RU2466888C1 - Hovercraft - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: hovercraft sectional wing, alighting gear, horizontal fins unit installed on vertical fins unit, hull, power unit. Sectional wing contains centre wing and outer wings connected to it. Centre wing with negative transverse installation angle and rear edge sweep forward. Outer wings are jointed with centre on its rear edge side at positive crosswise angle. Alighting gear has floats installed on end sections of centre wing and beam with air propellers installed on it which beam is placed in front of centre wing. The beam is made able to be displaced in vertical plane. Power unit contains at least one engine accommodated inside centre wing, which engine is kinematically connected with corresponding air propeller of alighting gear via shaft line equipped with at least two one-axis articulated joints one of which is designed to connect shaft line with engine shaft, and the other - to connect shaft line with air propeller shaft. Hovercraft has water propeller made capable to rise from water. Each of shaft lines is made capable to change its length. Span of horizontal fins exceeds hovercraft span by at least 1.2 times.

EFFECT: invention allows to expand area of pitch angles and angles of altitude where necessary condition of dead-beat stability is met and to increase maneuvering ability in sailing and gliding mode.

13 cl, 18 dwg

Description

The invention relates to aircraft using a dynamic air cushion during flight, and in particular to ekranoplanes made according to the composite wing scheme, with a take-off and landing device using air blasting under the composite wing.

Known ekranoplanes made according to the scheme of a composite wing, using as a take-off and landing device, blowing air jets under the wing.

In the patent of the Russian Federation No. 2099217 for the invention “Wing, its take-off and landing device and wing folding drive”, IPC B60V 1/08, B64C 39/00, B64C 25/54, B64C 3/56, publication date 12/20/1997, [1 ], an ekranoplan containing a composite wing, a takeoff and landing device, horizontal tail mounted on a vertical tail, a fuselage, a power plant, a composite wing contains a center wing and consoles attached to it, a center wing with a negative transverse installation angle and a reverse sweep along the rear, is presented. edge, consoles are connected to with an entroplane from the side of the rear edge of the center section at a positive transverse installation angle, the side chord of the console is smaller than the end chord of the center section, the take-off and landing device contains floats installed in the end sections of the center section and a beam placed in front of the center section with air propellers mounted on it, the beam can be deflected in the vertical the plane, the power plant contains at least one engine located inside the center section, kinematically connected with the corresponding m air mover landing gear by shafting equipped with at least two hinges with two degrees, one of which is intended for connection to the motor shaft shafting, and the other - for connecting the shaft line with the shaft of the air mover.

According to the invention [1], the swing of the horizontal tail does not exceed the swing of the center section. This leads to the fact that the horizontal plumage flows around at negative bevel angles from vortices coming out from under the center section. In addition, the limitation of the range of horizontal plumage for a given specified moment of stability of the static moment of horizontal plumage leads to a decrease in its effectiveness due to the need to increase the area and, therefore, reduce the elongation and effectiveness of the horizontal plumage. This is a disadvantage of the ekranoplan presented in the description of the invention [1].

In the RF patent No. 2286268 for the invention “Ekranoplan”, IPC B60V 1/08, publication date 10/27/2006, [2], an ekranoplan containing a composite wing, a take-off and landing device, horizontal tail mounted on a vertical tail, the fuselage is presented , a power plant, a composite wing contains a center section and consoles attached to it, the center section is made with a negative transverse installation angle and with a reverse sweep along the trailing edge, the consoles are connected to the center section from the rear edge of the center section under the positive cross section m-pitch, chord onboard console lower end of center chord, landing gear comprises a fixed end sections and a center section disposed in front of the floats center-beam with the attached air movers, the beam is configured to deflect in a vertical plane. Moreover, according to the invention [2], when performing an ekranoplane with an extension of the composite wing of at least 3.0, an extension of the center section of 0.5 ... 0.8, an area of consoles equal to 0.3 ... 0.6 of the area of the center section, the static moment of horizontal tail and consoles equal to 0.25 ... 0.45, including the static moment of consoles 0.06 ... 0.11, the winged wing has good stability characteristics. However, in the invention [2] there is no information about the range of horizontal plumage, which is a disadvantage of the description of the invention [2], since it can lead to a decrease in the efficiency of horizontal plumage.

