RU2532658C2 - Ram wing sea plane - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: sea plane comprises airframe composed of bearing airfoil with central part with payload space and passenger cabins and freight compartments, starting-landing device, tail unit, power plants, control system and second composite airfoil arranged above bearing airfoil. Sea plane features tandem configuration whereat front and rear wings are bearing components. front baffle bearing airfoil is configured to "inverse gull-wing" on rear view. On top view, it is trapezoidal with minor elongation and relatively large chord, training edge notable sweepforward and Stocks rams. This wing is designed in integral stepwise combined configuration. Second airfoil is flat on front view with V-shape and positive sweep on top view. It is shifted relative to front ram airfoil and arranged in height above airframes at tail unit larger than second airfoil chord relative to bearing underlying surface. It features positive angle of attack, incorporates elevators with wings at ends composed of horizontal aerodynamic plates. Additionally, it is equipped with detachable wing parts with aileron elevators. Starting-landing device incorporates extra retractable/releasable skis.

EFFECT: better aerodynamics, increased payload.

2 cl, 22 dwg, 2 tbl

Description

The invention relates to aircraft and relates to the creation of aircraft using the screen effect.

Known ekranolet (see RF patent No. 2185979, IPC B60V 1/08, s.16.03.1998), consisting of a housing with a tail unit and a wing of small elongation, over which one or more engines with a propeller are installed, characterized in that the side and the trailing edges of the wing are located in a single plane, and the ribs of the wing, paired with the sides of the winged hull, are set at an angle of 5-16 ° to the specified plane, the domed shape is set on the bottom surface of the wing, in addition, the trailing and lateral edges of the wing are made of flexible reinforced material and form flexible air cushion guard, propellers are located above the wing, in front of the plane of rotation of the screw, the wing surface is lowered below the end of the blade of the screw and extends beyond the plane of rotation of the screw, forming an annular channel in front of the screw.

The known aircraft (ekranolet) has insufficient lift and insufficient aerodynamic qualities to perform airplane mode at high altitude and insufficient lateral and longitudinal controllability during climb and departure from the on-screen flight mode.

The closest in technical essence to the claimed technical solution is an ekranoplane (see RF patent No. 2273572, IPC B60V 1/08, s.15.04.2004) containing a body in the form of an aerodynamic supporting wing containing a central part in the form of a low-lying body - wing with useful volume and passenger compartments and cargo compartments, a launch and landing device with a fan unit for creating an air cushion, horizontal and vertical tail and a marching power unit, control system, contains a second aerodynam an integrated wing, consisting of a central part having an angle of attack, with slats, with aileron flaps, located above the winged winged wing - a low wing body in its tail section, and two gull-type aerodynamic wing-consoles located at a height exceeding their chord relative to the underlying underlying surface, having an angle of attack, with sweep along the leading edge, with slats, with aileron flaps, with wings at the ends in the form of vertical aerodynamic plates tin, and in the bow of the supporting wing of the winged wing - the low-lying wing-body - a third wing is installed, located at a height exceeding its chord relative to the supporting underlying surface, made integral and consisting of a central part having an angle of attack, with slats, with aileron flaps and aerodynamic wing-cantilevers having an angle of attack, with sweep along the leading edge, with slats, with aileron-flaps, with wings at the ends in the form of vertical aerodynamic plates.

The known aircraft (ekranoplan) has insufficient lift and insufficient aerodynamic qualities to perform airplane mode at high altitude, and insufficient lateral and longitudinal controllability during climb and departure from the on-screen flight mode.

The problem to which the technical solution under consideration is directed is to develop an aircraft using the screen effect, with high aerodynamic qualities, with reduced energy costs when moving the device on screen mode and at the same time with a significantly increased payload carried by the device.

The problem is solved due to the fact that the seaplane with a screen effect contains a body in the form of an aerodynamic load-bearing wing containing a central part with a useful volume - passenger cabins and cargo compartments, launch and landing device, vertical tail, power plants, control system (not shown) , the second aerodynamic wing, made integral and located behind and above the bearing wing. The seaplane is made according to the tandem scheme, in which both the front and rear wings are load-bearing (i.e., with a positive angle of attack), with the separation of the functions of creating lift to the front - in the on-screen flight mode, and the rear - in the airplane flight mode.

