RU2297933C1 - Ground-effect craft - Google Patents

Abstract

FIELD: hovercraft; manufacture of hovercraft.

SUBSTANCE: proposed ground-effect craft has fuselage, hydrofoil, horizontal and vertical tails, cruising (air propeller) and booster propulsors with respective engines and landing gear. Engine, turbo-jet engine for example, is located in nose section of fuselage in passage provided with air intake with doors, as well as with nozzle and flap which is provided with doors which form slit at deflection. Trailing edge of lowered flap is located in front of leading edge of hydrofoil. In raised position, flap forms extension. Propeller is mounted in front of horizontal tail and is connected with airframe for rotation about axis passing through axis of rotation of propeller and center of mass of engine and engine nacelle which are connected with propeller.

EFFECT: reduction of aerodynamic drag at cruising speed; enhanced controllability of ground-effect craft during motion at supercharging.

16 cl, 14 dwg

Description

The invention relates to vehicles on a dynamic air cushion, and in particular to ekranoplanes and ekranolet.

From the prior art, ekranoplanes and ekranoleta equipped with a system of blowing gas jets from air propellers under the wing to ensure aerodynamic unloading of the apparatus.

So, from the patent of the Russian Federation No. 2139212 for a group of inventions "A method of creating air unloading and traction for a vehicle, a device for its implementation and an ekranolet with a device for creating air unloading and traction", IPC B 60 V 1/08, 64 C 35/00 , B 64 C 25/66, publication date 10/10/1999, [1], an ekranoplan is known, including a wing, horizontal and vertical tail, a float landing gear, a fuselage, a mid-flight and a starting propulsion connected to the corresponding power drive, while the starting propulsion is located in the bow of the fuselage Before the leading edge of the wing, the engine air intake is located above its nozzle, in the upper part of the fuselage there is an intake manifold mated to the engine air intake, the lower part of the fuselage at the location of the engine nozzle is equipped with a deflectable front shield, and in the lowered position, the rear edge of the wing is located in front of the front edge of the wing . Performing an ekranoplan [1] with a displacement nose of the fuselage and with a front gapless flap leads to significant spray resistance of the displacement bow of the fuselage, and a gapless flap leads to the practical absence of ambient air suction (injection) by jets of the starting air propulsion. Therefore, the magnitude of the pressure head in the jet behind the starting propulsion is limited, which leads to the use of low-pressure air propulsors, for example, fans having significant dimensions. Therefore, the invention is advisable to use in layouts with large dimensions of the bow (in particular, width) of the fuselage, which limits the scope of the invention in other layouts of ekranoplanes.

From the patent of the Russian Federation No. 2253580 for the invention "Ekranoplan with nasal inflatable engines", IPC B 60 V 1/08, publication date 06/10/2005, [2], an ekranoplan is known that includes a wing, horizontal and vertical tail, float landing gear, fuselage, marching and starting propulsors connected to the corresponding power drive, while the starting propulsion is located in front of the leading edge of the wing on the pylon with the possibility of deflection in the vertical plane of the jet of gas flowing from the propulsion (engine nozzle). The necessity of placing the engines on the pylon and deflecting the gas jet, for example, by turning the pylon or turning visors, leads to an increase in the weight of the airframe glider structure. In addition, to meet the requirements to reduce the temperature of the gas incident on the wing, and the need to reduce the speed in the jet, the engines are removed from the leading edge of the wing by a large distance, which increases the length of the nose of the fuselage and the moments of inertia of the winged aircraft. As a result, the weight of the airframe structure and the drag of the ekranoplan increase, its aerodynamic quality decreases and its stability and controllability characteristics deteriorate. WIG [2] adopted for the closest analogue of the invention.

The technical task to be solved is to increase the aerodynamic quality of an ekranoplane with inflatable engines at cruising flight modes by reducing its drag.

The technical result consists in reducing the aerodynamic drag of the vehicle at cruising flight modes. In addition, the technical result consists in increasing the controllability of the ekranoplan when moving with blowing (on a dynamic air cushion).

Disclosure of the invention.

