RU2232690C2 - Wing-in-ground effect craft - Google Patents

Abstract

FIELD: designing of wing-in ground effect craft.

SUBSTANCE: proposed wing-in ground effect craft has hull with upper wing and lower wing with side extensions arranged to biplane layout. Said wing-in-ground effect craft has also horizontal and vertical control surfaces, booster and cruise engines and control system. Upper wing is made with sweepback of leading edge, with leading-edge slats and slotted flaps. Lower wing is rectangular in plan with flat lower surface and flaps, and its side extensions are made in form of floats-skegs. Distance between upper wing and lower wing is greater than upper wing chord. Booster engine is located in hull nose and is provided with outlet channels-nozzles to direct gas jets under lower wing and form starting air cushion. Third wing arranged in nose part of wing-in-ground effect craft consists of two aerodynamic wings-cantilevers with wing angle of attack and sweepback of leading edge, leading-edge slats and slotted flaps with aerodynamic vanes on ends I form of vertical plates. Height of location of said wing relative to center of mass of wing-in ground effect craft is smaller than corresponding height for upper wing located in tail part of wing-in-ground effect craft. Upper wing can be have angle of attack, aerodynamic vanes on ends in form of vertical plates and aspect ratio

Lower wing can have aspect ratio

Flat lower surface of lower wing can form wing angle of attack with support underlying surface.

EFFECT: improved operating characteristics of wing-in-ground effect craft owing to increased profitableness, efficiency and safety.

4 cl, 3 dwg

Description

The invention relates to transport and for the design and construction of ekranoplanes.

Known ekranoplan containing a fuselage with upper and lower having side washers, wings arranged according to the biplane, vertical and horizontal tail, launch and mid-flight engines, control system, the upper wing is made by lengthening λ≥5, with sweep along the leading edge with slats and slotted flaps, the lower wing is made with an elongation λ≤1.5 of rectangular shape in plan, with a flat lower surface with flaps, and its side washers are made in the form of skeg floats, and the distance of the upper wing from neither there is more chord of the upper wing, its starting engine is located inside the nose of the fuselage and is made with gas outlet nozzles for directing gas jets under the lower wing and forming the starting air cushion (patent RU 2129501 C1, 6 V 60 V 1/08, 64 C 39/08, publ. 04/27/1999, bull. No. 12).

However, the known ekranoplan has low performance.

The technical result from the implementation of the described invention is to improve the performance of the ekranoplan by increasing its profitability, economic efficiency and operational safety.

This technical result is achieved by the fact that in an ekranoplane containing a fuselage with upper and lower wings having side washers, wings arranged according to the biplane diagram, vertical and horizontal tail units, launch and main engines, a control system, the upper wing is made with lengthening λ <5, with sweep along the leading edge with slats and slotted flaps, the lower wing is made with an elongation λ> l, 5 of rectangular shape in plan, with a flat lower surface with flaps, and its side washers are made in the form of float-skeg s, and the distance of the upper wing from the lower one is greater than the chord of the upper wing, its starting engine is located inside the nose of the fuselage and is made with gas outlet nozzles for directing gas jets under the lower wing and forming the starting air cushion, according to the invention, the third wing is located in the nose of the winged wing consisting of two aerodynamic wing-consoles having an angle of attack with sweep along the leading edge, with slats and slotted flaps, made with aerodynamic wings kami at the ends in the form of vertical plates, wherein the height of the wing with respect to this center of mass WIG smaller than the corresponding height for the wing disposed in the rear WIG. The upper wing in the tail of the winged wing, having an angle of attack with sweep along the leading edge, is also made with aerodynamic wings at the ends in the form of vertical plates. The use of the aerodynamic wing in the bow significantly increases the supporting properties of the winged aircraft due to both an increase in the total aerodynamic component of the aerodynamic wings in the bow and tail of the winged wing, and the corresponding optimal distribution of the aerodynamic lift in a certain optimal proportion between the front and rear wings of the winged wing and the resulting point of its application (aerodynamic focus, determined from the condition of stability of the ekranoplan), significantly improving the stability the airworthiness and controllability of the ekranoplan, increasing the reliability of the “attachment” of the aircraft to the screen, the ekranoplan’s ability to self-stabilize in height increases and the longitudinal stability during flight on the screen increases compared to the prototype, it allows to reduce takeoff and landing speeds, reduce dynamic loads on the controls and on the structural and power circuit of the apparatus and thereby reduces the total weight of the entire structure, thereby increasing the useful weight return of the ekranoplan as a vehicle compared with the prototype, it also allows to increase stability and controllability, which means to increase flight safety both on the screen and in transition modes. All this makes it possible to have a relative elongation of the upper wing in the tail section of the winged aircraft λ <5, the lower wing is made with an extension of λ> 1.5, and the flat lower surface of the lower wing forms an attack goal relative to the supporting underlying surface, thereby further improving the “attachment” of the apparatus to the screen, its self-stabilization in height and a further increase in longitudinal stability when flying on the screen, increasing flight safety compared to the prototype, while increasing, as mentioned above, the supporting properties of the winged aircraft as Tranfer money.

Thus, the use of aerodynamic wing-cantilevers in the bow of the winged wing can reduce the relative elongation of the upper wing located in the tail, and make it λ <5, and the lower screen wing, made with an angle of attack relative to the supporting underlying surface, to perform with a relative elongation λ > 1.5, thereby allowing you to significantly increase the useful weight return of the ekranoplan as a vehicle compared to the prototype, allows you to increase stability and controllability, and therefore increase and flight safety on the screen and in transient conditions.

