faces second side. Said wing deflecting tip 20 can be set by retention mechanism 23 and drive that coupled said tip with torsion box 10a between first, IN, position and second, OUT, position. First transition parts 20a of the tip can slide on over wing front surface. Wing deflecting tip can be mounted between first and second positions at preset angle to wing torsion box 10a, and wing profile may be widened around imaginary rotational axis 30.

EFFECT: improved aerodynamic properties.

27 cl, 12 dwg

The technical FIELD

The invention relates to rotary elements to increase the lifting force, in particular to say no to socks, for wings with high aerodynamic quality.

The LEVEL of TECHNOLOGY

In the technique known numerous devices designed to enhance the performance of the lifting force of the wings with a high glide ratio, which is used to increase the curvature and/or length of the wing profile in the direction of the width of the wing, which results in increasing its lifting force.

Such components are intended to increase the lifting force and mounted on the front edge of the wing relative to the air flow, fundamentally divided into two groups: say no to socks wings, which are almost without a gap adjacent to the leading edge of the wing profile, and say no to the slats, which between them and the front edge of the wing has a slot through which air flow from the lower surface of the slat is fed to the upper surface of the wing.

Say no to the slats preferable for the step landing, because in this case there is a delay separation of the boundary layer, however, due to the increase of drag they are not very suitable to perform takeoff, and as in this case, inevitably in senecaut vibrations and air turbulence, passing through the zone of the slit, then reject the slats are the source of excessive noise.

The known solution, which was used in the Airbus A380 represents a decline toe wing, which is almost without a gap to slide along the edge of the wing, and this sock has a rigid profile and can be rotated on the axis of rotation, mounted on the lower surface of the wing profile, to move from the retracted position into the extended position. In this design the upper rear edge of the toe wing is doing around the specified axis of rotation movement around the circumference along the skin of the wing leading edge, having a similar curvature, and therefore between the leading edge of the wing and say no to toe there is almost no gap.

In addition, there are various designs deny toe wing, which contain a flexible sheath having a variable curvature, the axis of rotation is also in the profile of the wing. Such decline of the wing are described, for example, in U.S. patents US 4475702, US 6015115, US 6796534, US 4200253, US 4553722 and in the European patent EP 0302143. The drawback of such decline socks wings with variable curvature is not only the complexity of their design, but also due to this complexity is the difficulty of keeping a given wing profile with the required accuracy. Other designs deviated nose is s wings with variable curvature is known from U.S. patent US 4650140 and US 4706913.

In U.S. patent US 5927656 describes deny toe wing with rigid profile that using a lever mechanism can be installed at a desired position relative to the front surface of the rotor wing, and between the toe and the front surface of the wing there is a crack through which air from the lower surface of the wing flows on its upper surface.

In the European patent EP 100775 describes deny toe wing axis of rotation, located on the bottom of the wing profile, and this decline toe wing equipped with a long flexible membranes that do not fit tightly to the underside of the wing.

Finally, U.S. patent US 544847 and US 5839699 describes a device increase the lifting force, which uses the slat put forward regarding the design of the wing on the guiding rail that curves around the circumference, and thus, the slat is rotated about an imaginary axis of rotation under the wing profile, i.e. on the side of high pressure. When the slat is extended between it and the wing design has a slit through which the air from the bottom side of the wing arrives at its upper side. On the back of the slat experiencing intense vortical zones, which are the cause of excessive noise and increased drag.

The ESSENCE of the IMAGE IS POSSIBLE

The aim of the invention is to provide a rotary element for increasing the lifting force, in particular the decline of the sock, for a wing with a high aerodynamic quality, which provides a sufficiently large increase in lifting force, and at the same time noise and drag increase slightly.

