RU2471660C2 - Hovercraft - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to dynamic air-cushion vehicles, in particular to hovercrafts. Hovercraft has fuselage, wing, vertical and horizontal fins, power plant and take-off-landing device. Power plant includes at least one engine connected with air propeller. Take-off-landing device has floats connected with wing and pillar mounted on fuselage in front of front wing edge. At least one air propeller is mounted on pillar and furnished with device for gas jet deflection relative to centre-section wing. Planing step is arranged between fuselage stem and wing rear edge. Floats are provided with at least one lateral planing step. Vertical fins are made twin-tailed with dorsal fins and vertical stabiliser. The dorsal fins are formed by extension of fuselage side wall. Fuselage aft is made tapering in vertical plane. Top surface of fuselage aft is provided with hatch connected with fuselage with possibility to move relative to fuselage, and with hatch displacement drive.

EFFECT: invention increases dimensions of cargoes and improves hovercraft maintenance conditions and its take-off-landing characteristics.

8 cl, 8 dwg

Description

The invention relates to aircraft using a dynamic air cushion during flight, and in particular to ekranoplanes.

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

In the patent of the Russian Federation No. 2286268 for the invention “Ekranoplan”, IPC B60V 1/08, publication date 10/27/2006 [1], an ekranoplan containing a fuselage, a wing, vertical and horizontal tail, a power plant, take-off and landing device, is presented this wing is made integral, including the central wing - the center section, and the consoles attached to it, the center section is made with a negative transverse installation angle and with a reverse sweep along the trailing edge, floats are installed at the ends of the center section, the consoles are connected to the center section from its side the bottom edge and are installed at a positive transverse angle, the power plant contains at least one engine kinematically connected to the corresponding air propulsion device, the take-off and landing device contains floats connected to the center section, a pylon mounted on the fuselage in front of the front edge of the center section, with on the pylon with at least one air propulsion device equipped with means for deflecting the gas jet relative to the center section. Presented in the description of the invention [1] the set of features of an ekranoplan provides good aerodynamic characteristics, stability and controllability. However, the ekranoplan presented in the description of the invention [1] is single-winged, which complicates the loading and unloading of passengers and goods and limits the dimensions of the goods carried.

RF patent №2252175 for the invention "Multipurpose amphibious aircraft (ISA)", IPC ВСС 35/00, publication date 05/20/2005 [2], a seaplane containing a fuselage, a wing, a power plant, a take-off and landing device, is presented horizontal plumage and two-keel vertical plumage, while the aft of the fuselage is made tapering in a vertical plane and equipped with a cargo hatch. The presented set of features allows loading and unloading of goods with dimensions in the cross section close to the cross section of the fuselage cabin. However, the deviation of the hatch flaps to the sides and their fixation along the keels of the vertical tail while ensuring the cross-sectional dimension of the entrance hatch is equal to the cross-sectional dimension of the fuselage cabin leads to a complication of the structure. In addition, the seaplane presented in the description of the invention [2] cannot fly in the zone of effect of the screen effect, which limits its operational properties in comparison with the ekranoplan.

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

Solved in the invention, the task is to improve the performance of the ekranoplane. The technical result achieved is an increase in the dimensions of the transported goods and an improvement in the conditions for servicing the ekranoplan. The technical result also consists in improving takeoff and landing characteristics.

The invention consists in the following.

The ekranoplan, as in the closest analogue [1], contains a fuselage, a wing, a vertical and horizontal tail, a power plant, a take-off and landing device, a power plant contains at least one engine connected to an air propulsion device, the take-off and landing device contains floats connected to the wing and the pylon mounted on the fuselage in front of the leading edge of the wing, at least one air propulsion device is provided on the pylon, equipped with means for deflecting the gas jet relative to the wing, but unlike the most a close analogue [1] between the stern of the fuselage and the trailing edge of the wing, a redan is made, the floats are made with at least one side redan, the vertical tail is double-winged, containing forks and keels, and the forks are made as a continuation of the corresponding side wall of the fuselage, aft part of the fuselage is made tapering in a vertical plane, the upper surface of the aft part of the fuselage is equipped with a hatch connected to the fuselage with the possibility of its movement relative to the fuselage, and a drive to move the hatch.

