RU2235654C2 - Wing-in-ground effect craft - Google Patents

Abstract

FIELD: transport engineering; wing-in-ground effect craft.

SUBSTANCE: proposed wing-in-ground effect craft has hull with upper high-aspect ratio wing rectangular in plan, with leading edge slats, slotted flaps and ailerons with flat lower surface symmetrical relative to diametric plane of wing-in-ground effect craft. Wing-in ground effect craft has lower low-set low-aspect ratio wing with flat lower surface rectangular in plan, with flaps and side extensions in form of displacement floats-skegs. Distance between upper and lower wings in height exceeds chord of upper wing. Wing-in-ground effect craft is provided with vertical and horizontal control surfaces, cruise engines and control system. Cruise engines are of tractor-type, third wing located in nose part of wing-in-ground effect craft consists of two aerodynamic cantilever wings with angle of attack, sweepback of leading edge, with leading edge slats and ailerons-flaps. Cantilever wings of third wing are provided with aerodynamic vanes on ends in form of vertical plates. Upper wing can be made with aerodynamic vanes on ends in form of vertical plates and with aspect ratio λ<8. Lower wing can have aspect ratio λ >1, and its flat lower surface can have angle of attack with support underlying surface.

EFFECT: improved performance of wing-in-ground effect craft.

2 cl, 3 dwg

Description

The invention relates to transport and for the creation of ekranoplanes - vessels with dynamic principles of maintenance, which are high-speed vehicles of a new type.

Known ekranoplan containing a fuselage with an upper wing of large elongation of a rectangular shape in plan with slats, slotted flaps and ailerons with a flat lower surface, symmetrical with respect to the diametrical plane of an ekranoplane, a lower low-lying wing of small elongation with a flat lower surface, rectangular in plan with flaps and side washers in the form of displacement skeg floats, while the distance between the upper and lower wings in height is greater than the chord of the upper wing, vertical and horizontal horizontal tail, marching engines, control system (RU No. 2078002 C1, 6 B 60 V 1/8, published. 04/27/97, bull. No. 12).

This ekranoplan has reduced performance.

The technical result from the implementation of this invention is to increase the technical characteristics of the known ekranoplan. This result is achieved in that the ekranoplane containing the fuselage with the upper wing of large elongation is rectangular in plan with slats, slotted flaps and ailerons with a flat lower surface symmetrical with respect to the diametrical plane of the winged plane, the lower low-lying wing of small elongation with a flat lower surface of rectangular shape in plan with flaps and side washers in the form of displacement skeg floats, while the distance between the upper and lower wings is greater in height than the chord of the upper wings, vertical and horizontal tailings, marching engines, control system according to the invention, thrusting marching engines are made pulling, a third wing is installed in the bow, consisting of two aerodynamic wing-cantilevers having an angle of attack with sweep along the leading edge, with slats and slotted ailerons -flaps made with aerodynamic wings at the ends in the form of vertical plates, the flat lower surface of the lower low wing forms an angle of attack relative to the support oh underlying surface.

The use of an 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 along with the upper wing of large elongation, and the corresponding optimal distribution of the aerodynamic lift in a certain optimal proportion between the front and upper wings of the winged wing and the resulting points of its application (aerodynamic focus, determined from the condition of the stability of the ekranoplan), increasing the increased reliability of the “binding” of the device to the screen, the ability of the winged wing to self-stabilize in height increases and the longitudinal stability during flight on the screen increases compared to the prototype, which allows to reduce takeoff and landing speeds, reduce dynamic loads on both control elements and structurally the power circuit of the apparatus as a whole, thereby allowing to reduce the total weight of the entire structure, allowing to increase the useful weight return of the ekranoplan as a vehicle in comparison with the prototype, also allowing to increase stability and controllability, which means to increase flight safety both on the screen and in transition modes. Based on the analysis of the drawings of the prototype, we can conclude that the relative elongation of the upper wing is about λ> 8.5, the relative elongation of the lower low wing is about λ = 1. Using the third aerodynamic wing in the bow for this arrangement allows to reduce the relative elongation of the upper aerodynamic wing and make it λ <8, increase the relative elongation of the lower low wing and make it λ> 1, thereby further improving the “binding” of the device to the screen, it self-stabilization in height and a further increase in longitudinal stability during flight on the screen, increasing flight safety compared to the prototype, while increasing, as mentioned above, load-bearing properties kranoplana as a vehicle.

Thus, the use of aerodynamic wing-cantilevers in the bow of the winged wing can reduce the relative elongation of the upper wing of a large elongation and make it λ <8, and the lower low-lying screen wing, made with an angle of attack relative to the supporting underlying surface, to perform with a relative elongation λ> 1, thereby allowing you to significantly increase the useful weight return of the ekranoplan as a vehicle, increase stability and controllability, and therefore, increase flight safety on the screen and in transient regimes compared to the prototype.