The purpose of the invention is achieved by the present invention, which proposes a rotary element for increasing the lifting force, in particular deny the toe, for a wing with a high aerodynamic quality, having a given profile, in particular for rotor wing aircraft. Wing contains the caisson, on the upper side of which has a first casing, a second, opposite side has a second skin, and its edge turned to say no to toe, is the front surface of the wing, which is at least partly a continuation of the first casing in the shape of a wing profile. Say no to toe wing contains a rigid main body, which provides a transition from the first side to the second side of the wing, and the first transition portion, which faces the first side wing, and a second transitional portion which faces the second side of the wing, and say no to toe wing can be installed using the mechanisms of the and retention and drive connecting deny toe wing caisson, between the first, retracted, position in which the toe wing covers a large portion of the front surface of the wing, and a second, extended, position in which the toe of the wing overlaps the lower portion of the front surface of the wing, and the first transition portion of the sock facing the first side wing can slide along the front surface of the wing so that in any position it is supported on the first casing and/or on the front surface of the wing, and does not have any cracks. The invention provides that deny toe wing can be installed between the first and second positions at a selected angle relative to the torsion box with a simultaneous extension of the profile of the wing about an imaginary axis of rotation that is located on the side opposite to the first casing, and is outside the profile of the wing, and the second transition portion deny toe wing, facing to the second side of the wing, at each position of the sock wings pressed tightly against the second casing, so that there was almost no cracks.

Proposed in the invention deny toe wing provides the ability to get the shape of the wing profile, which is generally smoother and more streamlined throughout the profile, resulting in reduce the peaks I strong rarefaction on the profile of the wing and prevents or delays the saturation profile. Profile shape, which is basically a smoothed on both sides of the wing, in comparison with the known decline socks provides drag reduction and noise reduction. In comparison with the known constructions deny socks wing is provided a noticeable increase in lifting force, which is due to the simultaneous increase of the curvature of the profile and its extension in the direction of the width of the wing in heavy traffic toe wing scheme Fowler. The exception occurrence of vortex zones on the lower surface of the wing increases the aerodynamic performance, this decreases the level of noise pollution, and reduced drag. At the stage of designing such interrelated characteristics as the deflection angle and the trajectory of the toe during its extension, which is used in the schema Fowler, can be selected within wide limits. The exclusion of any cracks on the top surface of the profile and areas of occurrence of vortices on the bottom surface deny the toe leads to lower noise and reduce drag.

In accordance with one variant of the invention, the position of the imaginary axis of rotation, around which way adjustable turns deny the toe of the wing is changed according to a given curve, depending on the provisions of the Oia say no to toe.

However, in accordance with the preferred embodiment of the invention the position of the imaginary axis of rotation, around which way adjustable turns deny toe wing, by changing the position of the sock is not changed.

In accordance with one embodiments of the invention, the retention mechanism and the actuator includes connecting elements in the form of guide rods connecting the torsion box with say no to toe wing, and the retention mechanism and the actuator can be operated from the steering actuator, which acts on these guide rods.

In a preferred embodiment of the invention, the retention mechanism and the actuator includes a guide rail that connects the torsion box with say no to toe wing and flowing generally in the direction of the width of the wing, and the retention mechanism and the actuator can be operated from the steering actuator, which acts on the guide rail.

In accordance with a preferred embodiment of the invention the guide rail has the shape of a circular arc, the center of which is on an imaginary axis of rotation, and the front surface of the wing, which is at least partly a continuation of the first casing in the shape of a wing profile, also has the shape of an arc of a circumference around woopra emeu axis, so the first transition portion deny toe wing can move circumferentially along a circular front surface of the wing when the regulated deviation toe wing.

In accordance with a preferred embodiment of the invention, the second transition portion deny toe wing, facing to the second side of the wing, is formed on the panel of the wing running casing, which is a continuation of the hard shell of the main body say no to toe wing and passes to the second skin of the wing, and the second transition portion is designed to slide relative to the second casing so that in any position of the sock wing transition to this covering almost had no cracks.

In this embodiment of the invention it is preferable that the area of the second casing along which can slide the second transition portion deny the toe of the wing when it is regulated deviation, were generally tangentially with respect to an imaginary axis of rotation.

In accordance with a preferred embodiment of the invention, the second transition zone is formed of a flexible part of the wing panel with working siding; which is a continuation of the rigid main body say no to toe wing.