The ekranoplan is characterized by the fact that on the surface of the forks are made guides interacting with the reciprocal elements of the hatch, and a drive is installed on the fuselage, which ensures the deflection of the hatch in the vertical direction.

The ekranoplan is characterized in that the trailing edge of the forks is vertical.

The ekranoplan is characterized in that the keels of the vertical tail are installed at an angle to the vertical plane passing through the construction horizontal of the ekranoplan.

The winged wing is characterized by the fact that the wing is made of a composite, formed from the center section and the consoles attached to it, the center section is made with a negative transverse installation angle and with a reverse sweep along the trailing edge, floats are installed at the ends of the center section, the consoles are connected to the center section from the side of its rear edge and installed at a positive lateral installation angle.

At the same time, the ekranoplan is characterized by the fact that the center wing is equipped with gapless two-link flaps, and the ventral part of the center wing is equipped with a two-link flap, with each of the flap and flap links equipped with its own displacement drive.

Wing is characterized by the fact that the means of deflecting the gas jet relative to the wing is made in the form of a rotation mechanism in the vertical plane of the pylon with engines mounted on it.

The ekranoplan is characterized in that it is equipped with at least one engine connected to the horizontal tail.

The invention is illustrated by drawings.

Figure 1 shows a winged plane in plan view.

Figure 2 shows the winged plane when viewed from the side.

Figure 3 shows the ekranoplan when viewed from the front.

Figure 4 shows a section aa in figure 1.

Figure 5 shows a section bB in figure 4.

Figure 6 shows a section bb in figure 1.

In Fig.7 shows a section GG in Fig.1.

On Fig shows a section DD in figure 1.

WIG is arranged as follows.

Wing (1, 2, 3) contains the fuselage 1, wing, vertical and horizontal 2 plumage, floats 3, at least one engine 4 connected to an air propulsion device, made, for example, in the form of a propeller 5 and located in front of wing. As the engine 4 can be used aircraft piston, turboprop and other engines. On light ekranoplans, an automobile engine can be used as engine 4.

The horizontal tail 2 is installed above the fuselage 1, for example, on a vertical tail. The vertical plumage is made two-keel, each of which contains a fork 6 and the keel 7 proper, equipped with a rudder (not indicated in Fig.). Forkil 6 is made as a continuation of the corresponding lateral wall 8 of the fuselage 1, their trailing edge can be either swept, having, for example, the same sweep with the trailing edge of the keels 7 of the vertical tail (Fig. 2), and perpendicular to the horizontal construction (GF) of the fuselage 1 ( Fig 4). The keels 7 of the vertical tail can be installed both vertically (not shown in Fig.), And at an angle to a vertical plane passing through the construction horizontal of the ekranoplan (Fig. 3).

The fuselage 1 in the aft 9 is made with maintaining a constant width and tapering in a vertical plane (figure 2). The aft part 9 of the fuselage 1 is equipped with a hatch 10 located on its upper surface. The hatch 10 is connected to the fuselage 1 with the possibility of its movement relative to the fuselage 1 by means of a drive. The drive movement of the hatch 10 contains a power drive, made, for example, in the form of at least one hydraulic cylinder 11 connected to the structure of the fuselage 1, and guides 12 mounted on the forks 6, interacting with the response element of the hatch 10 (Fig. 4).

The guide 12 can be made in the form of an open profile 13 located along the arc, equipped with a rail 14, etc. an element that does not extend beyond the theoretical contours of the forkil 6. In this case, the response element of the hatch 10, interacting with the corresponding guide 12, can be made in the form of a roller 15 with flanges 16 covering the rail 14 (Fig. 5). In the extreme positions, namely, with the closed and open hatch 10, each of the guides 12 and the rollers 15 is equipped with a latch for their relative position (not shown in Fig.). The latch can be made in the form of an electromechanism, for example, a solenoid with a retractable shaft entering into the coaxial holes on the guides 12 and in the roller 15 (not shown in Fig.), Electric locks and otherwise.

The hatch 10 can be made integral, with the upper part lifted by the power drive, as well as the lower part 17, tilted down and serving as a ramp during loading and unloading (figure 4).