The invention [1] is taken as the closest analogue.

Solved by the invention, the task is to expand the operational modes of the ekranoplan. The technical result is the expansion of the range of pitch angles and heights at which the necessary condition of aperiodic stability is fulfilled, as well as an increase in maneuverability in the swimming and planing mode.

The invention consists in the following.

The ekranoplan, as in the closest analogue [1], contains a composite wing, a take-off and landing device, a horizontal tail mounted on a vertical tail, a fuselage, a power plant, a composite wing contains a center wing and consoles attached to it, the center wing is made with a negative transverse angle installation and with reverse sweep on the trailing edge, the console is connected to the center wing from the rear edge of the center wing at a positive transverse angle of the installation, the take-off and landing device contains the floats in the end sections of the center section and the beam placed in front of the center section with air propellers installed on it, the beam can be deflected in a vertical plane, the power unit contains at least one engine located inside the center section kinematically connected to the corresponding air drive of the take-off and landing aircraft devices by means of a shaft line equipped with at least two two-stage hinges, one of which is designed to connect the shaft line to the motor shaft, and the other for connecting the shaft line to the shaft of the air propulsion device, but unlike the closest analogue [1], the range of the horizontal tail exceeds the center-wing span by at least 1.2 times, each of the shaft lines is made with the possibility of changing its length, and the ekranoplan is equipped with at least one water propulsion device, configured to rise from the water.

An ekranoplan, characterized in that the elongation of the composite wing is at least 3.0, the elongation of the center section is 0.5 ... 0.8, the area of the consoles is 0.3 ... 0.6 of the area of the center section, and the static moment of the horizontal tail and consoles is 0, 25 ... 0.45, including the static moment of the consoles 0.06 ... 0.11 and the static moment of horizontal plumage 0.19 ... 0.34.

Ekranoplan, characterized in that the consoles are connected to the center section by inflows, each inflow is connected to the center section with a positive transverse angle, while the transverse angle of the influx is greater than the transverse angle of the consoles, the side chord of the console is equal to the end chord of the pylon, and the side chord of the pylon is smaller than the end chord center section.

WIG, characterized in that each air propulsion device of the takeoff and landing device is made in the form of a propeller.

WIG, characterized in that each air propulsion device of the takeoff and landing device is made in the form of a propeller in the ring.

WIG, characterized in that the vertical tail is single-tail.

WIG, characterized in that the vertical tail is made of two-keel.

Moreover, each keel of the vertical tail is formed by a fork and the keel itself, the fork is made as a continuation of the corresponding side wall of the fuselage, and the keel itself is set at an angle to the vertical plane.

In addition, the access hatch is located in the aft of the fuselage.

WIG, characterized in that it is additionally equipped with at least one mid-flight engine.

Ekranoplan, characterized in that the engine kinematically connected with the water propulsion is installed in the aft part of the fuselage.

An ekranoplan, characterized in that the engine kinematically connected with the water mover is installed in the stern of at least one float.

In this case, the drive shaft of the water mover is located in the casing, a water steering wheel is mounted on the casing, and the rotation mechanism of the water mover relative to the vertical axis is connected to the casing.

The invention is illustrated by drawings.

Figure 1 shows an ekranoplane with one keel when viewed in plan.

Figure 2 shows an ekranoplane with one keel in side view.

Figure 3 shows an ekranoplane with one keel in front view.

Figure 4 shows an ekranoplane with two keels when viewed in plan.

Figure 5 shows a winged aircraft with two keels when viewed from the side.

Figure 6 shows a winged aircraft with two keels when viewed from the front.

Figure 7 shows a section aa in figure 1.

On Fig shows a section bB in figure 4.

In Fig.9 shows a section bb in Fig.7 and Fig.8.

Figure 10 shows a section GG in figure 9.