In accordance with a preferred implementation of the Oia flexible portion of the wing panel with running casing, which is a continuation of the rigid main body say no to toe wing is formed at its end.

In accordance with a preferred embodiment of the invention the wing from working lining contains a first rigid part, which is a continuation of the rigid main body say no to toe wing, and the second flexible part, which is a continuation of the first part of the panel and which forms a second transitional portion.

Preferably the inner side of the first rigid part of the panel is provided with ribs which run essentially in the direction of the width of the wing.

Preferably the flexible part, which is provided with end panels of the wing running casing and which is a continuation of the rigid main body say no to toe wing, is in the form of a sealing edge, based on a second skin.

In accordance with a preferred embodiment of the invention, the retention mechanism and the drive contains the guide rails having the form of arcs of circles and spaced along the length of the wing along the imaginary axis of rotation, which are the centers of these circles rails.

In accordance with a preferred embodiment of the invention uses multiple guideways having the form of arcs of okruzhnosti and spaced along the length of the wing, and the radii of curvature of such rails are the same.

In accordance with another preferred embodiment of the invention uses multiple guideways having the form of arcs of circles and spaced along the length of the wing, and the radii of curvature of such rails are reduced in the direction of the length of the wing.

In accordance with one embodiments of the invention, the front surface of the wing, which is a continuation of the first casing, at least part of the profile shape of the wing has a constant radius of curvature along the length of the wing.

In accordance with a preferred embodiment of the invention the radius of the anterior surface of the wing, which is a continuation of the first casing, at least part of the profile shape of the wing decreases along the length of the wing.

Preferably, the radii of curvature of the guide rails and the front surface of the wing decreases in the direction of the length of the wing to the same extent.

In accordance with this embodiment of the invention the main body say no to toe wing tapering in the direction of the length of the wing to decrease the radius of curvature of the guide rails and/or the front surface of the wing.

In accordance with a preferred embodiment of the invention, the second casing provided with a recess or notch designed to I the present wing running casing, passing in the direction of the second casing, and this recess provides a generally smooth transition from the wing panel with a working lining deny toe wing to the second cladding torsion box at least in the retracted position the toe of the wing.

In this device, the depth of the recess is essentially corresponds to the thickness of the wing panel with working trim panel that goes in the direction of the second casing.

In accordance with a preferred embodiment of the invention the guide rail, which is part of the retention mechanism and the drive is a toothed rack, which can move the drive gear pinion control actuator, and a drive gear gear interacts with a toothed rack.

Preferably the guide rail is moved along the guide rollers.

In accordance with a preferred embodiment of the invention the torsion box features a locking device with which the wing from working paneling say no to toe wing, passing in the direction of the second cladding can be fixed relative to the torsion box in the retracted position the toe of the wing.

In particular, in this configuration, the locking device may be formed of the locking rollers for mode cruising flight.

Predpochtite the flax decline across the toe is installed sealing device, which provides aerodynamic seal deny the toe of the wing in relation to outer space.

The sealing device may consist of a transverse panels which can slide relative to each other.

In accordance with a preferred embodiment of the invention, the hard shell of the main body say no to toe wing and/or rigid part of the wing panel with working trim panel that goes in the direction of the second casing made of plastic reinforced with carbon fiber.

Further, in accordance with the preferred embodiment of the invention, the flexible portion of the wing panel with working trim panel that goes in the direction of the second cladding made of glass fiber reinforced plastics.

BRIEF DESCRIPTION of DRAWINGS

Option of carrying out the invention is described below with reference to the drawings.

In the drawings shown:

Figure 1 is a partial view of a section of the streamlined wing with say no to toe wing, which increases the lifting force, in accordance with the embodiment of the invention.

Figures 1A) and 1b) are enlarged views of parts of figure 1 (circled).

Figures 2A) and 2b) is a bottom view and a perspective view respectively of the streamlined wing with say no to toe, providing an increase in lifting the silts in accordance with the embodiment of the invention, the cross-section shown in figure 1, made according to line a-a of figure 2A.

