RU2788231C1 - Vtol aircraft - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to the field of aircraft engineering. The VTOL aircraft comprises a fuselage having a nose section, a tail section and a middle section located between them, at least one keel located in the tail section of the fuselage. A gas turbine engine with a drive shaft located in the rear fuselage, the drive shaft is kinematically connected to the fan axles through the main gearbox and gearboxes. Fans installed in the middle part of the fuselage in such a way that they are able to create a flow of fluid from the hole in the upper part of the fuselage in the direction from the fuselage to the sides. The wings are designed in such a way that the lifting force is created by the fluid flow in the direction from the fuselage to the sides, the wings are connected to the motor shafts. Motors made with the ability to rotate the wings relative to the axis of the shafts in such a way that in one of the positions the wings are tilted forward, and in the other of the positions they are tilted back. A screen-exhaust device designed to reduce the temperature of the exhaust gases by mixing with atmospheric air entering the mixing chamber by creating a low-pressure area in it by passing a high-speed compressed air flow flowing from the nozzle apparatus and mixing the mixed flow with the incoming air in the exhaust channel flow. Devices of on-board radio-electronic equipment, made with the possibility of extension vertically upwards. Module of the vertical launch device with cells of the transport-launch container of guided missile weapons, located in the middle part of the fuselage. Fairings with channels made in them with a slot in such a way that they are able to create a fluid flow in the direction up and down from the fairing. Nozzles, in fairings, in the nose and tail of the fuselage, made with the ability to control the pitch, yaw and roll in all flight modes.

EFFECT: improvement of tactical and technical characteristics, in particular stealth and increase in the combat effectiveness of the aircraft.

4 cl, 8 dwg

Description

FIELD OF TECHNOLOGY TO WHICH THE INVENTION RELATES

The invention relates to aviation technology, and can be used as a close support aircraft for ground forces over the battlefield.

BACKGROUND OF THE INVENTION

The Mi-28NM direct air support attack helicopter (ru.wikipedia.org Mi-28) is known from the prior art. The Mi-28NM is a single-rotor helicopter with a tail rotor and a two-man tandem cockpit. The helicopter is designed to search and destroy tanks and other armored vehicles, enemy manpower, reconnaissance and target designation in the face of fire resistance. The complex of on-board radio-electronic equipment (avionics) ensures the combat use of the helicopter around the clock and in adverse weather conditions, the performance of combat missions at extremely low altitudes with enveloping the terrain. The armament of the helicopter includes built-in small arms, unguided rocket, guided missile, air-to-air missiles.

Protection of the crew members is ensured by the use of highly resistant armor and glazing that can withstand direct hits by armor-piercing bullets of 7.62 mm, 12.7 mm caliber, as well as high-explosive fragmentation shells of 20 mm caliber. To increase survivability, constructive and layout solutions are used: spacing engines, shielding crew members with massive parts, shielding important components with less important ones, protecting fuel tanks, etc. Reduced visibility in the infrared range due to the installation of screen-exhaust devices (EVU). Protection against destruction by guided missiles is provided by equipment for jamming radar stations and infrared homing heads. At the same time, the elements of the carrier system, including the main and tail rotors, transmission, main gearbox, controls (swashplate), engines are not protected from small arms fire, small-caliber anti-aircraft artillery, which excludes the performance of combat missions directly above the battlefield, in populated points and cities.

The disadvantage of the helicopter is the high level of visibility for modern surveillance equipment. The main unmasking factor is the carrier system and tail rotor. This is a rather complex mechanism with many moving parts that effectively reflect the radio signal and help the radar solve its problems. The thermal signature of a helicopter is created by the heating of the running engine and gearbox, as well as the release of high-temperature exhaust gases, which makes it possible to detect it using infrared equipment. The operation of the engine and the rotation of the propellers produce a characteristic noise at different frequencies, which makes it possible to determine the presence of a helicopter. Reducing the infrared signature with the installation of screen-exhaust devices (EVU) does not provide the helicopter with guaranteed safety from such, in particular, weapons with a thermal homing head, such as a man-portable air defense system (MANPADS).