The ekranoplan, as in the closest analogue [2], contains a wing, horizontal and vertical tail, landing gear, fuselage, mid-flight and launch propulsors connected to the corresponding engine, while the launch propulsion is located in front of the leading edge of the wing, but unlike the closest of an analogue, the starting mover is located in the channel in the nose of the fuselage, the air intake of the channel is located above its nozzle, the lower part of the fuselage at the location of the nozzle is equipped with a deflectable front shield made of at least bottom transverse slit equipped with a sash.

The winged wing is characterized in that at least one of the flaps of the front flap is equipped with a drive for its deflection.

Wing is characterized by the fact that the front flap is equipped with aerodynamic ridges.

In this case, the aerodynamic ridges are fan-shaped.

In addition, the aerodynamic ridges are made in the form of an arc, the radius of which decreases with distance from the longitudinal axis of the shield.

The ekranoplan is characterized in that the fuselage is equipped with sashes for blocking the air intake of the channel.

The ekranoplan is characterized in that the propulsive propulsion unit is connected to the ekranoplan glider by means of a motor frame and is located in front of the horizontal tail.

In this case, the propulsion unit is connected to the motor frame with the possibility of rotation in a vertical plane.

In addition, the mid-flight propulsion unit is connected to the mid-flight engine, the fastening element of the mid-flight engine is made in the form of a power element of the nacelle of the mid-flight engine connected to the motor frame by means of a swivel, the axis of which passes through the intersection point of the axis of rotation of the mid-flight propulsion and the center of mass of the units rotating relative to the specified axis and March propulsion.

The ekranoplan is also characterized in that the motor frame is connected to the fastening element of the mid-flight engine by means of a thrust of variable length made with the possibility of connection with an electric drive.

The ekranoplan is characterized in that the horizontal tail is connected to the vertical tail in its upper part.

The winged wing is characterized in that the flap is made two-link, and the second link of the flap is made with the possibility of deviation up and down.

The ekranoplane is characterized in that the wing is made integral, including the center section and the consoles attached to it.

In this case, the center section is made with an elongation of 0.4 ... 0.7, is equipped with a flap, floats or end washers are installed on the sides of the center section.

In addition, the flap is made two-link, and the second link of the flap is made with the possibility of deviation up and down.

The ekranoplane is characterized in that the consoles are installed behind the center of mass of the ekranoplane with a positive transverse angle V and are equipped with ailerons.

In this case, the ailerons are made freezing.

The invention is illustrated by drawings.

Figure 1 shows the ekranoplane when viewed from the side.

Figure 2 presents the ekranoplan when viewed from above.

Figure 3 presents the ekranoplane when viewed from the front in a cruising configuration.

Figure 4 presents the ekranoplane with a composite wing when viewed from the front in the starting configuration.

Figure 5 shows a longitudinal section aa in figure 2 in a cruising configuration.

Figure 6 shows a longitudinal section aa in figure 2 in the starting configuration.

In Fig.7 shows a section bB in Fig.6 with the deflected flaps of the front flap.

On Fig shows a section bB in Fig.6 with non-deflected flaps of the front flap.

Figure 9 shows a section bb in figure 2.

Figure 10 shows a section GG in figure 2.

Figure 11 presents a section DD in figure 2.

On Fig presents a section EE in figure 1.

Figure 13 is a view of And figure 11.

On Fig shows the relative position of the glider and the propulsion relative to the supporting surface at different pitch angles.

The implementation of the invention.