Figure 3 is a perspective view deny the toe of the wing, which increases the lifting force, in accordance with the variant shown in figure 1, and the retention mechanism and drive the toe of the wing is shown only schematically.

Figure 4 is a perspective view deny the toe of the wing, which increases the lifting force, which is represented on figure 1, shown from a different angle (wings not shown).

Figures 5A)-5e - sectional views deny the toe of the wing, which increases the lifting force, which is represented in the figure 1, in the retracted position (figure 5A)and in various positions at the nomination of the sock of the wing (figure 5b)-5e)).

DETAILED description of the INVENTION

The figure 1 shows the cross section of the front part of the rotor wing aircraft, which is generally denoted by the reference number 10, and the wing is equipped with say no to toe, providing an increase in lifting force, which is denoted by reference number 20.

Wing 10 includes a casing 10A, the upper surface of which is provided with a first casing 11 and the lower surface provided with a second casing 12. In front of the torsion box of the casing 11, 12 are held at a given rasstojanija from each other by the spar 13. Further, in the direction to the rear surface deny the toe 20 of the wing first cladding 11 partially continues the front surface 14 of the wing.

Say no to the toe 20 of the wing contains the main body 21 with the casing 21A, which completes the front of the wing profile. The main body 21 and the shell 21A say no to socks have a rigid structure.

The lower part of the main body 21 for shell 21A in the direction of the second shell 12 of the casing 10A of the wing continues panel 22 of the wing with a working skin. This panel 22 are rigidly connected to the shell 21A of the main body 21, and its end facing the second casing 12 of the casing 10A of the wing, is arranged in such a manner that it can slide relative to the second shell 12. On the inner side panel 22 of the wing running casing has ribs 25 stiffness, which are approximately in the direction of the width of the wing and attach stability panel 22 to maintain its shape.

Rear deny the toe 20 of the wing is provided with a transverse panels 26, 27 (see figure 1), which can slide relative to each other, and these lateral panels 26, 27 provide aerodynamic seal deny the toe 20 of the wing with respect to the external space.

The lower end of the side member on the side facing the decline toe 20 of the wing may be provided with a strip 29 of rigidity, which, campocatino on an enlarged cross section of figure 1A), in the described embodiment, has a cross-section representing a quarter circle, and is used to counteract the cutting loads on the transition between the casing 10A of the wing and say no to the toe 20 of the wing.

The panel 22 of the wing running casing contains the hard part 22A which is attached to the main body 21 deny sock 20, and the stability of the rear panel 22 is provided above the ribs 25 of rigidity, and, in addition, the panel 22 includes an elastic portion 22b, which is where the panel 22 of the wing rests on the second casing 12 of the casing 10A of the wing.

As shown in figures 2A) and 2b), the rotary element 20 can be performed as say no to toe in the immediate vicinity of the root portion of the wing 10, or it may take place along the major sections in the direction of the length of the wing 10. Cross-section view of which is shown in figure 1, made according to line a-a of figure 2.

Figure 3 schematically shows the retention mechanism and the actuator, which is generally indicated by the reference number 23. This mechanism is designed to hold reject the toe 20 with the casing 10A of the wing and to ensure installation deny the toe 20 of the wing in the first, retracted, position and a second, extended, position, and, of course, to install in any position between the above two extreme positions.

This mechanism 23 by keeping the deposits and the actuator includes a guide rail 23a, passing along the arc of a circle, the center of which defines an imaginary axis 30 of rotation, around which turns deny sock 20 as it slides along the guide rail 23a when changing from one position to another.

As shown in figure 1, the front surface 14 of the wing, which is a continuation of the first cladding 11 is a curved surface with a constant radius of curvature (figure 1 radius indicated by the arrow), the centres of circles which are located on the axis 30 of rotation deny the toe 20 of the wing. This means that we reject the toe 20 with the first transition zone 20A, which is determined by the end of the decline of the sock 20 facing the first casing 11 (the upper end of the sock 20 in figure 1), with its adjustable movement in a working position and back always firmly pressed against the front surface 14 of the wing, i.e. the gap between them does not occur. The second transition zone 20b, which deny the toe 20 on the lower surface of the wing 10 is transferred in the profile shape of the second shell 12, is defined by the rear end panel 22 of the wing running casing, that is, at the end of the second, flexible portion 22b.

