RU2786118C1 - Ground-effect plane - Google Patents

Abstract

FIELD: aircraft.

SUBSTANCE: invention relates to aircraft using the energy of the airflow, the lift of the wing, and the ground effect. The ground-effect plane is characterised by consisting of a catamaran with two fuselages, wherein a horizontal aerodynamic wing is mounted along said fuselages on supports at a height of 1.6 m to the entire length of the fuselages and with a width of 2 m. Two propulsion units are installed under the wing on the fuselages: one in the nose, the other in the stern. A vertical plane is secured on each wing side.

EFFECT: increase in the reliability, speed, and loading capacity.

9 cl, 9 dwg

Description

The field of technology.

The technical solution relates to vehicles, in particular to aircraft, airplanes and ekranoplanes, ekranoplans using the energy of the air flow, wing lift, and the ground effect. The technical solution can work as a snowmobile or a boat. It is intended for performance of search and rescue operations, rendering honey. assistance in the Ministry of Emergency Situations and the Armed Forces. It can work in all climatic zones of Russia, in winter, summer, on water and snow.

The level of technology.

From the prior art, for example A.N. Panchenkov, P.T. Drachev, V.I. Lyubimov. Examination of ekranoplanes: N.Novgorod, 2006, it is known that ekranoplanes (or their variety ekranoplanes) have significant advantages over other modes of transport. It is known that the transportation of goods by ekranoplanes is 30% more economical than by cars, four times more profitable than by airplanes and seven times more economical than by helicopters. There are several serial working ekranoplans.

Of the existing devices of this type, the very successful ESKA-1 device (https://topwar.ru/22683-eksperimentalny-ekranoplan-eska-1.html) published in the MK magazine for 1983 No. 4 is known, which was designed and manufactured by highly qualified engineers from inexpensive and available materials. The disadvantages of ESKA-1 include a small carrying capacity, the presence of one engine reduces the reliability of the device.

Of the existing and in operation hovercraft SVPs have a powerful lifting engine, and therefore high fuel consumption, which limits work away from bases, low speed.

The closest to the claimed technical solution could include snowmobiles of various designs, but they also have different disadvantages, it makes no sense to list them.

Ekranolet devices are known, for example, Belavin N.I. "Screenshots." P .: Shipbuilding, 1968 and A.N. Panchenkov, P.T. Drachev, V.I. Lyubimov. Examination of ekranolet: Nizhny Novgorod, 2006. There are several types of serial ekranolet operated in different countries.

The disadvantage of the above design solutions is the impossibility of continuing the flight in case of failure of any engine for a twin-engine ekranolet with transverse engines.

Known ekranolet (patent RU 2747322). The ekranolet contains a V-shaped fuselage with a cabin inside, wings equipped with ailerons and stabilizers with rudders for air, as well as jet engines are located in the rear fuselage. In this case, the stabilizers are attached to the ends of the fuselage and are equipped with additional rudders for water. The wings are located between the ends of the fuselage and form a single rear wing, which is attached from above to the stabilizers in the rear fuselage. At the same time, the peripheral parts of the rear wing with ailerons are additionally attached to the tail parts of the fuselage with the help of two struts, and jet engines are fixed on the central part of the rear wing, which is pivotable in the vertical plane. In the front part of the fuselage there is a girdle with a wing profile in the lower part, and in the rear part from the sides of the stabilizers there are sponsons for a smooth entry into the water surface, and the girdle wing is mechanically connected to a hydraulic cylinder installed inside and at the beginning of the V-shaped fuselage.

Disadvantages include low carrying capacity and the use of jet engines with high fuel consumption, requiring a large supply of fuel, which limits operation away from bases.

Ekranoplan is known according to the "Duck" scheme (patent RU 2550568). It contains a fuselage with a cockpit, in front of which a horizontal tail is installed, in the aft part a small aspect ratio wing and a vertical tail with a rudder, two engines with superchargers. The fuselage contains two cockpits located on the sides of the center section uniting them, in the bow of which the emergency controlled surface is movably fixed by means of a drive. The inner walls of the cockpits and the upper skin of the center section form a chute with coaxially placed bow and stern superchargers of the working flow. Behind the bow supercharger, horizontal rotary flaps are introduced, equipped with a rotary mechanism, made with the possibility of communicating a part of the working flow with the channel. The channel is introduced between the upper and lower skins of the center section, in which, in the plane of the lower skin, blinds equipped with a rotary mechanism are movably installed. EFFECT: increased flight safety, improved aerodynamic quality of the ekranoplan.