In Fig.11 shows a section DD in Fig.1 and Fig.4.

On Fig shows a section EE in figure 1 and figure 4.

In Fig.13 shows a section FJ in Fig.1 and Fig.4.

On Fig shows a section II in figure 1 and figure 4.

On Fig shows a section KK in figure 4.

On Fig shows a section LL in Fig.15.

On Fig presents a graph (Xfa-Xfh) = f (Lgo / Ltsp) with h = Nmts / Vsgtsp = const.

On Fig presents a graph (Xfa-Xfh) = f (Lgo / Ltsp) with ϑ = const.

WIG is arranged as follows.

The ekranoplan (figures 1, 2, 3 and 4, 5, 6) contains the fuselage 1, a composite wing, consisting of a center section 2 and consoles 3, horizontal 4 and vertical 5 plumage, powerplant, takeoff and landing device (Fig.7 ... 10), as well as the power plant for maneuvering in the swimming and planing mode (Fig.2, 5, 13, 15, 16).

The center section 2 is made with reverse sweep along the trailing edge and with a negative transverse installation angle (with a transverse transverse "V"), equipped with mechanization of the front and / or trailing edge (Fig. 11, 12, 13). Consoles 3 are equipped with ailerons 6, which are advisable to perform freezing, i.e. combined with flaps (Fig.14). Consoles 3 are connected to the center wing 2 directly or by means of the pylon 7. The horizontal tail 4 is mounted on the vertical tail 5 and has a swing lgo that exceeds at least 1.2 times the swing of the center wing 2 ltsp: lgo / ltsp≥1.2. The fuselage 1 is preferably performed not exceeding the theoretical contours of the lower surface of the center wing 2. The vertical tail 5 can be performed single-keel (Fig. 1, 2, 3), two-keel (Fig. 4, 6) and with a large number of keels, for example, three-keel (in FIG. not shown). The horizontal plumage 4, it is advisable to connect with a single-keel vertical plumage 5 through struts 8 (Fig.2, 3). When performing vertical plumage 5 with a two-keel, each keel is expediently made of forkil 9, made in the form of an extension of the side wall of the fuselage 1, and the keel 10 itself, which can be installed with a transverse angle less than 90 degrees (Fig.6), and vertically (not shown in FIG.). In this case, the access hatch (not shown in Fig.) Is located from the stern of the fuselage 1 between the forks 9 (Fig. 4).

The power plant contains at least one engine 11, located in the center section 2 and kinematically connected with air propellers. As the engines 11 can be used automotive and piston aircraft engines. Wing can be equipped with an additional marching engine 12 (Fig.4, 5, 6), which can also be performed as a piston automobile or aircraft, as well as turboprop or turbojet.

The take-off and landing device contains floats 13 mounted on the center section 2 in its cross-sectional end sections (Figs. 1, 4), as well as air propellers kinematically connected with engines 10 located in front of the center section 2 (Figs. 1, 2, 4, 5 ) and equipped with a vertical deflection system. The air propellers are made in the form of a propeller 14 (Figs. 4, 5, 6, 8) or a propeller 14 in an annular nozzle 15, i.e. screws in the ring (figure 1, 2, 3, 7), and mounted on a beam 16 connected to the fuselage 1 with the possibility of rotation in a vertical plane.

As shown in Figs. 7 and 8, the beam 16 turning mechanism can be in the form of a power drive, for example, an electromechanism 17 pivotally connected to the power set of the fuselage 1, for example, a frame 18, and a single-stage hinge 19 connecting the beam 16 to the power set of the fuselage 1 (not shown in FIG.). The kinematic connection of the air propellers is made in the form of a shaft line 20 and two-stage hinges 21 and 22, connecting the shaft line 20, respectively, with the shaft 23 of the engine 11 and with the shaft 24 of the propeller 14 (Fig.7, 8). In this case, the shafting 20 is configured to change its length, i.e. telescopic (Fig.9, 10), which allows you to place two-stage hinges 24 and a single-stage hinge 19 in the plane, i.e. not lying on one straight line (Fig.7, 8). As two-stage hinges 21 and 22, cardans, constant velocity joints (CV joints) and other mechanisms can be used to change the position of the shaft 24 of the axis of the propeller 14 to angles, usually in the range of 0 ... 22 degrees, providing effective blowing by jets along the center section 2. The telescopicity of the shafting 20 can be ensured when performing the shafting 20 consisting of concentric shafts 25 and 26 interconnected by a spline connection 27 (Fig.9, 10).