The front screen aerodynamic carrier wing is made when viewed from the front according to the “reverse gull” pattern, when viewed from above, it is trapezoidal with small elongation and relatively large chord, with a large backward sweep of the trailing edge, with Stokes shields installed (not visible in the drawing), designed according to the integral , step, combined scheme, the second aerodynamic wing when viewed from the front is flat with zero V-shaped and positive sweep when viewed from above, shifted back relative to the front screen a non-planar aerodynamic carrier wing and is located at a height significantly higher than the fuselage bodies, on a vertical tail that exceeds the chord of the second wing relative to the supporting underlying surface, having a positive angle of attack, with elevators, with wings at the ends, in the form of horizontal aerodynamic plates, is additionally equipped with detachable wing parts with aileron elevators.

The launching and landing device is additionally equipped with hydro-skis that are let out and retracted during the flight; there are no wheeled chassis in heavy-duty vehicles, while there are hydro-skis, which can significantly improve the take-off and landing characteristics of the device.

In heavy vehicles, start-marching engines are additionally used, the front part of the apparatus is made as a set of a package of start-marching power plants arranged in a single horizontal cowling of engines (which is not the third wing), the thrust vector of which at the time of launch is directed to the underlying surface under the center section of the first screen wing to increase the relative pressure under the wing, and in cruise flight the thrust vector changes and is directed above the upper surface of the front screen cetroplane Nogo wing to increase the flow rate above the wing, which increases the negative pressure above the wing.

The performance of the seaplane according to the tandem scheme, in which both the front and rear wings are load-bearing (i.e., with a positive angle of attack), allows you to increase the lift both in the screen mode - to a greater extent due to the load-bearing front wing and in airplane mode - due to a greater degree of the supporting rear wing. This increases the stability and controllability of the seaplane. When the aircraft leaves the screen mode (when climbing), the focus of the aircraft shifts forward, and it is on the rear wing, due to the positive deviation of the elevators and flaps of the rear wing, creating a large lift force of the rear wing, due to which the focus returns to its place, increasing stability seaplane in transition mode, which allows this unit to easily switch from screen mode to airplane and vice versa. Thus, the tandem scheme allows you to freely make the transition from screen mode to airplane and vice versa.

The implementation of the front screen aerodynamic carrier wing, when viewed from the front according to the "reverse gull", when viewed from above - trapezoidal with small elongation and relatively large chord, with a large reverse sweep of the trailing edge, with installed Stokes flaps, which are signs of an integrated circuit, the effect " inverted funnel ”, which allows you to focus the main lifting force on-screen to the axis of the aircraft and increases the carrying capacity of the aircraft.

The front screen aerodynamic carrier wing is designed to create the main lifting force and increase the aerodynamic quality, and therefore, reduce the necessary traction when moving this unit on the screen flight mode. This means that it leads to a reduction in energy consumption.

The implementation of the front screen aerodynamic supporting wing in an integrated, stepwise, combined scheme ensures the creation of several inductive vortices with a low-pressure region along the axis of the vortex, which significantly (up to 40%) increases the load-bearing properties of the device at large angles of attack (during take-off and landing), which significantly improves the take-off and landing characteristics of the device as a whole and enables the device to lift a significantly larger payload.

The second aerodynamic wing, when viewed from the front, is flat with zero V-shape and positive sweep when viewed from above, is shifted back relative to the front winged aerodynamic carrier wing and is located at a height significantly higher than the fuselage bodies, on a vertical tail that exceeds the chord of the second wing relative to the supporting underlying surface having a positive angle of attack, with elevators, with wings at the ends, in the form of horizontal aerodynamic plates, is additionally equipped temnymi parts wing with ailerons, elevators.

The implementation of the second aerodynamic wing displaced backward relative to the front winged aerodynamic bearing wing and located at a height significantly higher than the fuselage bodies, on a vertical tail that exceeds the chord of the second wing relative to the supporting underlying surface, having a positive angle of attack with elevators and flaps, allows you to create a significant part of the lifting power and perform flight of the device both on screen and in airplane modes with high stability and controllability.

The implementation of the second aerodynamic wing equipped with detachable parts of the wing with wings at the ends in the form of horizontal aerodynamic plates allows you to get a large-scale wing with high aerodynamic characteristics, which in turn allows you to perform airplane flight mode and winged flight mode with high aerodynamic characteristics [long flight range ( up to 15,000 km), high cruising flight speed (up to 550 km / h), very large payload exceeding the empty weight of the aircraft itself ].