The use of weapons with an infrared homing head forces helicopters to use guided and unguided weapons outside the firing range of MANPADS (5-6 km.) An increase in the range of weapons for direct air support reduces the combat effectiveness of the helicopter.

The use of a carrier system on a helicopter with a main rotor diameter (17 m), a tail rotor (3.85 m), a fuselage length (17 m) does not allow it to be used in street battles in settlements and cities to support ground forces. The closest to the proposed technical solution is the design of a vertical takeoff and landing aircraft (patent RU 2752276, 2021, Bituev AG). Known aircraft contains a fuselage, in the nose and tail of which is the carrier system, and in the middle part of the cockpit and engine-transmission department. The carrier system consists of wings installed with the leading edge to each other, parallel and symmetrical with respect to the longitudinal axis of the aircraft, closed with fairings at the ends. The wings are streamlined by the air flow of the fans in the direction from the fuselage to the sides. In the middle between the fans in the space between the walls of the air ducts, motors are installed, the shafts of which are connected to the wings. The motors are made with the ability to rotate the wings relative to the axis of the shafts in such a way that in one of the positions the wings are tilted forward, and in the other of the positions they are tilted back. When the wings are tilted forward or backward, the aircraft is given a horizontal speed directed forward or backward. Aircraft control in all flight modes is carried out by jet rudders. The advantage of the known technical solution is the large carrying capacity of the carrier system. Increased controllability and maneuverability of the aircraft, small dimensions make it possible to use it from sites of limited size in dense urban areas.

The use of the aircraft for military purposes is limited by the lack of survivability systems.

SUMMARY OF THE INVENTION

The technical objective of the invention is to improve the tactical - technical characteristics (stealth) and increase the combat effectiveness of the aircraft. The task was solved due to the fact that the proposed VTOL aircraft contains:

fuselage (1) having a nose, a tail and a middle part located between them,

at least one keel (5) located in the rear fuselage (1),

at least one gas turbine engine (11) with a drive shaft (12) located in the rear fuselage,

fans (4) installed in the middle part of the fuselage (1) in such a way that they are able to create a fluid flow from the hole in the upper part of the fuselage in the direction from the fuselage to the sides,

drive shaft (12) kinematically connected to the axes of the fans through the main gearbox (13) and at least one gearbox (8),

wings (2) made in such a way that the lifting force is created by the fluid flow in the direction from the fuselage to the sides,

wings (2) connected to shafts (10) of motors (9),

motors (9) made with the ability to rotate the wings (2) relative to the axis of the shafts (10) in such a way that in one of the positions the wings are tilted forward, and in the other of the positions they are tilted back,

a screen-exhaust device designed to reduce the temperature of the exhaust gases by mixing with atmospheric air entering the mixing chamber (17) by creating a low-pressure area in it by passing a high-speed flow of compressed air flowing out of the nozzle apparatus (16) and mixing in the exhaust channel (18) mixed flow with ram air flow,

on-board electronic equipment devices 23, made with the possibility of extension vertically upwards,

at least one module of the vertical launch device 21 with cells of the transport and launch container of guided missile weapons 22, located in the middle part of the fuselage 1,

fairings (3), with channels made in them with a slot (15) in such a way that they are able to create a fluid flow in the direction up and down from the fairing,

nozzles, in fairings (3), in the nose and tail of the fuselage (1), made with the ability to control pitch, yaw and roll in all flight modes.

In fact, the task is achieved as follows: a vertical take-off and landing aircraft with a fuselage, wings, fans, differs in that in the mixing chamber of the screen-exhaust device, the exhaust gases are mixed with atmospheric air and are mixed with the oncoming air flow at the outlet.

As it will be clear to a specialist, the advantages of the proposed aircraft in comparison with the selected prototype are achieved mainly due to the fact that in the screen-exhaust device, by mixing the exhaust gases with atmospheric air, the temperature of the exhaust gases is reduced.

In preferred embodiments of the aircraft described above:

- the engine (11) is made of turboshaft.