On the side that faces the imaginary axis 30 of rotation, i.e. on the lower surface of the guide rail 23a in figure 3, the guide rail 23a contains teeth that inter is actuat drive gear gear 23C of the drive rotation (figure not shown). Thus, the guide rail 23a generates the rack, which interacts with the drive gear gear 23C, so say no to the toe 20 of the wing can be mounted in the desired position by means of actuator rotation, which rotates the toothed gear 23C. In the described embodiment of the invention, in which the purpose of clarity the whole structure is shown schematically, the guide rail is rigidly attached to the casing 10A of the wing, while the toothed drive pinion 23C and its drive (not shown) placed in the internal space say no to the toe 20 of the wing, and can be moved together with him. Of course, it is possible to use a construction in which the guide rail 23a is rigidly connected to deny the toe 20 of the wing and moves with it, and a toothed drive pinion 23C and its actuator are accommodated in the casing 10A of the wing.

Say no to the toe 20 of the wing is designed so that it is rigidly connected with the guide rail 23a and through the mechanism 23 of the holding and drive can move relative to the casing 10A of the wing. Proper operation of the mechanism 23 of the holding and the actuator is provided with guide rollers 23b, toothed gears 23C and the rotation drive (not shown), which in this embodiment of the invention shown in figure 3, is placed in front of longera the th 13 and thus, motionless.

In figures 5A)-5e) shows sectional views of the front part of the casing 10A of the wing and engine of the toe 20 of the wing, similar to those shown in figure 1.

In the figure 5A) say no to the toe 20 of the wing shown in the fully retracted first position corresponding to figure 1, which deny the toe 20 of the wing mainly covers the front surface 14 of the wing and, thus, completes the profile of the wing at its forward edge, forming the configuration of the wing 10 in cruise flight mode.

In the figure 5e) say no to the toe 20 of the wing shown in the second fully extended position, in which it is only slightly overlaps the front surface 14 of the wing and which represents the configuration of the wing 10 during takeoff and/or landing, providing the maximum lift force. Adjusting the position deviated by the toe wing is performed in accordance with the scheme Fowler, in which an increase in the curvature of the profile is performed simultaneously with the extension of the profile of the wing in the direction of the width of the wing.

In figures 5b)-5d) shows three intermediate position.

As it becomes clear from comparing figures 5A)-5e), when moving deny the toe 20 of the wing first transition portion 20A, which is turned towards the first casing 11, moves on a circular path around an imaginary axis 30 of rotation (cf the and figure 1), while the second transition portion 20b, which is located on the end panel of the wing running casing and facing the second shell 12, while the nomination deny the toe 20 of the wing moves along the second shell 12 in the direction of the width of the wing. This second transition portion 20b of the panel 20 of the wing with a working lining is always close to the second casing 12, there are no cracks practically does not occur. Thus, in each position, that is in the first retracted position shown in figure 5A), and in the second extended position shown in figure 5e), and in any intermediate position between the two above-mentioned provisions, which are shown in figures 5b)-5d), say no to the toe 20 of the wing is always close, almost without cracks, to the first casing 11 and/or to the front surface 14 of the wing or to the second casing 12.

As you can see on the form in perspective, shown in figure 4, panel 22 of the wing running casing, which departs from the main body 21 deny the toe 20 of the wing in the direction of the second shell 12 of the casing 10A of the wing is formed, on the one hand, first, the hard part 22A of the panel, which is much closer to the main body 21, and, on the other hand, the second flexible part 22b of the panel, which is located farther from the main body 21. Specified the flexible portion 22b of the panel forms a flexible sealing edge, which is pressed to the second casing 12 of the torsion box 10A.