To improve take-off and landing characteristics and movement in the mode of navigation of the winged wing between the stern of the fuselage 1 and the trailing edge of the wing, a redan 18 was made (Fig. 2, 4), floats 3 are made with at least one side redan 19 (Fig. 1, 2 ) At least one air propulsion device installed in front of the wing is equipped with a gas jet inclination means, made for example in the form of a pylon 20 connected to the fuselage 1 with at least one engine 4 mounted on it, which is moved by means of a drive 21 relative to axis 22 (Fig.6). As an air propulsion device, an air propeller 5, a turbojet nozzle and other devices for moving gas can be used (not shown in FIG.).

To increase profitability in the cruise mode of screen flight, the ekranoplane can be equipped with at least one engine 23 connected to the horizontal tail 2 (figure 1 ... 4).

In a preferred embodiment, the winged wing is made integral, consisting of a center wing 24 and consoles 25, a center wing 24 is made with a reverse sweep along the trailing edge (figure 1) and with a negative transverse installation angle (transverse "V" - figure 3), console 25 equipped with ailerons 26 (Fig. 1) and can be equipped with mechanization of the front and / or trailing edges (not shown in Fig.), and the fuselage 1 does not go beyond the theoretical contours of the lower profile surface of the center section 24 (Fig. 3). The center section 24 is equipped with mechanization of the trailing edge, made in the form of a flap 27, which is preferably made gapless two-link. The flap 27 can be performed divided by the span of at least two sections. Each link gapless two-link flap 27 has its own drive 28 and 29 (Fig.7). Under the fuselage 1, a flap 30 is installed, containing the same number of links with the flap 27, each link, for example, a two-link flap 30, is equipped with its own actuators 31 and 32 (Fig. 8).

WIG works as follows.

When loading and unloading, the hatch 10 is raised up by extending the rod of the hydraulic cylinder 11, moving the roller 16 connected to the hatch 10 along the guides 12 and fixing the hatch 10 relative to the fork 6. When the hatch 10 is made from the upper and lower 17 parts, the upper part of the hatch 10 is raised, and the lower part 17 of the hatch 10 is omitted to move goods along it. After the completion of loading and unloading operations, the hatch 10 is closed and locked in the closed position. WIG is translated into take-off configuration (dash-dotted lines in figure 4, 6, 7, 8). At the same time, the pylon 20 with the motors 4 installed on it is rotated by the drive 21 to ensure the inclination of the jet behind the air propulsion device, made, for example, in the form of a propeller 5 (Fig.6).

When performing an ekranoplan, in a preferred embodiment, the gapless two-link flaps 27 of the center wing 24 are moved to the take-off position, in which the first link with the drive 28 deviates downward and the second link with the drive 29 deviates upward relative to the first link (Fig. 7). Synchronously with the flap links 27 are rejected by the actuators 31 and 32, respectively, the first and second link of the flap 30 (Fig. 8).

Then the pylon 20, together with the motors 4 mounted on it, drive 21 deviates into the take-off position, the engines 4 are turned on, and the air stream from the propellers, for example propellers 5, is directed under the wing, for example, under the center section 24. This creates a dynamic air cushion, and the second links of the flap 27 and the flap 30 deflected upward prevent reverse flow under the center section 24, and an air stream flowing out from under the flaps 27 and the flaps 30 creates thrust. The ekranoplane begins to move, descends from the gentle coast into the water and begins to run through the water. The presence of lateral redans 19 on the floats 3 provides an ekranoplane exit with blowing to the planing mode, and redan 18 prevents the ekranoplan exit to unstable planing modes. Thanks to the blowing, the ekranoplan unloads and leaves the water at a speed at which the aerodynamic lift is less than the weight of the ekranoplan. After exiting the water, the hydrodynamic resistance decreases, and the ekranoplan moves with acceleration. When cruising speed is reached, the pylon 20 with installed engines 4 with air propellers, for example screws 5, is converted to the cruising configuration, the flaps 27 and flaps 30 are removed (solid lines in Figs. 6, 7, 8), and the ekranoplane performs a cruise flight to screen mode. After the flight, the flaps 27 and the flaps 30 are transferred to the landing configuration, and the winged wing landing. To go ashore, the pylon 20 with the engines 4 installed on it is rotated to the landing position, the flaps 27 and the flaps 30 are transferred to the landing configuration, due to the blowing the ekranoplan is unloaded and goes ashore on a dynamic air cushion.