- the exhaust channel (18) is closed with a heat-insulating screen (19) made in such a way that an air gap is formed between them.

- it is equipped with two keels (5) located vertically at a distance from each other in the rear fuselage (1).

The present invention is illustrated in the drawings.

BRIEF DESCRIPTION OF THE FIGURES OF THE DRAWINGS

On FIG. 1 shows a general view of the aircraft in three projections.

On FIG. 2 shows section A-A.

On FIG. 3 shows the B-B section.

On FIG. 4 shows the kinematic diagram

On FIG. 5 shows the creation of an air curtain of wings and horizontal thrust

On FIG. 6 shows a screen-exhaust device

On FIG. 7 shows the section B-B. On

Fig. 8 shows the G-G section.

Positions 1-23 are designated:

I - fuselage, 2 - wings,

3 - wing fairings,

4 - fans,

5 - keel,

6 - chassis,

7 - air intakes,

8 - fan gearbox,

9 - motors,

10 - motor shafts,

II - engine,

12- drive shaft,

13 - main gearbox,

14 - transmission shafts,

15 - slotted channels,

16 - nozzle apparatus of the ejector,

17 - mixing chamber,

18 - exhaust channel,

19 - heat-insulating screen,

20 - mobile gunnery mount,

21 - vertical launch device module,

22 - cell of the transport and launch container of guided missile weapons,

23 - retractable avionics device.

IMPLEMENTATION OF THE INVENTION

According to the layout scheme, the aircraft is two-engine with side air intakes. The vertical plumage is two-keeled. Chassis "normal" three-post, non-retractable.

As shown in FIG. 1 plane contains:

fuselage 1,

wings 2,

wing fairings 3,

fans 4,

keels 5,

chassis 6,

air intakes 7,

exhaust port 18,

mobile gunnery mount 20,

vertical launcher module 21,

retractable device of onboard radio-electronic equipment 23.

As shown in FIG. 1 and FIG. 2 in the middle fuselage 1 with the leading edge to each other, parallel and symmetrical with respect to the longitudinal axis of the aircraft, wings 2 are installed, closed at the ends by fairings 3.

As shown in FIG. 3 in the middle between the fans 4 in the space between the walls of the air ducts, motors (pneumatic / hydro) 9 are installed, the shafts 10 of which are connected to the wings 2.

As shown in FIG. 4 in the rear of the fuselage there is an engine-transmission department, in which two gas turbine engines (GTE) 11 are installed, which are connected by drive shafts 12 to the main gearbox 13. The main gearbox 13 transmits torque to two-stage fans with rotors by means of fan gearboxes 8 and transmission shafts 14 reverse rotation 4.

As shown in FIG. 5 in the front fairings 3 in the upper and lower surfaces there are channels with slots 15 from which the high-speed flat flow of compressed air coming from the engine compressor flows out.

As shown in FIG. 6, FIG. 7 in the engine-transmission department there is a screen-exhaust device (EVU) of the ejector type, consisting of a mixing chamber 17, nozzle devices 16, an exhaust channel 18 closed with a heat-insulating screen 19.

As shown in FIG. 1, Fig. 8 in the middle part of the fuselage between pairs of fans 4 there are two modules of the vertical launch device 21. Each module contains a certain number of cells 22 for transport and launch containers of guided missile weapons.

Vertical takeoff is carried out as follows:

1) after starting the engine 11, the drive shaft 12 transmits torque to the main gearbox 13

2) the torque from the main gearbox 13 through the gearboxes of the fans 8 and the transmission shafts 14 is brought to the fans 4. The air flow of the fans flowing around the wings 2 creates lift (F _y ) and drag force (F _x ) (Fig. 2)

3) as soon as the vertical thrust, as the sum of the lifting forces of the wings (F _y ), becomes greater than the force of gravity, the aircraft will lift off the surface and vertical takeoff will begin.