The implementation of the second aerodynamic wing with elevator elevators allows you to provide more longitudinal and lateral controllability, aileron rudders are designed to increase lift in airplane flight mode.

Implementation of a launching and landing device with hydro-skis discharged and retracted during flight can significantly reduce the hydrodynamic resistance of the apparatus as a whole when taking off from water in the planing mode on the water, the chassis (for landing on a hard surface) is discharged from the hydro-ski. At the same time, hydraulic skis absorb shock, reduce energy consumption at the time of starting from the water.

Use in heavy vehicles of additional starting and marching engines arranged in a single horizontal cowl (not the third wing), the thrust vector of which at the time of launch is directed under the center wing of the first screen wing, and in cruising flight the thrust vector changes and is directed above the upper surface of the front screen center wing wings. The starting-marching engine package is made in the form of a horizontal set of starting-marching power plants in the front of the device, the starting-marching engines are made with a variable thrust vector, each to increase pressure under the lower surfaces of the center wing and under the main planes of the wings.

All of them are necessary to increase the screen effect by increasing the gas pressure under the wings at the time of launch.

The drawings show:

Figa - seaplane (AL-20), front view.

Figb - seaplane (AL-20), side view.

Figv - seaplane (AL-20), top view.

Figa - heavy seaplane (AL-30), front view.

Fig.2B - heavy seaplane (AL-30), side view.

Figv - heavy seaplane (AL-30), top view.

Figa - heavy seaplane (AL-40), front view.

Fig.3B - heavy seaplane (AL-40), side view.

Figv - heavy seaplane (AL-40), top view.

Figa - heavy seaplane (AL-50), front view.

Figb - heavy seaplane (AL-50), side view.

Figv - heavy seaplane (AL-50), top view.

Figa - heavy seaplane (AL-1300), front view.

Fig.5B - heavy seaplane (AL-1300), side view.

Figv - heavy seaplane (AL -1300), top view.

Figa - heavy seaplane (AL-2600), front view.

Fig.6B - heavy seaplane (AL-2600), side view.

Figv - heavy seaplane (AL-2600), top view.

Figa - heavy seaplane (AL-3400), front view.

Figb - heavy seaplane (AL-3400), side view.

Figv - heavy seaplane (AL-3400), top view.

Fig. 8 is a schematic illustration of the nature of the appearance of inductive coupled vortex flows formed above the upper surface of the wings of a seaplane with a screen effect, designed on the basis of an integrated-step plan of the configuration of the plan view wings.

Seaplane contains:

1. The body-fuselage of the center section of the first aerodynamic carrier wing;

- 1a - two hulls of the fuselage of a catamaran type boat;

- 1b - external trapezoidal center wing;

- 1c - slats;

- 1g - detachable part of the console;

- 1d - wings;

- 1e - aileron;

2. Starting power plants;

3. Launch and landing device;

4. Vertical plumage;

5. Marching power plants;

6. The second aerodynamic wing;

- 6a - the Central part of the second aerodynamic wing;

- 6b - detachable part of the console;

- 6c - aileron elevator;

- 6g - slats;

- 6d - wings.

7. Starting marching engines on a heavy aircraft;

8. The fairing.

The seaplane with a screen effect is a tandem sequential biplane with three transversely spaced, parallel fuselages 1, 1a inscribed in a long chord, the center wing of the main trapezoidal wing (1-1e).

The middle fuselage (1a) below the bottom is not solid, but breaks into the front and rear bottoms (not shown). It is made higher on the base of the bottom of the extreme two fuselages, as a result of which it does not touch the water during calm sea waves, therefore it does not create additional hydrodynamic resistance. But if strong sea waves rise and the waves reach the bottom of the middle fuselage, then the middle fuselage begins to stabilize the movement of the seaplane in the longitudinal direction, increasing stability, due to its displacement. Thereby, the amplitude of the oscillation of the heaving from sea waves decreases. All of this, on the whole, will significantly lead to an improvement in seaworthiness, stability, and to a significant decrease in the hydrodynamic drag of ekranoplanes at the time of launch and with a displacement regime of navigation at low speeds.