The ekranoplan contains a fuselage 1, wing 2, horizontal 3 and vertical 4 plumage, marching 5 and starting 6 propulsion devices connected to the corresponding engines 7 and 8, a take-off and landing gear, including, for example, floats 9 (Figs. 1 ... 4) , end washers, skis, wheels, etc. (not shown). As a starting engine 8, it is advisable to use a turbojet engine (the nozzle 6 of which is the nozzle), and place it in the nose of the fuselage 1 in channel 10 (Fig. 1). Channel 10 on the upper surface of the fuselage 1 forms an air intake 11, and on the lower surface an outlet nozzle 12. At the entrance to the air intake 11 of channel 10, there are controlled flaps 13 that close the air intake 11 in the cruise configuration of the winged aircraft (figure 5) and open - in the start ( or take-off and landing) ekranoplan configuration (Fig.6). The output nozzle 12 is blocked by a front shield 14 deflected relative to an axis 15 located in the region of the leading edge 16 of the nozzle 12. The shield 14 is deflected by a drive made, for example, in the form of hydraulic cylinders 17 (Figs. 5, 6). The flap 14 is composed of at least two flaps 18, deflected by the drive, for example a hydraulic cylinder 19, with the formation of a gap 20 between adjacent flaps 18 (Fig.5, 6). The lowered flap 14 with the deflected wings 18 with open slots 20 is essentially a trellised wing (Fig.6, 7). The trailing edge 21 of the shield 14 is wider than the leading edge, on which the axis 15 is fixed, and in the lowered (starting) position is located in front of the leading edge 22 of the wing 2 (Fig. 1), and in the raised (cruising) position adjoins the lower surface of the bow the fuselage 1 (figure 5), forming an influx of 23 (figure 2). On the upper surface of the shield 14 (from the side of the wing 2) aerodynamic ridges 24 can be installed, which, when viewed in plan view, can be fan-shaped and performed along an arc with a decrease in the radius of the arc as the distance from the longitudinal axis 25 of the winged aircraft (6, 7, 8) .

The wing 2 can be equipped with flaps 26 (figure 2), configured to deflect up and down. Flaps are made, as a rule, two-link. The second flap link 27 may deviate both down and up with respect to the first link (FIG. 9). In the deflection mechanism of the flap 26 and its links there is an elastic element, for example a shock absorber 28, which deflects the corresponding link of the flap 26 when it encounters an obstacle, such as a wave, and returns it to its former position after passing the obstacle (Fig. 9).

Wing 2 can be made integral, i.e. have a center section 29 and a console 30 (figure 2, 4). The center section 29 is performed with an extension of 0.4 ... 0.7, the console 30 is located behind the center of mass (figure 2 - CM) ekranoplan. The consoles are equipped with roll controls, for example, ailerons 31 (FIGS. 2, 10), which can be performed freezing, i.e. having the ability to deviate downward as flaps, and in this position to deviate upward and downward as ailerons (Figs. 4, 10). Consoles 30 are mounted with a positive lateral angle "V".

The mover 5 of the main engine 7, which can be used as a piston, turboprop or turbojet engine, in the preferred embodiment, the ekranoplane is located in front of the horizontal tail 3, for example, on a pylon (not shown) or on the keel 32 of the vertical tail 4 (figure 1 .. .four). As the march propulsion 5, a propeller 33, a fan, a nozzle (not shown) can be used. The mover 5, as a rule, is connected to the engine 7. The fastening elements 35 of the engine 7 are connected to the motor 36, which in turn is connected to a glider (for example, keel 32) ekranoplan (11, 12).

In a preferred embodiment, the engine 7 through the fastening elements 35, which can be made in the form of a power element, for example, the frame of the engine nacelle 34, is connected to the motor 36 with the possibility of rotation in a vertical plane, for example, relative to the axis 37 (Fig, 13). In this case, the axis 37 passes through the center of mass (Figs. 11-14, CM _{DV + MG} ) of the assemblies rotating relative to the axis 37 (for example, the engine nacelle 34 with the engine 7 and propulsion 5 located therein) and the axis of symmetry of the air propulsion 5, which coincides, as a rule, with the axis of rotation 38 of the propeller 33 or the nozzle of the engine (not shown), through which the thrust vector of the propulsion device 5 passes (11, 13). Elements 35 of the engine mount, made, for example, in the form of a power element of the nacelle 34, are connected to the motor 36 by means of a control hydraulic cylinder 39 (Fig. 11), the control system of which is included in the system for determining and / or indicating the spatial position of the ekranoplan, for example, with a horizontal horizon ( not shown).

WIG operates as follows.