4) after reaching a certain height, the motors 9, by turning the shafts 10, synchronously tilt the wings 2 at the same angle forward (Fig. 3, Fig. 5). When the wings tilt forward, a horizontal component (F _r ) of lift (F _y ) is formed, which tells the aircraft the horizontal speed (Fig. 5). The tilt of the wings reduces the vertical component (F _B ) of the lift (F _y ), which can lead to a loss of altitude of the aircraft. To prevent this from happening on the aircraft, the “angle-gas” system is used, which, simultaneously with an increase in the angle of inclination of the wings, sends a command to the fuel automatics to increase engine speed, thereby excluding a decrease in the vertical component (F _in ).

5) In cruise mode, the wing air curtain system is activated. Compressed air from the engine compressor 11 is supplied to the channels with slots 15 in the upper and lower surfaces of the front fairings 3. The oncoming air flow (V2) interacting with a high-speed flat jet of compressed air (V ₁ ) flowing from the slots of the channel 15 is decelerated and deflected (V ). To increase the efficiency of the air curtain, it is possible to install several channels with slots. In addition, for a smoother (laminar) flow around the wings, it is possible to control the speed and direction of the outflow (angle) of compressed air depending on the speed of the aircraft. (Fig. 5)

Vertical landing is carried out as follows:

1) When approaching the landing site, the motors 9 rotate the shafts 10 synchronously tilt the wings 2 at the same angle back. The resulting horizontal component (F _r ) of the lifting force (F _y ) will be directed in the opposite direction of the aircraft's movement and, consequently, reduce its speed.

Thus, the aircraft will decelerate in the air until it comes to a complete stop.

2) A smooth decrease in engine speed allows for a vertical landing.

During the operation of the engines, the exhaust gases from the exhaust pipes are directed upward through the gas ducts into the mixing chamber 17, into which a high-speed stream of compressed air coming from the engine compressor flows out of the nozzle devices 16. When a high-speed air flow passes through the mixing chamber 17, a reduced pressure is created in it, which causes atmospheric air leakage. Thus, in the mixing chamber, the exhaust gases, atmospheric air and high-speed compressed air flow are combined and form a mixed flow. In the process of heat exchange in a mixed flow between high-temperature exhaust gases with atmospheric air and compressed air, the temperature of which is many times lower, a significant decrease in the temperature of the exhaust gases occurs. From the mixing chamber 17, the expanding flow enters the exhaust channel 18 and is removed outside. When the aircraft moves in the exhaust channel 18, the mixed flow is cooled when mixed with the oncoming air flow. In addition, the cooling of the mixed flow in the exhaust channel 18 is carried out by the flowing air between the walls of the exhaust channel and the heat shield 19. (Fig. 6, Fig. 7).

In all flight modes, a jet (jet) control system is used. Nozzle devices of the jet control system are installed in the nose and tail sections of the fuselage and in the wing fairings.

Thus, when the wing fans are located in the air flow, with the leading edge to each other, parallel and symmetrical with respect to the longitudinal axis of the aircraft, the vector sum of the drag forces becomes equal to zero.

This makes it possible to use airfoils with the highest lift coefficient (C _y ) without taking into account their drag coefficient (C _x ). In addition, the lift coefficient can be increased by using a boundary layer control system.

The implementation of the above measures aimed at increasing the lift coefficient makes it possible to significantly increase the lift (ceteris paribus) with minimal energy consumption and, consequently, increase the aircraft's carrying capacity.

The location of the wings along the sides of the fuselage significantly reduces the drag of the wings to the oncoming air flow when the aircraft is moving, thereby increasing its efficiency.

Installing the wings in fairings and an air curtain with a high-speed flat flow of compressed air directed up and down from the fairing significantly reduces the drift of the air flow of the fans by the oncoming flow without additional energy consumption, which increases the efficiency and carrying capacity of the aircraft.

An increase in the carrying capacity and efficiency of the aircraft makes it possible to significantly strengthen the fuselage armor and cockpit glazing to the level that can withstand direct hits from armor-piercing bullets of small arms, large-caliber small arms, and small-caliber anti-aircraft artillery shells. Placing the main elements of the carrier system, such as fans, gearboxes, transmission, engines in the armored fuselage, significantly increases the combat survivability of the aircraft. Increasing the survivability of the aircraft makes it possible to perform combat missions at extremely low altitudes under enemy fire.