After the ekranoplan stops, the upper part of the hatch 12 rises, the lower part 19 is lowered and the ekranoplan is unloaded. When carrying out preventive and repair work, as well as in preparation for the next flight, especially away from the base, the upper surface of the raised hatch 12 can be used as a support for installing ladders, placing tools and equipment on it. This improves the performance properties of the ekranoplan both in terms of loading and unloading, and in terms of performing maintenance and repair of the vertical tail and the engine 23 mounted on the horizontal tail 2.

Thus, the claimed combination of features improves the performance of the ekranoplan both during take-off and landing, and during loading and unloading, maintenance and repair of the ekranoplan.

Presented in the description of the invention, the level of disclosure of the set of essential features is sufficient for the development and manufacture of an ekranoplan glider at specialized enterprises with the achievement of the claimed technical result.

The list of positions to the figures of the invention "WIG"

1 - fuselage;

2 - horizontal plumage;

3 - floats;

4 - engine;

5 - propeller;

6 - forkil;

7 - keel;

8 - side wall of the fuselage 1;

9 - aft of the fuselage;

10 - hatch;

11 - a hydraulic cylinder;

12 - guide;

13 - open profile guide 12;

14 - rail;

15 - roller;

16 - flanges of the roller 15, covering the rail 14;

17 - the lower part of the hatch 10;

18 - redan between the stern of the fuselage 1 and the trailing edge of the wing;

19 - side redan on the float 3;

20 - pylon;

21 - pylon drive 20;

22 - the axis of rotation of the pylon 20;

23 - an engine mounted on a horizontal tail 2;

24 - the center section of the composite wing;

25 - console composite wing;

26 - ailerons of consoles 25;

27 - gapless two-link flap center section 24;

28 - drive deflection of the first link of the flap 27 of the center section 24;

29 - deflection drive of the second link of the flap 27 of the center section 24;

30 - two-link flap;

31 - drive deflection of the first link of the flap 30 of the center section 24;

32 - drive deflection of the second link of the flap 30 of the center section 24.

GFS - the average horizontal of the fuselage;

VL - waterline.

Claims (8)

1. The ekranoplan containing the fuselage, wing, vertical and horizontal tail, power plant, takeoff and landing device, the power plant contains at least one engine connected to an air propulsion device, the takeoff and landing device contains floats connected to the wing, and a pylon, mounted on the fuselage in front of the leading edge of the wing, at least one air propulsion device is provided on the pylon, equipped with means for deflecting the gas jet relative to the center section, characterized in that between the stern of the fuselage and days, the wing edge is made redan, the floats are made with at least one side redan, the vertical tail is made of two-keel, containing forks and keels, while the forks are formed by the continuation of the corresponding side wall of the fuselage, the aft of the fuselage is made narrower in the vertical plane, the upper surface of the aft part of the fuselage is equipped with a hatch connected to the fuselage with the possibility of its movement relative to the fuselage, and a drive to move the hatch. 2. Wing according to claim 1, characterized in that on the surface of the forks are made guides interacting with the mating elements of the hatch, and a drive is installed on the fuselage, providing the deflection of the hatch in the vertical direction. 3. Wing according to claim 1 or 2, characterized in that the trailing edge of the forks is vertical. 4. The ekranoplan according to claim 1 or 2, characterized in that the keels of the vertical tail are installed at an angle to the vertical plane passing through the construction horizontal of the ekranoplan. 5. Wing according to claim 1, characterized in that the wing is made up of a composite formed from the 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, floats are installed at the ends of the center section, the consoles are connected to the center section from the side of its trailing edge and installed at a positive transverse angle of installation. 6. The ekranoplan according to claim 5, characterized in that the center wing is equipped with gapless two-link flaps, and the ventral part of the center wing is equipped with a two-link flap, with each of the flap links and the flap equipped with its own displacement drive. 7. Wing according to claim 1, or 2, or 5, characterized in that the means of deflecting the gas jet relative to the center section is made in the form of a turning mechanism in the vertical plane of the pylon with engines mounted on it. 8. Wing according to claim 1, or 2, or 5, characterized in that it is equipped with at least one engine connected to a horizontal tail.

Images