Before movement in the blowing mode, the ekranoplane is transferred to the launch (takeoff and landing) configuration: the flaps 13 are rejected, opening the entrance to the air intake 11, the flap 14 is lowered, opening the nozzle 12 of the channel 10 in the nose of the fuselage 1, the flap flaps 18 are deflected with the formation of slots 20 between by them, flaps 26 of wing 2 are deflected down. Starting 7 and marching 8 engines are launched, movers 5 and 6 create traction, and the ekranoplan starts moving. The jets of the starting propulsion 6, flowing from the nozzle 12 of the channel 10, pass over the upper surface of the shield 14. Air is injected (sucked in) through the slots 20, which, mixing with the jet behind the propulsion 6, increases the mass of the gas directed under the wing 2 (or center section 29) and reduces its speed. In this case, the dynamic component decreases and the static component of the total jet pressure increases. This allows you to bring the engine 8 closer to the leading edge of the wing 2 and thereby reduce the length of the fuselage 1 and the moment of inertia of the winged aircraft. The gas directed under the wing 2 is inhibited in the chamber formed between the floats (skegs, side washers) and the flap 26 lowered, the dynamic pressure is converted to static pressure, which, acting on the lower surface of the wing 2 (or center section 29), creates a lifting force. Mounted on the surface of the flap 14, aerodynamic ridges 24, arranged by a fan, provide the distribution of the jet along the wingspan 2, and the regulation of the gap between the surface (screen) and the trailing edge of the flap 26 (and with a two-link flap - its second link 27) when deflecting provides the creation of reactive thrust the flowing gas stream and creates a mass balance of the gas supplied under the wing and leaving the under the wing, ensuring the creation of lifting force and traction when blowing (dynamic air cushion), preventing the flow of the jet gas forward and reducing spatter. This achieves the maximum ratio between the lifting force and thrust (jet impulse) of the starting propulsion 6. The presence of shock absorbers 28 on the flap 26 ensures that the corresponding link of the flap 26 is deflected upward when encountering an obstacle, such as a wave, and returning to their previous position after passing the obstacle .

As the acceleration accelerates, the angle of installation of the valves 18 is regulated (by means of a drive, for example, a hydraulic cylinder 19), during which a flow develops on the front shield 14, which acts as a trellised wing, when it flows around with a free flow and injected (suction jet of the propulsion 6). This allows you to control the ekranoplane in the starting (takeoff and landing) pitch configuration when driving in the boost mode.

After passing the hump of resistance and acceleration, the ekranoplan can take a cruising configuration: with the hydraulic cylinder 17, the front shield 14 rises up, forming an influx 23, with the hydraulic cylinder 19 of the sash 18 deflecting, closing the slots 20 and forming the lower surface of the influx 23, and blocking the nozzle 14 of the channel 10, the sash 13 closes air intake 11. The flaps 26 of the wing 2 are converted into a cruising configuration. As a result, drag decreases and the aerodynamic quality of the ekranoplan in a cruising configuration increases.

In cruising flight, the sash 13 of the air intake 11 and the sash 18 of the flap 14 can open with the formation of slots 20 between them, the starting engine 8 is turned on, and the gas stream exiting through the nozzle 12 of the channel 10 and the slit 20 between the flaps 18 creates an additional thrust and lift to the marching propulsion 5 force. Regulation of the angle of deflection of the valves 18 provides a change in the angle of the outflow of the jet and, therefore, the regulation of the longitudinal moment of the winged wing. This increases the controllability and maneuverability of the ekranoplan in the vertical plane.

When performing wing 2 composite, i.e. including the center section 29 and the console 30, equipped with ailerons 31, which can be performed freezing, it is possible to provide the optimal balance of stability near the screen and the aerodynamic quality of the wing 2: by increasing the chord of the center section 29 increases the height stability, and increasing the wingspan 2 due to the consoles 30 reduces inductive resistance and, therefore, increases the aerodynamic quality of the ekranoplan, sufficient for flights outside the area of the screen effect, i.e. ekranoplan becomes ekranolet. The location of the consoles 30 behind the center of mass (CM) of the ekranoplan gives them stabilizer properties, increasing the stability of the ekranoplane, which reduces the static moment of the horizontal tail 3 (equal to the product of the area of the plumage 3 by the distance between it and the center of mass of the ekranoplan) by reducing the size of the horizontal tail, and reduce drag in general. The presence of hovering ailerons 31 allows you to increase the lifting force at the start while maintaining roll control.