The middle fuselage 1 is non-waterproof (not reaching the water level), designed to accommodate the main passenger and cargo compartment. The side fuselages - boats 1a - are displacement, made according to the catamaran scheme, they limit the center section from inductive flow and close the power hydrodynamic and aerodynamic scheme of the device, which gives a decrease in inductive resistance and a significant gain in the bearing properties of the device. Such a tandem power scheme of an aircraft allows to optimize and improve aerodynamics and stability of the ekranolet especially in the screen flight mode.

It will allow to unload and evenly distribute all loads from cargo and from air-dynamic, hydrodynamic forces acting on the wings and body of the aircraft. All this, with the large size of the seaplane with a screen effect, will allow the use of a more simplified, and therefore lighter, structural and power frame of the device. This will significantly reduce the weight of the device as a whole. This makes it possible to make the seaplane body more compact, lighter and more durable. At the same time, the manufacturability of automation of loading and unloading operations on these seaplanes will significantly improve. In addition, with this arrangement of the three fuselages with a central center wing, a more rational placement, consolidation and distribution of goods along the bearing surface of the wing and inside the center sections and fuselages is ensured. This will make these aircraft more compact and versatile when transporting a large variety of types and quantities of cargo.

The central center wing (1-1e) stepwise-integrally passes into a set of wings, stepwise tapering and decreasing in area, installation angle of attack and in the size of the chord on each side. This is an integrated step circuit. Due to the use of such a combined integrated stepwise aerodynamic layout, it is possible to most fully obtain the maximum amount of lift with a minimum of drag from the central center section of small elongation and from the main wings at large angles of attack, both in screen mode and in airplane mode.

The main screen wing (1) of this seaplane is trapezoidal with small elongation and relatively large chord. This wing is designed to receive the main lifting force on-screen flight mode. It is designed according to an integrated, stepwise, combined scheme of variable elongation, sweep and narrowing (plan view from above). The surfaces of the tapering center sections have a well-developed front mechanization in the form of slats, and in its rear part it is equipped with a mechanization in the form of a Stokes shield (not shown in the drawing), which significantly increases the load-bearing properties and quality of the whole apparatus as a whole, both during take-off and landing, and on a cruise flight. And the upper back surface of the central center wing is modified from above, that is, profiled in such a way that two (or four) half-rings of the tunnel type are formed along the axis, in which two (three, four) mid-flight propeller-driven power plants are installed (5). These power plants (5) located in half-tunnel channels above the wing profile will significantly increase the load-bearing properties of the central center sections and the entire wing as a whole of all considered seaplanes with a screen effect. The combination of the center section and the detachable parts of the consoles are made, when viewed from the front, according to the scheme "reverse gull" (reverse W-shaped V-shaped). At the ends of the wings are detachable parts of the consoles (1 g) (OCHK) based on the profile P-301M-15, which are attached to the main wing through side one-sided washers-floats. The detachable parts of the consoles (1 g) are effectively mechanized by slats. Target ailerons (1e) are located on the detachable parts of the consoles (1g), which provide lateral stability and controllability in all flight modes.

The tail unit (4) is located in the rear part of the apparatus in the form of three keels of vertical tail unit, at the upper ends of which a second wing of large elongation is attached (6). It is designed to create the main lifting force in airplane flight modes.

In airplane mode, the second wing (6) of large elongation and area will create a significant proportion of the bearing lifting force while maximizing stability and controllability of the seaplane, compensating for the focus moving forward when it moves away from the underlying surface in transition mode.

The inventive seaplanes with a screen effect have a non-standard configuration of their wing contours in plan, made according to an integral-step scheme. The shape of the configuration of the contours of the entire wing as a whole in terms of is based on the principles of vortex aerodynamics arising on the basis of integral step-down contracting wings (as can be seen in Fig. 8) with negative aerodynamic and geometric twists of the wing. Large bearing profiled center section, small elongation with three gliding fuselage-boats inscribed in it, made according to the trimaran scheme.

On Fig it is shown how the central center section 1 stepwise-integrally passes into a set of wings, stepwise tapering and decreasing in area, installation angle of attack and in magnitude of the chord on each side. This is an integrated step circuit. Due to the use of such a combined integrated stepwise aerodynamic layout, an increase in lift is possible with a minimum of drag from the central center section of small elongation and from the main wings at large angles of attack, both in screen mode and in airplane mode.