The disadvantage of the ekranoplan is that only the power of the front engine is used to create an air cushion blower, i.e. the air flow may be insufficient to lift the ekranolet from the surface, which requires the installation of three doors to provide the necessary air flow for boost, the complex design of the propeller groups in two separate annular channels, the complex design of the box tail.

Known ekranolet (patent RU 2612067). The ekranolet contains two fuselages united by a common bottom, with engines in each fuselage, with screws in the annular channels and a transmission from each engine, as well as a rotary flap, a box-shaped tail. In this case, the engines each have their own transmission, united by a gearbox of a common bushing of coaxial propellers in a single annular channel.

The disadvantages include a small carrying capacity, engines are placed in each fuselage, which reduce the free (operated for cargo transportation) volume of the fuselage.

Analogues do not provide effective use of the ground effect, which directly affects the retention of the device in the air and, as a result, have an increased resistance to movement, which means a decrease in carrying capacity, speed, or an increase in fuel consumption. The location and design of the aerodynamic wing in analogues does not allow to effectively create aerodynamic lift, the energy of the oncoming flow is not used efficiently. The location of propeller installations, the design of the drive reduce the carrying capacity, and other operational characteristics of ekranoplanes.

The essence of the technical solution.

The technical solution provides for the expansion of the arsenal of technical means, ekranoletov. Provides increased efficiency in the use of airflow energy, wing lift, and ground effect for movement. EFFECT: increased efficiency of using the ground effect, keeping the apparatus in the air, reducing resistance during movement, which means an increase in carrying capacity, speed or a decrease in fuel consumption. The flow exit from under the wing to its side surfaces is limited, which increases the efficiency of using the energy of the oncoming air flow. The location of the propeller units (VMU) and the oncoming flow add up to increased pressure under the wing. When the speed of the ekranolet changes from gliding to flight, the bottom surface and platform - wing are switched on. The total air flow consists of the oncoming flow and the flow from the two propellers under the wing. A significant lifting force is created. Upon reaching a speed of about 80 km / h, the ekranolet breaks away from the surface, the flight begins. The use of two VMUs located under the wing significantly increases the reliability of the ekranolet.

The technical result is achieved by the fact that the ekranolet consists of a catamaran with two fuselages (6 m long), an air wing is mounted above the catamaran on supports at a height of 1.6 m for the entire length of the fuselages 2 m wide (wing area S is about 12 sq. m. ). Under the wing, on the fuselages, two propeller-driven installations (VMU) are installed, one in the nose, the other in the stern, restrictive planes are fixed to the side of the wing.

The use of two VMUs under the wing significantly increases the reliability of the ekranolet.

In emergency situations on the water, it is possible to use the R-30÷40 kW outboard engine.

The use of the ground effect, as a natural phenomenon, affects the retention of the device in the air and, as a result, an increase in speed, carrying capacity and fuel economy.

It is envisaged that, with the appropriate equipment, it can operate in unmanned mode.

The invention is illustrated by graphic materials:

Fig. 1 - General view, side projection.

Designations: 45 - striving apparatus; 1 - platform-wing; 2 - screw hub; 3 - bearings P 1-2; 4 - reducer; 5 - foundation of the engine and gearbox; 6 - steering wheel axis; 7 - trim plate; 8 - thrust bearing 0-1-2; 9 - lower edge of the side vertical surface. Symbols: P-1-2 - bearings; B-1-2 - screws; F-1-2 - fuselages; D-1-2 - engines; K-1-4 - cockpit; B-1-4 - fuel tanks; R-1-2 - horizontal rudders; KG - horizontal wing.

Fig. 2 - General view projection from above.