The invention is illustrated by drawings, in which:

- figure 1 is a side view of an ekranoplane;

- figure 2 is a view of the winged aircraft from above;

- figure 3 is a front wing view.

The winged wing contains a fuselage 1, an upper wing 2 in the tail with slats 3, slotted flaps 4, aerodynamic wings 17 at the ends, a wing 13 in the bow with slats 14, with flaps 15, aerodynamic wings at the ends 16. Upper wing 2 in the tail and the lower wing 5 are arranged according to the biplane scheme, the lower wing 5 has flaps 6 and side washers 7 in the form of skeg floats. The ekranoplan is made with vertical 8 and horizontal 9 feathers. There are marching engines 10 and a starting engine with an air intake 11 (the engine is located in the nose of the fuselage 1 and has gas outlet nozzles for supplying gas jets through the lower outlet nozzles 12 under the wing 5). The upper wing 2 is made with an extension of λ <5 and with sweep along the leading edge, and the lower wing 5 has a rectangular shape in plan with an extension of λ> 1.5, the flat lower surface of which has an angle of attack relative to the supporting underlying surface. The distance of wing 2 from wing 5 is greater than the chord of wing 2.

WIG is made with a control system (not shown in the drawings).

WIG operation is as follows.

The run of the ekranoplan (similar to the prototype) is carried out against the direction of the wind with small directional angles to the wave front of the supporting surface and begins by transferring the engines to the maximum operating mode.

At the beginning of the movement, skeg floats 7 are in contact with water, and then, as the speed of the ekranoplane increases under the influence of the incoming air flow and the starting “blow” engine, which receives air through its air intake 11 on wing 5, on the upper aerodynamic wing 13 in aerodynamic lifting force is generated in the bow and wing 2 in the tail of the winged wing from the incoming air flow, under the influence of which the winged wing breaks off the surface of the water and continues flying in cruise mode eniya only with engines 10, i.e. as a result, the lifting force tearing the winged wing from the water surface is the sum of the aerodynamic lifting force on the nose wing 13, the aft wing 2 and the screen wing 5.

Wing landing similar to the prototype is carried out on the water surface by transferring the engines to low-throttle flight mode with the flaps 4 of the upper rear wing 2 released, the flaps 15 of the front wing 13 and the flaps 6 of the lower wing 5 released. from the starting engine in the speed range of planing.

Engines, aggregates, mechanisms and equipment (not shown in the drawings) are selected from serial aviation products and provide specified operating modes.

Comparing the technical and economic characteristics of the developed ekranoplan with the third wing located in the bow, consisting of two aerodynamic wing-consoles and with a biplane wing, with well-known modern vehicles, we can conclude that the distinctive features of the described invention together give the ekranoplan properties and provide him with advantages in the technical, economic and environmental aspects, namely in the reliability of the design, functional simplicity and os This is especially true in a rational aerodynamic configuration that provides sufficient “attachment” of the apparatus to the screen due to the lower wing 5 and wing 13 located in the bow of the ekranoplan, their combination and interaction allow speed maneuvers to safely pass the narrowness of rivers, congestion of ships, bridges, etc. .P.

The technical appearance and appearance of the ekranoplan is formed as a fundamentally new type of marine high-speed vehicle, which has no analogues either in appearance or in the range of operational characteristics, which is determined by all-weather and year-round operation, a high level of reliability and guaranteed flight safety.

The application of the ekranoplan is diverse, for example, for operation in river, lake and coastal marine conditions - for the fast delivery of passengers, goods, mail, etc. from one region to another, as well as such ekranoplans will find application for changing shifts, etc.

The results of studies and tests in wind tunnels, on a towed model, allowed for the calculation optimization of the main parameters and characteristics of systems, assemblies and equipment that correspond to the layout scheme and provide the specified operating modes, proving the possibility of obtaining high flight performance at different altitudes of the screen flight.

Claims (4)

1. An ekranoplane containing a fuselage with an upper and lower one having side washers, wings arranged according to a biplane, vertical and horizontal tail, launch and mid-flight engines, a control system, while the upper wing is swept along the leading edge, with slats and slotted flaps, the lower wing is made rectangular in plan with a flat lower surface and with flaps, and its side washers are made in the form of skeg floats, and the distance of the upper wing from the lower one is greater than the chord of the upper edge la, its starting engine is located inside the nose of the fuselage and is made with gas exhaust nozzles for directing gas jets under the lower wing and forming the starting air cushion, characterized in that in the nose of the winged wing there is a third wing, consisting of two aerodynamic wing-consoles, having an angle of attack, with sweep along the leading edge, with slats and slotted flaps, made with aerodynamic wings at the ends in the form of vertical plates, and the height I of this wing relative to the center of mass of the winged wing is less than the corresponding height for the upper wing located in the rear of the winged wing. 2. Wing according to claim 1, characterized in that the upper wing has an angle of attack, aerodynamic wings at the ends in the form of vertical plates and an elongation of λ <5. 3. Wing according to any one of the preceding paragraphs, characterized in that the lower wing has an elongation of λ> 1.5. 4. Wing according to any one of the preceding paragraphs, characterized in that the flat lower surface of the lower wing forms an angle of attack with a supporting underlying surface.

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