If the panel 22 of the wing running casing made of plastic reinforced by fiber, the first, rigid portion 22A of the panel, preferably made of plastic reinforced with carbon fiber, and the second, flexible portion 22b forming the sealing edge may be made of glass fiber reinforced plastics. Shell 21A say no to toe, which forms the front edge of the wing, may also be made of hard plastic reinforced with carbon fiber. To increase the structural strength of the shell 21 and the first rigid portion 22 of the panel is preferably executed as one unit. Parts 22A and 22b can be connected with rivets or screws or other suitable connecting means.

Transverse panel 26, 27, shown in figures 1 and 4, which can slide relative to each other, connected with the casing 10A of the wing by means of a connecting element 28, the length of which is variable.

As shown in figure 1, a portion of the second shell 12 along which can slide the second transition portion 20b (in the present embodiment of the invention is the second part 22b of the panel, which is made as a flexible sealing edge) when performing the adjustable positioning of cloneimage sock relative to the second shell 12, directed essentially tangentially relative to an imaginary axis 30 of rotation. This means that the above-mentioned sliding movement of the second transition portion 20b along the second shell 12 may in this position only to a small deformation of the second part 22b of the panel.

The mechanism 23 of the holding and drive in this variant contains more guide rails 23a, having an arched shape and spaced along the length of the wing, as shown in figure 3. The centers of these circles guide rails 23a are located on the imaginary axis 30 of rotation, i.e. the movement of the guide rail 23a and, accordingly, the movement reject the toe 20 of the wing occurs around the axis 30 of rotation, which runs in the direction of the length of the wing, with only one axis point 30 shown in figure 1.

These arc the guide rails 23a, which are spaced from each other along the length of the wing 10 can have the same radii of curvature, or they may have different radii of curvature, which, as a rule, decrease in the direction of the length of the wing.

The front surface 14 of the wing, which is a continuation forward of the first cladding 11 of the wing profile, typically has a radius of curvature which decreases in the direction of the length of the wing, and thus there is a corresponding narrowing of the main body 21 rejected the constituent of the toe 20 of the wing. In this design, as a rule, the radii of curvature of the guide rails 23a and the front surface 14 of the wing is reduced to the same extent.

As shown in figure 1 and in particular in the enlarged view of figure 1b), the second casing 12 provided with a recess 24, which includes an end panel 22 of the wing running casing, which takes place in the direction of the second shell 12, and the recess 24, at least in the retracted position deviated by the toe, provides mostly smooth, i.e. without steps, the transition from panel 22 deny the toe 20 of the wing to the second casing 12 of the casing 10A of the wing. The depth of this recess 24 approximately corresponds to the thickness of the panel 22 of the wing with a working lining.

For locking panel 22 deny the toe 20 of the wing relative to the casing 10A of the wing when the sock was removed, that is, it is in the position of flight in cruise mode (see figures 1 and 5A)), the inner surface of the panel 22 of the wing with a working shell near the side member 13 of the casing 10A of the wing may be provided with locking devices in the form of locking rollers for mode cruising flight, which is known in the art (these videos on the figure 1 is not shown).

The transition is almost without cracks deny the toe 20 of the wing to the first casing 11 or the front surface of the wing 14, which is present at the site of the first cladding 11 is the first transition h is here 20A, on the one hand, and on the site of the second skin 12 - second transition portion 20b, on the other hand, forms in the finished wing profile, in which virtually no breaks and which provides significantly improved aerodynamic shape of the wing, the lift force which increases significantly at low wind resistance and low noise pollution. This design is effective, in particular, it provides almost continuous contour of the wing profile, in which there are no zones of origin of the vortices on the lower surface of the wing, as well as other enclosed area on the lower surface of the wing, which are sources of vortices.

