RU2364551C2 - Flying wing of vertical take off and landing (fwvtl) - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: invention relates to VTOL flight vehicles heavier than air. Flying wing of vertical take-off and landing incorporates adaptive wind and power plant comprising engines and centrifugal compressors that allow changing thrust vector and boundary layer control. Round- or oval-shape wing features surface coordinates located on 2^nd-order lines. Plane wherein every line lies is perpendicular to that of the wing lengthwise profile shape. Power plant comprises air jet engine integrated, via pto-device and air duct, with pneumatic drive of centrifugal compressor. The latter is furnished with motor-generator or super flywheel and nozzle with flaps to change thrust vector from vertical to horizontal one. FWVTL upper part split wing features slits to make air intakes of centrifugal compressors and to control boundary layer.

EFFECT: expanded performaces.

10 dwg

Description

The technical field to which the invention relates.

The invention relates to aircraft heavier than air, vertical take-off and landing, mainly to light-weight, unmanned.

The prior art.

Light vehicles (LMA) are designed to perform tasks at a slight distance from the target of interest without detection by the enemy and to supply intelligence groups with important tactical information in combat scenarios in urban and mountainous areas. The small size of the aircraft is necessary primarily to reduce the total cost of the system compared to large military UAVs, as well as for ease of transfer or transportation. A typical combat mission of an LMA consists of flying to an object of interest at 25 km, at a speed of 0 to 700 km / h, at an altitude of “shaving” to 3 km, flying around an object’s zone for half an hour and returning to its original location. The LMA must make tactical flights in the zone of turbulent winds up to 45 km / h, maneuver near buildings and in mountainous areas, and repeatedly gain altitude to overcome obstacles. LMA should also be suitable for conducting video reconnaissance from the air and convenient for deployment with minimal time spent on training sessions.

LMA should have small overall dimensions and weight, work in areas of strong winds and deliver high-quality video images. The design of these aircraft should be based on integrated technology, the task of which is the overall operation of the LMA system.

The shape of the wing in terms of affects drag. All things being equal, at low speeds, an elliptical wing is the most advantageous, but it is more difficult to manufacture. At subsonic speeds, it is aerodynamically advantageous to have wings with large elongations, but for high-speed aircraft, elongated wings cease to be advantageous.

For LMA, various drives are used, more often than others electric ones, for which various batteries are being developed, including organic.

“Now a huge number of foreign firms and research centers, mainly in the USA, are engaged in the development and creation of super-flywheel engines, including for aviation and space purposes. Super-flywheel engines are made of tape and fibers, which do not give dangerous fragments when ruptured. In terms of the most important indicator - specific energy - they are already equal to the best electrochemical batteries, and the specific power is hundreds of times more ”/“ Engineering and Science ”, 1982, No. 1 /.

So far, rocket and jet engines are rarely used in LMA.

Solid propellant rocket engines (RDTT) are characterized by high reliability (99.96-99.99%); the possibility of long-term storage, that is, constant readiness for launch; significant draft due to a very short burning time; safe handling due to lack of toxic materials; high fuel density (1.5-2 g / cm ² ).

Disadvantages of solid propellant rocket motors: a large mass of the structure due to high pressures in the combustion chamber; the sensitivity of most fuels to shock and temperature changes; inconvenience of transporting equipped solid propellant rocket engines; short working time; difficulties associated with the regulation of the thrust vector; low specific impulse in comparison with liquid rocket engines.

An air-jet engine (WFD), which uses oxygen from atmospheric air to burn fuel. WFD drives aircraft (airplanes, helicopters, aircraft-shells). The thrust force in the WFD results from the expiration of the working gases from the jet nozzle. To obtain a high velocity of the outflow of gases from the nozzle, the air entering the combustion chamber of the WFD is compressed. Depending on the method of compressing the air, the airjet engines are divided into turbo-compressor (turbojet), pulsating (PuVRD) and direct-flow (ramjet).

In a ramjet (ramjet) in the inlet diffuser, the air is compressed due to the kinetic energy of the incoming air flow. The operation process is continuous, so the ramjet has no starting thrust. At flight speeds below half the speed of sound (below 500 km / h), the increase in air pressure in the diffuser is negligible, therefore, the resulting thrust force is small. In this regard, at flight speeds corresponding to M <0.5 (where M is the Mach number), the ramjet is not used; Ramjet engines can work both on chemical (kerosene, gasoline, etc.), and on atomic fuel. The main advantages of ramjet engines are: the ability to operate at significantly higher flight speeds and altitudes than turbojet engines; greater efficiency compared to liquid rocket engines (LRE), the absence of moving parts and simplicity of design. The main disadvantages of ramjet engines: lack of static (starting) traction, which requires a forced start; low profitability at subsonic flight speeds / Lit.: Bondaryuk M.M., Ilyashenko S.M. Ramjet engines, M., 1958 /.