The performance of the marching mover 5 by blowing the horizontal tail 3 increases the controllability of the ekranoplan. The connection of the marching propulsion unit 8 and the engine 7 by means of fastening elements 35 with the possibility of rotation in a vertical plane relative to the motor 36 mounted on a pylon (not shown) or on the keel 32 of the vertical tail 4, provides airflow of the horizontal tail 3 at a constant pitch angle (to the horizon) ( Fig.14). The connection of the fastening elements 35 (which can be performed in the form of a power frame of the nacelle 34) of the engine 7 with the motor 36 can rotate relative to the axis 38 (passing through the center of mass of the engine 7 with the mover 5 and the engine nacelle 34, CM _{DV + MG} , 11, 14 ) and the thrust vector of the propulsion device 5, which, as a rule, coincides, as a rule, with the axis of rotation 38 of the propeller 33 or nozzle, ensures the stabilization of the angular position of the axis of rotation of the screw 33, operating as a gyroscope, relative to the horizontal plane. This increases the efficiency of the horizontal tail due to its flow around the stream at a speed exceeding the speed of the ekranoplan, almost at the same angle as wing 2, without bevel angles induced by vortices coming out of the wing 2. The presence of the control hydraulic cylinder 39, connecting the mounting element 35 of the engine 7 (for example, the power frame of the engine nacelle 34) with the motor 36, provides an adjustment of the angle of inclination of the axis of rotation 38 of the screw 33 relative to the horizontal plane, which may occur, for example, as a result of a precession when the aircraft wing is turned.

Presented in the description of the invention, the set of features and the degree of disclosure of the invention are sufficient for its implementation in the development and manufacture of ekranoplanes.

Claims (16)

1. The ekranoplan, including the wing, horizontal and vertical tail, landing gear, fuselage, marching and launch propulsion, connected to the corresponding power drive, while the launch propulsion is located in front of the front edge of the wing, characterized in that the launch propulsion is located in the channel in the nose of the fuselage, the air intake of the channel is located above its nozzle, the lower part of the fuselage at the location of the nozzle is equipped with a deflectable front shield made with at least one transverse slit equipped with a sash. 2. Wing according to claim 1, characterized in that at least one leaf of the front flap is equipped with a drive for its deflection. 3. Wing according to claim 1, characterized in that the front flap is equipped with aerodynamic ridges. 4. Wing according to claim 3, characterized in that the aerodynamic ridges are fan-shaped. 5. The ekranoplan according to claim 4, characterized in that the aerodynamic ridges are made in the form of an arc, the radius of which decreases with distance from the longitudinal axis of the ekranoplan. 6. The ekranoplan according to claim 1, characterized in that the fuselage is equipped with sashes for blocking the air intake of the channel in the nose of the fuselage. 7. The ekranoplan according to claim 1, characterized in that the propulsion engine is connected to the ekranoplan glider by means of a motor frame and is located in front of the horizontal tail. 8. Wing according to claim 7, characterized in that the fastening element of the mid-flight engine with a propulsion is connected to the motor frame with the possibility of rotation in a vertical plane. 9. Wing according to claim 8, characterized in that the marching propulsion is connected to the marching engine, the fastening element of the marching engine is made in the form of a power element of the nacelle of the marching engine connected to the motor frame by means of a swivel, the axis of which passes through the intersection of the axis of rotation of the marching propulsion and the center of mass of the units and the propulsion unit turning relative to the specified axis. 10. An ekranoplan according to claim 8 or 9, characterized in that the motor frame is connected to the engine mount with the propulsion element by means of a variable-length traction made with the possibility of connection with an electric drive. 11. Wing according to claim 7, characterized in that the horizontal tail is connected to the vertical in its upper part. 12. Wing according to claim 1, characterized in that the wing flap is made two-link, and the second flap link is made to deflect up and down. 13. Wing according to claim 1, characterized in that the wing is made integral, comprising a center wing and consoles attached to it. 14. The ekranoplan according to item 13, wherein the center section is made with an elongation of 0.4 ... 0.7, is equipped with a flap, floaters or end washers are installed on the sides of the center section. 15. The ekranoplan according to claim 13, characterized in that the consoles are installed at the rear of the center of mass of the ekranoplan with a positive transverse angle V and are equipped with ailerons. 16. The ekranoplan according to clause 15, wherein the ailerons are made freezing.

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