1. The rotary element to increase the lifting force, in particular deny the toe, for a wing with a high glide ratio and wing (10) includes a casing (10A), on the first side of which has a first casing (11), and on a second opposite side has a second casing (12), and the edge of the caisson, turned to say no to toe (20)has a front surface (14) of the wing, which is at least partly a continuation of the first casing (11) in the wing profile, and say no to toe (20) wing includes a rigid main body (21), which provides a transition from the first side to the second side wing (10), and the first transition portion (20A)that education is Jena to the first side wing (10), and second transitional portion (20b), which is converted to the second side wing (10), and say no to toe (20) wing has an adjustable manner by means of a mechanism (23) hold and drive connecting deny sock (20) wing caisson (10A)between the first retracted position in which the toe (20) covers a large portion of the front surface (14) of the wing, and a second extended position in which the toe (20) overlaps the lower portion of the front surface (14) of the wing, and the first transition portion (20A) sock (20)that faces the first side wing (10), can slide so that in any position it is supported on the first casing and/or on the front surface (14) of the wing, which is a continuation of the first casing (11), and there are no cracks, and toe (20) can be set at any position between the first and second positions with the formation of the corner relative to the caisson (10A) of the wing and the simultaneous extension of the profile of the wing by turning the sock around an imaginary axis (30) of the rotation, which is located on the side, opposite the first casing (11) outside the profile of the wing, and the second transition portion (20b) of the nose (20) wing, facing to the second side wing (10), in each position of the sock tightly pressed to the second casing (12) so that between them there are no cracks, being the m second transition portion (20b) deny sock (20) wing, facing the second side of the wing (10), is formed on the panel (22) of the wing running casing, which is a continuation of membranes (21A) of the rigid main body (21) deny sock (20) of the wing and passes to the second shell (12) of the wing (10), the second transition portion (20b) is designed to slide relative to the second casing (12) so that in any position of the sock wing transition to this covering had no cracks, while the second transition portion (20b) is formed of a flexible part of the panel (22) wing with a working lining, which is a continuation of the rigid main body (21) deny sock (20) wing, and a panel (22) of the wing running casing includes a first rigid portion (22A), which is a continuation of the rigid main body (21) deny sock (20) wing, and a second flexible portion (22b), which is a continuation of the first part (22A) of the panel and which forms a second transitional portion (20b).

2. The rotary element to increase the lifting force according to claim 1, in which the position of the imaginary axis (30) of rotation around which way adjustable turns deny sock (20) of the wing may vary along a given curve depending on the position of the sock.

3. The rotary element to increase the lifting force according to claim 1, in which the position of the imaginary axis (30) of rotation around which the regulation which has been created by the image turns deny sock (20) wing, not change when the position of the sock.

4. The rotary element to increase the lifting force according to claim 2 or 3, wherein the mechanism (23) hold and drive contains the connecting elements in the form of guide rods connecting the caisson (10A) wing with say no to toe (20) of the wing, and the mechanism (23) hold and drive is running from the steering actuator, which acts on these guide rods.

5. The rotary element to increase the lifting force according to claim 2 or 3, wherein the mechanism (23) hold, and the actuator includes a guide rail (23a)connecting the casing (10A) wing with say no to toe (20) of the wing and passing in the direction of the width of the wing, and the mechanism (23) hold and drive is running from the steering actuator, which acts on the guide rail (23a).

6. The rotary element to increase the lifting force according to claim 3, in which the guide rail (23a) has the shape of a circular arc, the center of which is located on the imaginary axis (30) of its rotation, and the front surface (14) of the wing, which is at least partly a continuation of the first casing (11) in the form of a wing profile, also has the shape of an arc of a circumference around an imaginary axis (30) so that the first transition portion (20A) deny sock (20) of the wing can be moved circumferentially along a circular front surface (14) cover the and when the regulated deviation toe wing.

7. The rotary element to increase the lifting force according to claim 1, in which the area of the second casing (12)along which can slide the second transition portion (20b) deny sock (20) wing with an adjustable deviation toe wing is generally tangentially with respect to the imaginary axis (30) of the rotation.

8. The rotary element to increase the lifting force according to claim 1, in which the flexible portion is located on the end panel (22) of the wing running casing, which is a continuation of the rigid main body (21) deny sock (20) of the wing.