For seaplanes with a screen effect, all power plants are divided into groups:

1. Power plants - to generate electricity.

2. Marching (5) - cruising type TVD and DTRD, working during the entire flight;

3. Starting (2) on the basis of turbojet engines, working only during the start, and have variable thrust vectors;

4. Marching-starting power plants based on DTRD with a variable thrust vector, each to increase pressure under the lower surfaces of the center wing and under the main planes of the wings. All of them are necessary to increase the effect of the screen by increasing the pressure under the wings at the time of launch (principle of blowing).

As you can see, the claimed seaplanes with a screen effect has very well-developed ending parts of the console 1g in its wing, all of these surfaces have ailerons 1e to increase lateral controllability, especially in airplane mode. The detachable parts of the console 1g are well developed in area, stand at a more negative angle of attack with respect to the center wing 1, and also have a good V-shape, and the large ailerons 1e are able to provide the seaplane with sufficient lateral stability and controllability, both on the screen and on airplane flight modes.

Also, the detachable parts of the 1 g console have a well-developed front mechanization in the form of 1c slats, which significantly increases the load-bearing properties and quality of the entire apparatus as a whole at the time of launch and at cruise screen and airplane flight modes. Released slats 1B increase the coefficient of lift and reduce the installation angle of attack with a stepwise change in the area of the tapering center section 1.

The inductive vortex disengaging from the stage from under the tapering center section 1, the detachable parts of the console 1d directed upward above the subsequent cantilever wing plane, causes an increase in the lift force of the smaller wing set at a more negative angle of attack, and this component of the lift force vector is directed forward.

Therefore, it compensates and translates this “lost vortex energy” into a component of the force vector formed on the subsequent external wing console. It significantly reduces, thereby, the total inductive reactance.

The inventive seaplane with a screen effect is characterized by a fundamentally new hydrodynamics of flow around the bottom contours. This consists in the fact that seaplanes with a screen effect consist of 3 fuselage bodies 1, 1a with three hydro-ski devices (launch and landing device 3), made according to a three-post scheme. Such a scheme, due to the protruding middle fuselage 1, significantly increases stability on the water surface, especially in conditions of strong wave rolling. With the help of a programmable, sequential release of hydro-skiing devices (first the front — longer — central hydro-ski, and then the rear lateral ones, not shown in the drawing) at the start of the take-off, we get a programmable method of lifting “raising” and getting out of the water to the airplane planing mode in the process of his run. The consecutive release (lowering down) of the displacement front ski, and then the rear displacement hydro-ski 3, due to buoyant hydrostatic (Archimedean force) and hydrodynamic forces, will lead to the fact that, accordingly, the sequence of lowering the front and then the main hydro-skis, the main the seaplane body with a screen effect will first raise its nose during acceleration, and then completely come out of the water mirror upwards, and then continue the gliding run on hydro-skis, reducing the hydraulic pressure by an order of magnitude otivlenie bodies of water. This will significantly improve take-off performance and reduce energy consumption during the take-off of the seaplane at the time of launch. In addition, the middle fuselage 1 below the bottom has only the front part, i.e. from below it is interrupted under the center section. Under the center wing there is no middle fuselage. Thereby, two expanding airflow confusers are created under the bottom, which are connected under the center section into one expanded stream, which in turn will lead to an increase in the relative static pressure under the center section and an increase in the bearing lifting force. The use of hydro-skis for launch at the moment of seaplane take-off with a screen effect is so effective and advisable that it gives an increase in the lifting load-bearing force, at the time of launch, higher than all the aerodynamic mechanization of the wing, therefore its use on seaplanes is quite reasonable and advisable.

The inventive seaplanes with a screen effect is an all-weather, highly economical multi-purpose vehicle with non-contact movement above the surface at heights of 1-10 m in the screen mode and above up to 4000 m in the airplane flight mode.

The claimed technical solution covers a series of seaplanes with a screen effect AL: small, medium and large load capacities, the characteristics of which are summarized in the tables below.