To increase the efficiency of blowing, the center section 2 is equipped with mechanization of the front (Fig. 12) and rear (Fig. 11, 13) edges. On the trailing edge of the center section 2, a flap (not shown in Fig. Not shown) and / or a flap (11) can be installed. The flap on the center wing 2 is expediently made by a gapless two-link, while the first 28 and second 29 links are made to be deflected by the drive 30 and 31, respectively, both down and up, especially when the second link 29 is deflected relative to the first link 28 (Fig. 13). When performing the fuselage 1 with a two-keel vertical tail 5 under the fuselage, it is advisable to install a flap 32, equipped with a drive 33 for its movement relative to the center section 2 (Fig.13). The shield 32 is also advisable to perform a two-link, with the possibility of deflecting the second link relative to the first both down and up (not indicated in FIG.) And synchronizing the deflection of the links of the shield 32 and the first 28, and the second 29 links of the center wing flap 2. In addition, to increase it is advisable to equip the center section 2 with a front shield 34 located under the fuselage 1 and equipped with a drive 35 (Fig. 12).

The power plant for maneuvering in the mode of swimming and planing contains a water propulsion kinematically connected to the energy drive and configured to rise from the water and lower it into the water. A propeller 38 (FIGS. 2, 5) and a water cannon (not shown in FIG.) Are used as a water propulsion device. It is advisable to use an engine 39, mainly a ship engine, as an electric drive; an automobile engine, an electric motor, a hydraulic motor, etc. can also be used. The kinematic connection of the water propulsion with an electric drive, for example a propeller 38 with the engine 39, can be made in the form of a column 40, protected by a casing 41, and angular gears 42 and 43 (Fig.13, 15). The lifting of the propeller 38 together with the column 40 in the casing 41 and the angular gears 42 and 43 can be performed around the axis 44 by means of a variable-length rod, for example, a hydraulic cylinder 45 (Figs. 13, 15), an electromechanism, a rocker mechanism, etc. (not shown in FIG.).

The power plant for maneuvering in the swimming and planing mode can also be equipped with a water steering wheel 46 (Fig.2, 5), which can be mounted on the casing 41 of the column 40, or on its own axis (not shown in Fig.). When installing the water steering wheel 46 on its own axis, such an axis can be located on the casing 41 (not shown in Fig.). Water steering 46 is controlled by a hydraulic cylinder 47 (Fig. 16), an electromechanism and. etc. power drives (not shown in FIG.). In a preferred embodiment, it is advisable to install the water steering wheel 46 on the casing 41 of the column 40, which allows it to be raised and deflected together with the column 40 and the casing 41 by means of a hydraulic cylinder 46 (Figs. 13, 15, 16).

The water mover, it is advisable to install in the stern of the fuselage 1 (Fig.2, 13) or in the stern of the float 13 (Fig.5, 15, 16).