9. The rotary element to increase the lifting force of claim 1, wherein on the inner surface of the first hard part (22A) panel has ribs (25) stiffness, which are essentially in the direction of the width of the wing.

10. The rotary element for increased lift of claim 8 in which the flexible part provided on the end panel (22) of the wing running casing, which is a continuation of the rigid main body (21) deny sock (20) wing shaped sealing edge, based on the second casing (12).

11. The rotary element to increase the lifting force according to claim 6, in which the mechanism (23) hold and drive contains the guide rails (23a)having the form of arcs of circles and spaced along the length of the wing (10) along the imaginary axis (30) of the rotation, where j is tsya the centers of the circumferences of the guideways.

12. The rotary element to increase the lift force by claim 11, in which is used a few rails, spaced along the length of the wing (10), and the radii of curvature of the guide rails (23a)having the form of arcs of circles, the same.

13. The rotary element to increase the lift force by claim 11, in which is used a few rails, spaced along the length of the wing (10), and the radii of curvature of the guide rails (23a)having the form of arcs of circles of different and decrease in the direction of the length of the wing.

14. The rotary element to increase the lift force on section 12, in which the front surface (14) of the wing, which is a continuation of the first casing (11), at least in part the shape of a wing profile has a radius of curvature that is constant along the length of the wing.

15. The rotary element to increase the lift force on item 13, in which the front surface (14) of the wing, which is a continuation of the first casing (11), at least in part the shape of a wing profile has a radius of curvature which decreases in the direction of the length of the wing.

16. The rotary element to increase the lift force on 15, in which the radii of curvature of the guide rails (23a) and front surface (14) of the wing decreases in the direction of the length of the wing to the same extent.

17. The rotary element to increase the lift force on item 13, in which the main body(21) deny sock (20) wing tapering in the direction of the length of the wing to decrease the radius of curvature of the guide rails (23a) and/or the front surface (14) of the wing.

18. The rotary element to increase the lifting force according to claim 1, in which the second casing (12) is provided with a recess or notch (24)intended for panel (22) of the wing running casing, passing in the direction of the second cover (12), and that the recess (24) provides a smooth transition from panel (22) of the wing with a working lining deny sock (20) wing to the second casing (12) of the casing (10A) of the wing at least in the retracted position the toe of the wing.

19. The rotary element to increase the lift force p, in which the depth of the recesses (24) corresponds to the thickness of the panel (22) of the wing running trim panel that goes in the direction of the second cover (12).

20. The rotary element to increase the lifting force according to claim 5, in which the guide rail (23a), which is part of the mechanism (23) holding the drive is a toothed rack, which can move the drive gear gear (23C) of the control actuator, and a drive gear gear (23 ° C) interacts with a toothed rack.

21. The rotary element to increase the lifting force according to claim 5, in which the guide rail (23a) is moved along the guide rollers (23b).

22. The rotary element to increase the lifting force according to claim 1, in which the caisson (10A) of the wing is equipped with locking device, with which the panel (22) of the wing with a working lining of cloneimage sock (20) wing, passing in the direction of the second cover (12)may be fixed relative to the casing (10A) of the wing in the retracted position the toe of the wing.

23. The rotary element to increase the lift force on p.22, in which the locking device is formed of the locking rollers for mode cruising flight.

24. The rotary element to increase the lifting force according to claim 1, in which the decline across the nose (20) wing hosted sealing device that provides aerodynamic seal deny sock (20) of the wing in relation to the environment.

25. The rotary element to increase the lifting force at point 24, in which the sealing device has a transverse panel (26, 27), which can slide relative to each other.

26. The rotary element to increase the lifting force according to claim 1, in which the hard shell of the main body (21) deny sock (20) of the wing and/or the hard part of the panel (22) of the wing running trim panel that goes in the direction of the second cover (12)made of plastic reinforced with carbon fiber.

27. The rotary element to increase the lifting force according to claim 1, in which the flexible portion of the panel (22) of the wing running trim panel that goes in the direction of the second cover (12)made of glass fiber reinforced plastics.