The main technical data proposed for the consideration of seaplanes with a screen effect Shield Modification Al-20TVD. Al-30TVD. Al-40TVD. Al-50TVD. Take-off maximum weight, G (tons) twenty thirty 40 fifty Crew (passengers), person 4 (up to 60) 4 (up to 70) 4 (up to 100) 4 (up to 130) Commercial payload, (t) 12 17 24 thirty Engine manufacturer Zaporizhzhya ZMKB Progress Zaporozhskii zavod ZMKB Progress Zaporizhzhya ZMKB Progress Zaporozhskii zavod ZMKB Progress Zaporizhzhya ZMKB Progress GE Honda Zaporozhskii zavod ZMKB Progress GE Honda Zaporizhzhya ZMKB Progress GE Honda Zaporozhskti zavod ZMKB Progress GE Honda 2 × TVD-1500, 3 × TVD-1500, 4 × TVD-1500, - marching: 4 × TVD V601E or V601D or
2xTVD AlliedSignal TRE331-140D-801E, or
3 × TVD AlliedSignal ТРЕ331-140Д-801E, or
4 × TVD AlliedSignal ТР331-140Д-801E, engine's type - starting: + Email Dv or2 TVD General Electric CT7-9B or 2 TVD General Electric CT7-9B or 2 TVD General Electric CT7-9B - APU: AI-450-MC 4 AI-450-MS 4 TVD-HF 120 Honda Turbofan 4TVD-HP 120 Honda Turbofan - marching: 4 * 550 4 * 750 2 * 1500 2 * 1500 Quantity * power, hp / kgf - starting: (or 2 * 1700) (or 2 * 1700) - APU 2 * 500 2 * 500 4 * 800 4 * 800 Fuel reserve, (tons) 5 5 one 6 Flight range, km, at N = 1-3 m 10,000 12000 13000 15,000 Flight range, km, with partial airplane mode. with N more than 3-5m 6000 6000 8000 10,000 Cruising flight speed, km / h 420 420 450 450 Maximum speed V flight, km / h 500 500 550 550 Draft in water drift, m 0.45 0.45 0.45 0.45 Permissible sea waves during take-off / landing, points 3-4 points H3% = 1.5-2 m, 3-4 points H3% = 1.5-2m, 3-4 points H3% = 1.5-2m, 3-4 points H3% = 1.5-2m, Seaworthiness - permissible sea waves during flight, points 6 6 6 6 Taxiing height, m 0.1 ... 0.2 0.1 ... 0.2 0.1 ... 0.2 0.1 ... 0.2

Operating surface at a height of 0-1-5 m water, soil, concrete, snow, ice, broken ice, swamp, meadow, soil water, soil, concrete, snow, ice, broken ice, swamp, meadow, soil water, soil, concrete, snow, ice, broken ice, swamp, meadow, soil water, soil, concrete, snow, ice, broken ice, swamp, meadow, soil Maximum airplane flight ceiling (m) (oxygen goal limitation) 4000 4000 4000 4000 Dimensions: - It is long (m): 29th 38 46 49 - Span (m): 26 36 42 46 - Height (m): 8 8 8.8 9.2 - Area (m ² ): 226 286 313 342 Specific load (kg · m ^2. ): 65/74 65/74 69/81 73/94 Poppy. aerodynamics. quality on (min, P) the most advantageous screen. Mode 35 35 40 42 Poppy. aerodynamics. quality on the screen. cruising flight mode twenty twenty 28 32 Max. Aerodynamics. quality in airplane mode 12 12 17 22 The required total min. required engine thrust for the best screen, dir. flight to naive. V (P = G / K) (kgf) 1667 1967 3690 4720 The required total required thrust of the engine for cruising on-screen flight mode (P = G / K); (kgf) 1950 2150 3250 4150 Minimum required total required engine thrust for an airplane cruising flight mode (P = G / K) (kgf) 2400 2400 4400 5900 Available total thrust (R kgf) of engines at max. dir. work dv. 5250 5250 7700 7700 Available total. traction march. engines on a cruise. dir. work dv. (75% of maxim, total. R dv.) (Kgf) 4187 4187 4500 4500 Thrust ratio P / G (kg / kg) max flight mode / cruise. mode. flight. 0.195 / 0.105 0.195 / 0.105 0.26 / 0.195 0.36 / 0.365