Designations: 45 - striving apparatus; 10 (1-11-2-12) wing supports; 2 - connecting flange; 4 - reducer D-1, D-2; 5 - foundation of the engine and gearbox; 6 - steering wheel axis; 7 - trim plate; 9 - bypass pipes; 11 - chipper lion. right; 12 - couplings; 13 - lateral vertical planes;

Symbols: P-1-2 - bearings; B-1-2 - screws; F-1-2 - fuselages; D-1-2 - engines; K-1-4 - cockpit; B-1-4 fuel tanks; R-1-2 - horizontal rudders; KG - horizontal wing.

Fig. 3 - General view projection from the front.

Designations: 1 - platform-wing; 2 - screw hub; 13 - bearing assembly brackets; 14 - slan; 15 - gaskets (felt, plywood); 16-brackets-bottom; 17 - blade; 18 - skis (pine, stainless steel); 19 - bottom; Symbols: KG - horizontal wing; B-1 screw #1; PVL - vertical left plane; PVP-plane vertical right; F-1-2-fuselages; D-1-2 - engines; K-1-4 - cockpit; B-1-4 fuel tanks.

Fig. 4 - Left fuselage (F-left). Designations: 1 - platform wing; 18 - stainless steel strip. 6000 * 120 * 0.6; 11 - chipper; 20 - stringers 6000*80*15 (pine); 21 - kerchief 3-sided; 18 - skis 6000*120*15 (pine); 19 - bottom; 22 - side surface D-16; 10 - wing support; 1-1 frame frame D16

Fig. 5 - Screw hub. Designations: 17 - blade; 23 - hole F10.2; 24 - blade base; 26 - rib; 30 - square 105*150*4; 31 - shaft Ф100; st.; 32 - key; 33 - cross.

Fig. 6 - Flight control scheme. Designations: 34 - talpers 2 pcs.; 35 - transverse rods; 36 - pulley Ф250 2 pcs. Al; 37 - cable; 38 - roller; 39 - clip. 40 - bearing 80201; 41 testolite gasket 2 pcs.; 42 - washer; 44 - axis, pin.

Fig. 7 - Blade. Designations: 17- blade; 23-hole 10.2mm 4 pcs; 24- blade bases; 25-seam welding; 26 - rib.

Fig. 8 - The base of the blade. Designations:; 23 - hole Ф 10.2mm 4 pcs.; 23 - hole 10.2mm 4 pcs.; 24 - blade bases; 25 - welding seam; 26 - rib; 27 - axle, bolt m10; 28 - section of the blade; 29 - groove.

Fig. 9 - Rudder. Straightening device. Designations: 6 - steering wheel axis; 7 - trim plate; 45 - striving apparatus; 51 - plug; 52 - bushing; 53 - rib; 54 horizontal jumpers; 55 - racks.

Device implementation

Vehicle. Ekranolet.

The technical solution relates to aircraft, airplanes and ekranolet, using the energy of the air flow from the propeller, the lift of the wing and the screen effect of movement near the surface. Increased load capacity and reliability of the device.

Ekranolet (figure 1; 2; 3) consists of a catamaran, with two fuselages, (length L= 6 m), above the catamaran on supports at a height of 1.6 m mounted wing for the entire length of the fuselage width of 2 m (wing area S of about 12 sq. m.). Under the wing, on the fuselages, two propeller-driven installations (VMU) are installed, one in the nose, the other in the stern, restrictive planes are fixed to the side of the wing.

The total air flow consists of the incoming and two propellers under the wing. A significant lifting force is created. Upon reaching a speed of about 80 km / h, the ekranolet breaks away from the surface, the flight begins.

The use of two VMUs under the wing significantly increases the reliability of the ekranolet.

In emergency situations on the water, it is possible to use the R-30÷40 kW outboard engine. The use of the ground effect, as a natural phenomenon, affects the retention of the device in the air and, as a result, an increase in speed, carrying capacity and fuel economy.

The design provides:

1. Maximum - the possible use of the screen effect - a natural phenomenon - directly affecting the retention of the apparatus in the air and, as a result, a decrease in resistance during movement, which means an increase in carrying capacity, speed or a decrease in fuel consumption.