The use of a carrier system in which the lifting force is created by the air flow around the fans, the wings fixedly installed along the fuselage, reduces the radar visibility of the aircraft many times over.

The mixture of exhaust gases with atmospheric air leads to a significant decrease in the temperature of the exhaust gases, which significantly reduces the visibility of the aircraft in the infrared and ultraviolet radiation ranges. The reduction of the thermal signature of the aircraft is facilitated by the placement of engines, the main gearbox, gearboxes inside the aircraft fuselage.

The use of a carrier system with fixed wings, fans installed in the channels of the fuselage, mixing of exhaust gases in the EED, placement of engines and transmissions inside the fuselage reduce the noise produced by the aircraft.

From the foregoing, it follows that the new carrier system used and a set of measures aimed at reducing unmasking factors significantly increase the level of aircraft stealth.

The connection of the wings with the motor shafts made with the possibility of turning the wings relative to the axis of the shafts in such a way that in one of the positions the wings are tilted forward, and in the other position back, enable the aircraft to perform vertical takeoff and landing, hover, move forward and backward, as well as braking to a complete stop.

The use of jet rudders allows the aircraft to move sideways, perform rotations around a vertical axis, parry external influences, as well as control pitch, yaw and roll in all flight modes. Increased controllability and maneuverability, small size, make it possible to use the aircraft, including in urban street battles.

The complex of the guided missile weapon system, including some devices and systems of on-board electronic equipment (radar, surveillance and sighting station for detecting and recognizing objects, capturing and auto-tracking, etc.), made with the possibility of moving up to the required height and a vertical launch device provide shelling of the target (ground, air) in any direction from a standstill and on the move, without changing the position of the aircraft in space. In addition, it is possible to shell a target due to obstacles (building, uneven terrain, trees, etc.) without entering the line of fire. Survivability, stealth, maneuverability, all-round use of aircraft weapons make it possible to perform combat missions at extremely low altitudes directly above enemy positions and in the depths of his defense, which increases combat effectiveness.

Claims (17)

1. A VTOL aircraft, containing: fuselage (1) having a nose, a tail and a middle part located between them, at least one keel (5) located in the rear fuselage (1), at least one gas turbine engine (11) with a drive shaft (12) located in the rear fuselage, fans (4) installed in the middle part of the fuselage (1) in such a way that they are able to create a fluid flow from the hole in the upper part of the fuselage in the direction from the fuselage to the sides, drive shaft (12), kinematically connected to the axes of the fans through the main gearbox (13), and at least one gearbox (8), wings (2) made in such a way that the lifting force is created by the fluid flow in the direction from the fuselage to the sides, wings (2) connected to shafts (10) of motors (9), motors (9) made with the ability to rotate the wings (2) relative to the axis of the shafts (10) in such a way that in one of the positions the wings are tilted forward, and in the other of the positions they are tilted back, a screen-exhaust device designed to reduce the temperature of the exhaust gases by mixing with atmospheric air entering the mixing chamber (17) by creating a low-pressure area in it by passing a high-speed flow of compressed air flowing from the nozzle devices (16) and mixing in the exhaust channel (18) of mixed flow with oncoming air flow, on-board electronic equipment devices 23, made with the possibility of extension vertically upwards, at least one module of the vertical launch device 21 with cells of the transport and launch container of guided missile weapons 22, located in the middle part of the fuselage 1, fairings (3), with channels made in them with a slot (15) in such a way that they are able to create a fluid flow in the direction up and down from the fairing, nozzles, in fairings (3), in the nose and tail of the fuselage (1), made with the ability to control pitch, yaw and roll in all flight modes. 2. The aircraft according to claim 1, characterized in that the engine (11) in it is made of a turboshaft. 3. The aircraft according to claim 1, characterized in that the exhaust channel (18) in it is closed with a heat-insulating screen (19) made in such a way that an air gap is formed between them. 4. The aircraft according to claim. 1, characterized in that it is equipped with two keels (5) located vertically at a distance from each other in the rear fuselage (1).

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