In a preferred embodiment, the ekranoplane fuselage 1 is integrated with a high-wing center wing 2, which reduces the surface area of the ekranoplane and, therefore, reduces its aerodynamic drag. In this case, with a single-keel vertical tail 5, the access hatch is located on the side wall of the fuselage 1, and with a two-keel vertical tail 5, the entrance hatch is located in the stern of the fuselage 1 between the forks 11. The consoles 3 are connected to the center section 2 by means of pylons 7, each pylon 7 is connected to the center section 2 with a positive transverse angle ψ _n > 0, while the transverse angle of the influx 7 is greater than the transverse angle ψ of _the installation of consoles 3 (ψ _n > ψ _k ), the side chord of the console 3 is equal to the end chord of the pylon 7, and the side chord of the pylon 7 is less than the end chord center section 2. The extension of the composite wing is at least 3.0 (λ = l ² / S≥3.0), the extension of the center section 2 is 0.5 ... 0.8 (λc = lc ² / S = 0.5 ... 0, 8), the area of the consoles Sк is 0.3 ... 0.6 of the area of the center section Sсп, the horizontal tail size lgo exceeds the size of the center section lсп not less than 1.2 times (lgo / lцп≥1,2), and the static moment of the horizontal tail 4 Ago = Sg * Lgo / (Ssn * Vac) and consoles 3 Ak = Sk * Lk / (Ssn * Wazp) is Ago + Ak = 0.25 ... 0.45, including the static moment of consoles 3 Ak = 0.06 ... 0.11 and the static moment of the horizontal tail 4 Ago = 0.19 ... 0.34.

Thus, in a preferred embodiment, the aerodynamic layout of the ekranoplan has the following parameters:

λ≥l ² / S≥3.0; λcp = lcp ² / S = 0.5 ... 0.8;

SK / SC = 0.3 ... 0.6; lgo / 1tsp≥1.2; ψ _P > ψ _K ;

Ago = Sgo * Lgo / (Sсп * Вапп) = 0.19 ... 0.34;

Ak = Sk * Lk / (Sc * Wac) = 0.06 ... 0.11;

Ago + Ak = 0.250.45;

Lgo = X _0.25Vago -X _CM - shoulder of the horizontal tail 4;

Lgo = X _{0.25; Waco-} X _CM - console arm 3;

X _TsM , X _0.25Vak , X _0.25Vago - coordinates along the building horizontal of the fuselage, respectively, of the center of mass of the winged wing, 0.25 of the average aerodynamic chord of Vak console 3 and 0.25 of the average aerodynamic chord of Vago horizontal tail 4.

WIG works as follows.

Before take-off, the ekranoplane via the water mover, for example, a propeller 38 and a water rudder 46 is discharged to the water area, for example the water area of the hydro-screen. The use of a water mover allows you to move with the engines 11 and 12 turned off, so that the noise level of the ekranoplan is acceptable for basing in the city, recreation areas, etc.

After reaching the initial take-off position, the winged wing is transferred to the take-off configuration (dashed lines in FIGS. 3 and 6, solid lines in FIGS. 11, 12, 13), namely, the first link 28 of the center wing flap 2 is rejected by the actuator 30 downward, the second the link 29 by the drive 31 is deflected relative to the first link 28 to the optimal position (usually up), the ventral rear 32 (Fig. 13) and the front 34 (Fig. 12) of the guards, respectively 33 and 35, are tilted down. The mechanization of the consoles 3, for example, the hanging ailerons 6, are translated into the take-off configuration by the drive 37 relative to the axis 36 (Fig. 14). With the drive 17, the beam 16 with the air propellers installed on it is deflected into the take-off position (shown in solid lines in Figs. 7 and 8). Moreover, since the single-stage 19 and two-stage 22 hinges lie in the same plane, but not on one straight line (Fig. 7. 8), when the beam 16 is rotated, the length of the shafting 20 changes due to the shafting 20 consisting of shafts 25 and 26 interconnected by spline connection 27 (Fig.9, 10).

Then, the jets from the propellers 14 (or propellers 14 in the annular nozzles 15, i.e., the propellers in the ring) mounted on an inclined beam 16, are directed under the lower surface of the center section 2, which together with the floats 6, the center section flaps 2 and the rear shield 32 form deflected front shield 34 reduces jet impulse losses due to return flows and thereby increases the ekranoplane lifting force when it is inflated.Tractor forces of propellers 14 or screws in the ring rotated by engines 11, 12 begin The dynamic air cushion created by blowing reduces the settlement of the floats 13, which leads to a decrease in the surface area of the floats washed by water and a decrease in hydrodynamic resistance.As a result, the distance and take-off time are significantly less than in the absence of blowing. speed sufficient to create an aerodynamic force exceeding the weight of the ekranoplane, and translates into a cruising configuration (solid lines in FIGS. 3 and 6, dashed lines in FIGS. 11, 12, 13).