Fig. 2. The location of the horizontal aerodynamic wing KG (drawing, Fig. 1) along the fuselages of the catamaran Ф⋅1 Ф⋅2 for their entire length at a height of 1600 mm.

3. To limit the exit of the flow from under the wing to its side surfaces, two vertical planes are fixed (Fig. 3 pos. PVP and PVL) for the entire length of the wing.

4. Two VMUs (propeller installations) are installed between the fuselages under the wing, in series. One in the bow, the other in the stern. Such an arrangement of the VMF and plus the oncoming flow give in total an increased pressure under the wing. The difference in pressure across the surfaces of the wing creates lift.

5. When the speed of the ekranolet changes from gliding to flight, the bottom surface (Fig. 3, pos. 19) and the platform - wing (pos. 1 of Fig. 3) are switched on.

With the appropriate equipment, it can operate in unmanned mode.

The ekranolet consists of the following nodes:

1. Wing KG. Avia. Dimensions: L-6000, b - 2 m. Attached to the fuselage with supports 1⋅11 and 2⋅12 (Fig. 2, pos. 10), brackets of the bearing unit (pos. 13, fig. 3). Straightener supports (pos. 45, Fig. 2), Rudder axles Р⋅1, Р⋅2 (Fig. 2). On both sides of the wing, the side planes of the HDL and HDL are fixed on supports 1⋅11 and 2⋅12 to the level of the top of the cabins K⋅1⋅4. For the exit of the propeller blades B⋅2, a transverse cutout is arranged in the wing (Fig. 1, item B-2).

2. VMU - Propeller installation - 2 pcs.: consists of a gasoline engine. Р-50÷60 kW, 3000 rpm, reducer (L⋅1, pos. 4) belt, chain or spur gears.

Bearing unit - 2 rad stop and spherical 2 row (item 3, L⋅1). Attached to the fuselages Ф⋅1 and 2 by braces 13 L⋅3 and vertical to the lower surface of the wing.

Fastening of motors, gearboxes, brackets of the bearing assembly are mounted through shock-absorbing pads.

Propellers - В⋅1, В⋅2 4-bladed ∅ 2000 at max speed up to 1300 rpm, duralumin.

Screw hub (Fig. 5). Consisting of a hollow shaft ∅ 100 mm (pos. 31), a cross-shaped welding insert pos. 33. A square pipe 105x150x4 in size is installed on the shaft (item 3, pos. 30). 4 dowels 32 are inserted diametrically into the cutouts of the pipe. 4 blades are bolted to each side of the square pipe (Fig. 7). The blade (pos. 17) is welded to the base (pos. 24, fig. 8). The base has a certain angle of rotation on the axial bolt (pos 27). After test runs, all bolts are fixed.

Fuselages Ф⋅1, Ф⋅2: l-6000, h - 1000, b - 700. The nose of the fuselages is beveled at an angle of 45°. From above, the fuselages are interconnected by a platform-wing (pos. 1 of Fig. 1), which serves to service the B⋅1 propeller and as a wing during flight. From the bottom of the fuselages there are four skis (Fig. 4, item 18) and stainless steel strips. Steel. Fixed with hidden bolts through the scarves to the frames pos. 1⋅1. The strips protect the fuselage from hitting the surface and for sliding. Inside the fuselages, frame frames are installed (Fig. 4, pos 1⋅1) welded together along the edges of 80 mm. All connections of frames with sheathing, skis, stringers, the bottom are connected by scarves on 2 or 3 planes.

To connect the fuselages, the foundations of the Engines are used, in the stern - a transom, in the center of the bottom and an inclined plane to the platform-wing.

The fuel system of the ekranolet consists of four tanks (Fig. 2 pos. B 1:4) located along the fuselages and lying on the bottom. This arrangement of the fuel tanks lowers the center of gravity. Simultaneously pumping fuel from tanks 1⋅2 to 3⋅4 and vice versa, the ekranolet longitudinal centering changes. This mode occurs when: headwind, at the start, when towing rafts. Pumping is carried out by two fuel pumps. Full load of fuel 300÷320 kg. The capacity of each tank is 100 kg. Control and management of the fuel system is carried out from K-1. The longitudinal centering of the ekranolet is still regulated by the distribution of the load.