Shield Modification Al-1300. Al-2600 Al-3400. Take-off maximum weight, G (tons) 1 1300 2400 34000 Crew (passengers), person 8 (up to 1200) 14 (up to 2600) 14 (up to 3400) Commercial payload, (t) 1300 2600 3400 Number of Eurocontainers: 40 ft. + 20 ft. (Pcs.) volume 11 + 11 24 + 11 26 + 12 Engine manufacturer Zaporizhzhya zd and ZMKB "Progress" Zaporizhzhya zd and ZMKB "Progress" Zaporizhzhya zd and ZMKB "Progress" - marching: D-27 D-27 D-27 engine's type AI-436T12 AI-436T12 AI-436T12 - starting: RD-33MK AL-31FN AL-31FN - APU: AI-450-MS AI-450-MS AI-450-MS - marching: 2 * 14000 8 * 14000 10 * 14000 Quantity * power, hp / kgf 6 * 12000 8 * 12000 8 * 12000 - starting: 6 * 9000 6 * 12700 6 * 12700 -VSU: 2 * 500 4 * 500 4 * 500 Fuel supply, t 160 300 500 Flight range, km, at an altitude of 1-3 m 15,000 15,000 20000 Flight range, km, with partial i airplane mode. With N more than 3-5 m 10,000 10,000 14000 Cruising flight speed, km / h 540 540 550 Maximum flight speed, km / h 600 600 600 Draft in water drift, m 1.45 2 3 Permissible sea waves during take-off landing points; 4-5 points H3% = 2.5-3 m, 6-7 points H3% = 3.5-4m, 7-8 points H3% = 4.5-6 m, Seaworthiness - permissible sea waves during flight, points not limited not limited not limited Taxiing height, m 1 ... 2 2 ... 3 3 ... 4 Operating surface at a height of 0-1-5 m water, snow, ice, broken ice, swamp, meadow, soil, etc. water, snow, ice, broken ice, swamp, meadow, soil, etc. water, snow, ice, broken ice, swamp, meadow, soil, etc. Maximum flight ceiling in airplane mode (m) j 4000 4000 4000 Dimensions: - It is long (m): 70 116 126 - Span (m): 62 98 108 - Height (m): fourteen 21 21 - Area (m ² ): 1308 3900 5300 Specific load (kg · m ^2. ): 75/84 611/764 691/794

Poppy. aerodynamics, quality at (min P) best screen, mode 60 i 80 90 Poppy. aerodynamics, screen quality, cruising flight mode 39 ^ 47 53 Max. aerodynamics, airplane quality fifteen eighteen 19 The required total min. required thrust of engines for the best screen. dir. flight to naive. V (P = G / K) (kgf) 80,000 15,000 180,000 The required total required thrust of the engine for cruising screen flight mode (P = G / K) (kgf) 120,000 170000 22000 Minimum required total required engine thrust for an airplane cruising flight mode (P = G / K) (kgf) 120,000 160,000 2,900,000 Available total thrust (R kgf) of engines at max. dir. work dv. 160,000 200,000 300,000 Available total. traction march. engines; to the cruise. dir. work dv. (75% of the max. Total. R dv.) (Kgf) 120,000 160,000 230,000 Thrust ratio P / G (kg / kg) max flight mode / cruise. flight mode. 0.185 / 0.085 0.17 / 0.075 0.16 / 0.07

The use of the inventive seaplane with a screen effect makes it possible to combine the quality of an ekranoplan in one device with significant savings in energy consumption for cruising at low altitude and the high quality of the aircraft if it is necessary to reach a high altitude to overcome ground obstacles.

Claims (2)

1. A seaplane with a screen effect, comprising a body in the form of an aerodynamic load-bearing wing, containing a central part with a useful volume and passenger compartments and cargo compartments, a launch and landing device, vertical tail, power plants, a control system, and a second aerodynamic wing, made integral and located above the carrier wing, characterized in that it is made in tandem pattern, in which both the front and rear wings are carrier (with a positive angle of attack), the front screen air the namic supporting wing is made when viewed from the front according to the “reverse gull” pattern, when viewed from above, it is trapezoidal with small elongation and relatively large chord, with large reverse sweep of the trailing edge, with Stokes shields installed, designed according to an integrated, stepwise, combined scheme, the second aerodynamic when viewed from the front, the wing is flat with zero V-shape and positive sweep when viewed from above, shifted back relative to the front winged aerodynamic carrier wing and is located at a height significantly higher than the fuselage bodies, on a vertical tail that exceeds the chord of the second wing relative to the supporting underlying surface, having a positive angle of attack, with elevators, with wings at the ends, in the form of horizontal aerodynamic plates, is additionally equipped with detachable wing parts with ailerons - elevators, the launch and landing device is additionally equipped with hydro-skis that are let out and cleaned in flight. 2. A seaplane with a screen effect according to claim 1, characterized in that in heavy vehicles additionally use start-marching engines, and the front of the device is made in the form of a set of a package of start-marching power plants arranged in a single horizontal cowl.

Images