The range of height above the screen and pitch angles during the cruising mode of movement is determined by the conditions of dynamic, static and aperiodic stability. A necessary condition for aperiodic stability is finding the aerodynamic focus in height Xfh = dMz / dCy (ϑ = const) in front of the aerodynamic focus in pitch Xfa = dMz / dCy (h = const), and the necessary condition for static and dynamic stability is finding the aerodynamic focus in pitch Xfa behind the center of mass _CM X WIG: Xfh <Xfa; X _CM <Xfa.

It is known that to obtain good stability and controllability characteristics, the aerodynamic focus in height should be located in the center of mass or close to it, and the focus spacing should be large: X _CM ≈Xfh <Xfa.

It has been established in the calculation and physical experiments that such conditions can be achieved in aerodynamic assemblies having the above parameters. Moreover, as shown in the graphs in FIGS. 17 and 18, the spacing of the aerodynamic foci begins to increase when the ratio of the horizontal tail to the center-wing span is at least 1.2: lgo / ltsn≥1.2. From the graphs in Fig.17, 18 it follows that the ratio of the range of the horizontal tail 4 and the center section 2 is taken based on the range of heights and speeds of screen flight required by the terms of reference for the development of an ekranoplan.

Thus, the set of features presented in the description provides an extension of the range of pitch angles and altitude at which the necessary condition of aperiodic stability is fulfilled, as well as an increase in maneuverability in the swimming and planing mode. The degree of disclosure of the ekranoplan device is sufficient to implement the invention in industry with the achievement of the claimed technical result.

The list of positions and symbols for the figures of the invention "WIG"

1 - fuselage;

2 - center section;

3 - consoles;

4 - horizontal plumage;

5 - vertical plumage;

6 - aileron console 3;

7 - pylon connecting the console 3 with the center section 2;

8 - strut horizontal plumage 4;

9 - forkil vertical plumage 5;

10 - the actual keel of the vertical tail 5;

11 - an engine located in the center section 2;

12 - mid-flight engine;

13 - a float;

14 - propeller;

15 - annular nozzles of the propeller 14;

16 - beam;

17 - the electromechanism of rotation of the beam 16;

18 - frame of the fuselage 1;

19 is a single-stage hinge connecting the beam 16 with the power set of the fuselage 1;

20 - shafting;

21 is a two-stage hinge connecting the shaft 20 to the shaft 23 of the engine 11;

22 - a two-stage hinge connecting the shaft 20 to the shaft 24 of the propeller 14;

23 - the shaft of the engine 11;

24 - the shaft of the propeller 14;

25 - shaft shaft 20;

26 - shaft shaft 20;

27 - spline connection of the shafts 25 and 26 with each other;

28 - the first link of the center wing flap 2;

29 - the second link of the center wing flap 2;

30 - drive movement of the first link 28 of the center wing flap 2;

31 - drive movement of the second link 29 flap center section 2;

32 - the back cover of the center section 2;

33 - drive moving the rear flap 32 of the center section 2;

34 - front dashboard of the center section 2;

35 - drive moving the front flap 34 of the center section 2;

36 - axis of rotation of the hanging aileron 6;

37 - drive moving the hanging aileron 6;

38 - propeller;

39 - engine for maneuvering afloat;

40 - column propeller drive 38;

41 - column cover 40;

42 - angular gearbox transmission propeller 38;

43 - angular gearbox transmission propeller 38;

44 - the axis of rotation of the column 40 of the transmission of the propeller 38;

45 - hydraulic cylinder lifting transmission propeller 38;

46 - water steering wheel;

47 - a hydraulic steering cylinder 46.

lgo - the span of the console 3;

ltsp - the scope of the center section 2;

Vacp - the average aerodynamic chord of the center section 2;

Vago - the average aerodynamic chord of horizontal plumage 4;

Vak - the average aerodynamic chord of consoles 3;