Management - flight, control over the operation of the engines is carried out from K-1. Since the flight takes place in centimeters from the surface, only touching the trim plates, there is no need to adjust the height of the ekranolet. Horizontal control is carried out by two rudders Р⋅1, Р⋅2 (Fig. 9 pos. Р⋅1), which are located in the center of the air flow of screws В⋅1, В⋅2. The rudders turn on the axis (pos. 6 of Fig. 9) in one direction or another at an angle of 45 °, providing a quick turn of the ekranolet. To ensure good controllability, all rotating parts of the steering are assembled on bearings.

The rudders are connected to each other by two articulated rods (pos. 35 fig. 6), the cable tension is adjusted by two lanyards (pos. 34 fig. 6). Transfer of rotation from the cabin K⋅1 through two Pulleys ∅ 200 mm, rollers and on the rudders. On the pulleys, the cable is wound in different directions by 3, 4 turns. The pilot is in K⋅1. During long and difficult trips, there is a navigator in K⋅2. In K⋅3 and 4, depending on the purpose of the flight, rescuers, medical staff, passengers, etc. The troops also have rescuers and people to perform various operations. Cabins are separated from the rest of the fuselage volume by deaf jumpers, and inside they are insulated with foam plastic, wood. Cabin caps open K⋅1⋅2 forward. K⋅3⋅4 back. The rest of the fuselage is used as an unsinkable volume.

Straightener (Fig. 9 pos. 45) - designed to limit the turbulence of the flow from the screw B⋅1. On both sides of the D-1 engine, two racks with transverse jumpers are installed. The bottom is attached to the engine foundation, the top is the support for the KG wing.

When operating the ekranolet on the water, it is possible to use the R-30÷40 kW outboard engine - with limited visibility, towing life rafts and just as an emergency use.

The ekranolet uses the energy of the air flow, the lifting force of the wing, and the ground effect, it can work like a snowmobile or a boat. Crew of 4 people, fuel weight 300÷kg, survival equipment, tools, weapons, etc. at a flight speed of 100 km / h, it is capable of performing any rescue work, as well as in the Navy, the border, and the Ministry of Internal Affairs. It can work in all climatic zones of Russia, in winter, summer, on water and snow, to perform search and rescue operations, to provide medical assistance. assistance in the Ministry of Emergency Situations and the Armed Forces.

Claims (9)

1. Ekranolet, characterized by the fact that it consists of a catamaran with two fuselages, along which a horizontal aerodynamic wing is mounted on supports at a height of 1.6 m for the entire length of the fuselages 2 m wide, two propeller-driven installations are installed under the wing on the fuselages, one in the nose, and the other in the stern, on each side of the wing a vertical plane is fixed. 2. Ekranolet according to claim 1, characterized in that the fuselages are made 6 m long. 3. Ekranolet according to claim 1, characterized in that the horizontal aerodynamic wing is located along the fuselages for their entire length. 4. Ekranolet according to claim 1, characterized in that two vertical planes are fixed to the side surfaces of the wing for the entire length of the wing. 5. Ekranolet according to claim 1, characterized in that the blade is welded to the base, which has the possibility of angular rotation on the axial bolt. 6. Ekranolet according to claim 1, characterized in that the top of the fuselages are interconnected by a platform-wing, the bottom of the fuselages are four skis and steel strips, the engine foundations are used to connect the fuselages, a transom is located in the stern, the bottom and an inclined plane are located in the center to the wing platform. 7. Ekranolet according to claim 1, characterized in that the fuel system of the ekranolet consists of four tanks located along the fuselage, lying on the bottom and equipped with pumps. 8. Ekranolet according to claim 1, characterized in that it contains two rudders, which are located in the center of the air flow of the propellers, with the ability to turn the rudders at an angle of 45°, the rudders are connected to each other by two articulated rods. 9. Ekranolet according to claim 1, characterized in that it contains a straightener, on both sides of the engine there are two racks with transverse jumpers.

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