The invention is illustrated by drawings:

- figure 1 shows an ekranoplane, side view;

- figure 2 is the same, top view,

- figure 3 is the same, front view.

The winged wing contains a fuselage 1, an upper wing 2 of a large elongation of a rectangular shape in plan with slats 3, slotted flaps 4 and ailerons 5, aerodynamic wings in the form of vertical plates 16, a lower low-lying wing 6 of small elongation of a rectangular shape in plan with flaps 7 and side washers in in the form of displacement skeg floats 8, vertical tail 9, horizontal tail 10, mid-flight engines 11, wing-cantilevers in the bow 12 with aerodynamic wings 13 at the ends in the form of vertical plates, pre flaps 14, ailerons-flaps 15, a control system (not shown in the drawings). The flat lower surface of the lower low wing is made with an angle of attack relative to the supporting underlying surface.

The run of an ekranoplan during its operation is usually performed against the wind with small directional angles to the wave front and begins by transferring the engines to the maximum operating mode, similar to the prototype.

At the beginning of the movement, water-side skeg floats 8 are in contact with water, and then, as the speed of the ekranoplan movement increases under the influence of the incoming air flow on the lower wing 6, the upper wing 2 is of great elongation, the front wings 12 generate aerodynamic lifting force, under the influence of which the ekranoplan detached from the surface of the water and continues flying in cruising mode of movement with marching engines operating. The ekranoplan landing is carried out on the water surface by transferring the engines to the low-throttle flight mode with the flaps lower 6, upper 2, front wings-consoles 12 released. Engines 11 and units, mechanisms and equipment not shown in the drawings are selected from serial aviation products that provide specified operating modes ekranoplan. Comparing the technical and economic characteristics of the developed ekranoplan with similar characteristics of the prototype, we can conclude that the distinguishing features of the claimed invention, namely:

- the use of pulling engines instead of pushing ones allows to improve blowing of the upper wing 2, and to increase the aerodynamic lifting force of this wing;

- the use of aerodynamic wing-cantilevers in the bow of the winged wing can reduce the relative elongation of the upper wing 2, and make it λ <8;

- the lower low-wing screen wing, made with an angle of attack relative to the supporting underlying surface, is performed with a relative elongation λ> 1, thereby allowing to significantly increase the effective weight return of the winged craft as a vehicle, increase stability and controllability, and therefore, increase flight safety on the screen and in transient conditions compared to the prototype.

The aerodynamic wings of the console 12 in the bow also allow you to increase the overall aerodynamic lifting force of the entire apparatus and reduce take-off and landing speeds, thereby allowing to reduce the dead weight of the entire structure and, as a result, increase the useful weight return of the ekranoplan as a vehicle and together give an ekranoplan new properties and provide him with advantages in the technical, economic and environmental aspects, namely: in the reliability of the design, functional simplicity and especially in national aerodynamic layout, providing reliable and sufficient “binding” of the device to the screen due to both the lower wing changed compared to the prototype, and due to the additional control action from the wings of the consoles in the bow, which increases the stability and controllability of the winged aircraft in flight, making it possible to successfully complete speed maneuvers, changes in the direction of movement necessary for the safe passage of narrowness and turns of rivers, congestion of ships, bridges, etc.

The technical appearance and appearance of the proposed ekranoplan are formed as a new type of 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 and lake conditions - for the quick delivery of passengers and goods from one region to another, as well as for changing shifts, etc.

The results of research and testing in wind tunnels, on a towed model, made it possible to carry out computational optimization of the main parameters and characteristics of systems, units 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 screen flight.

Claims (2)

1. An ekranoplane containing a fuselage with an upper wing of large elongation of a rectangular shape in plan with slats, slotted flaps and ailerons with a flat lower surface symmetrical with respect to the diametrical plane of an ekranoplan, a lower low-lying wing of small elongation with a flat lower surface of a rectangular shape in plan with flaps and side washers in the form of displacement skeg floats, while the distance between the upper and lower wings in height is greater than the chord of the upper wing, vertical and horizontal empennage, marching engines, control system, characterized in that the marching engines are pulling, in the bow of the winged wing there is a third wing, consisting of two aerodynamic wing-cantilevers having an angle of attack, with sweep along the leading edge, with slats and with aileron flaps made with aerodynamic wings at the ends in the form of vertical plates. 2. Wing according to claim 1, characterized in that the upper wing of a large rectangular elongation in plan is made with aerodynamic wings at the ends in the form of vertical plates and an extension of λ <8, the lower low-lying wing of small rectangular elongation in plan with a flat lower surface is made with lengthening λ> 1, and the flat lower surface of the lower low wing has an angle of attack with a supporting underlying surface.

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