Sc - the area of the center section 2;

Sk - the area of consoles 3;

Sgo - the area of horizontal plumage 4;

Lgo - shoulder of the horizontal tail 4;

Lк - console arm 3;

X _CM - the coordinate of the center of mass of the ekranoplan;

X _{0.25 Wago} - coordinate of the aerodynamic focus of the horizontal tail 4;

X _{0.25 Vac} - the coordinate of the aerodynamic focus of the console 3;

λ≥L ² / S - lengthening of the composite wing of the winged wing;

λcp = Lcp ² / Scc - extension of the center section 2;

Ago = Sgo * Lgo / (Sсп * Вапп) - static moment of horizontal plumage 4;

Ak = Sк * Lк / (Sсп * Вапп) - static moment of consoles 3;

ψ _P - transverse installation angle of the pylon 7;

ψ _K is the transverse installation angle of the consoles 3.

Claims (13)

1. An ekranoplan containing a composite wing, a take-off and landing device, horizontal tail mounted on a vertical tail, a fuselage, a power plant, a composite wing contains a center wing and consoles attached to it, the center wing is made with a negative transverse angle of installation and with a sweep at the trailing edge , the consoles are connected to the center section from the side of the rear edge of the center section at a positive transverse installation angle, the take-off and landing device contains end sections installed in the end sections ntroplanes of floats and a beam placed in front of the center section with air propellers mounted on it, the beam is deflectable in a vertical plane, the power unit contains at least one engine located inside the center section kinematically connected to the corresponding air propulsion device of the take-off and landing device by means of a shaft shaft, equipped with at least two two-stage hinges, one of which is designed to connect the shaft to the motor shaft, and the other to Connections shafting air mover to the shaft, characterized in that the WIG craft equipped aqueous mover operable to lift it from the water, each shafting is arranged to change its length, the magnitude of the horizontal tail superior swing center section not less than 1.2 times. 2. Wing according to claim 1, characterized in that the elongation of the composite wing is at least 3.0, the extension of the center section is 0.5 - 0.8, the area of the consoles is 0.3 - 0.6 of the area of the center section, and the static moment is horizontal plumage and consoles is 0.25 - 0.45, including a static moment of consoles 0.06 - 0.11 and a static moment of horizontal plumage 0.19 - 0.34. 3. The ekranoplan according to claim 1 or 2, characterized in that the consoles are connected to the center wing by inflows, each inflow is connected to the center wing with a positive transverse angle, while the transverse angle of the influx is greater than the transverse angle of the consoles, the side chord of the console is equal to the end chord of the pylon , and the side chord of the pylon is smaller than the end chord of the center section. 4. Wing according to claim 1 or 2, characterized in that each air propulsion device of the takeoff and landing device is made in the form of a propeller. 5. Wing according to claim 1 or 2, characterized in that each air propulsion device of the takeoff and landing device is made in the form of a propeller in the ring. 6. Ekranoplan according to claim 1, characterized in that the vertical tail is single-tail. 7. Wing according to claim 1, characterized in that the vertical tail is made of two-keel. 8. Wing according to claim 7, characterized in that each keel of the vertical tail is formed by a fork and the keel itself, the fork is made as a continuation of the corresponding side wall of the fuselage, and the keel itself is set at an angle to the vertical plane. 9. Wing according to claim 7 or 8, characterized in that the entrance hatch to the fuselage is located in the aft of the fuselage. 10. WIG according to claim 1 or 2, characterized in that it is additionally equipped with at least one mid-flight engine. 11. The ekranoplan according to claim 1, characterized in that the engine kinematically connected with the water mover is installed in the aft part of the fuselage. 12. The ekranoplan according to claim 1, characterized in that the engine, kinematically connected with the water propulsion device, is installed in the stern of at least one float. 13. The ekranoplan according to claim 11 or 12, characterized in that the drive shaft of the water propulsion device is located in the casing, a water steering wheel is mounted on the casing, and the rotation mechanism of the water propulsion device relative to the vertical axis is connected to the casing.

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