Known aircraft - an analogue closest to the invention, including an adaptive wing, engines, centrifugal compressors, mechanisms that provide the ability to change the thrust vector and control the boundary layer (RF Patent RU No. 2174484 C2, 1999, 7 V64C 29/00) [1 ].

The direct use of the apparatus [1] for an unmanned aerial vehicle, especially a small one, light-engine, is constrained by the following restrictions: the need to significantly reduce noise in the area of interest to the object, while it is necessary to have a high specific power of the engine for flying and maneuvering in the area of turbulent winds up to 45 km / h , near buildings and in mountainous areas, and repeatedly climb to overcome obstacles.

Disclosure of the invention.

The essence of the invention is that a Discolet is an aircraft heavier than air, vertical (short) take-off and landing, mainly unmanned, with an adaptive wing and a power plant, including engines, centrifugal compressors and mechanisms for changing the thrust vector and controlling the boundary layer, is equipped with a self-balancing, a disk-shaped (variant - ellipsoidal) flying wing, with the coordinates of the surface on the lines of rotation, in the form of circles, ovals, ellipses, etc., the plane in which the line of rotation lies erpendikulyarna longitudinal profile plane and the intersection of the planes coincides with the diameter of rotation of the lines so that one end of the diameter located at the bow and the other end at the line of intersection with the contour of the longitudinal profile;

The power plant is equipped with a solid propellant rocket engine (option 1), or an air-reactive engine (option 2), mostly direct-flow, which is integrated with a centrifugal compressor and super-flywheel (option 1) or with a centrifugal compressor and electric motor, motor generator, air drive (2, 3, 4 options), with the possibility of spinning the super-flywheel from its own or external drive, as well as from the vacuum that occurs in a narrow part of the jet nozzle when a flow of working gases passes through it.

The centrifugal compressor is equipped with a nozzle with dampers, which provide the ability to change the thrust vector from vertical to translational, and the boundary layer is controlled by slits in the split wing in the upper part of the apparatus, used as an air intake of the specified centrifugal compressor.

In addition, the device can be equipped with an electric current generator to ensure the operation of all systems and the aircraft as a whole, as a functional component of the aviation complex.

A brief description of the drawings.

Figure 1 shows a General view of a diskette with a solid propellant rocket micromotor (RDTT). Figure 2 shows a General view of a diskette with a jet engine (ramjet). Figure 3 shows the construction lines of the surfaces of the diskette. Figure 4 shows two options for the power plant: option 1 with a super-flywheel, option 2 - with an electric drive of a centrifugal compressor. Figure 5 is a side view of a power plant with solid propellant rocket motors (a spiral-shaped housing with an air intake is not shown). In Fig.6 is a side view of a power plant with ramjet, in Fig.7 is a front view of the diskette, in Fig.8 is a side view, in Fig.9 is a rear view, in Fig.10 is a diskette with an ellipsoidal wing.

1-8: 1 - adaptive self-balancing disk-shaped flying wing of the diskette, 2 - line of rotation in the form of a circle, ellipse, oval, etc., 3 - the plane in which the line of rotation lies, 4 - the plane in which lies a longitudinal profile 5, 6 — the line of intersection of the planes, 7 — diameter of the line of rotation, 8 — the point of intersection of one end of the diameter 7 with the bow of the wing 1.9 — the point of intersection of the other end of the diameter 7 of the line of rotation 3 with the contour of the longitudinal profile 5, 10 — solid propellant rocket engine (figure 1, 5) (1 option), 11 - air react willow engine (Fig. 4, 6) (option 2), mainly a direct-flow compressor, 12 - a centrifugal compressor (Fig. 4), 13 - a super-flywheel (option 1) 14 - an electric motor, a motor-generator or a pneumatic drive (2, 3, 4 options ), 15 - an external drive coupling, 16 - a vacuum selection ring, 17 - a narrow part of the jet nozzle, 18 - a venturi, 19 - a nozzle, 20 - shutters, 21 - air intake slots (Figs. 5, 6), 22 - split wing (Fig. 5, 6), 23 - controlled flat nozzle combined with ailerons, flaps and elevator (Fig. 4, 5, 6), 24 - controlled tail unit (Fig. 5, 6), 25 - satellite or radio navigation ionic equipment (4), 26 - cockpit or special equipment Intelligence, 27 - the electrical current generator, 28 - fuel tank (in the future - hydride and hydrogen fuel cells to the actuator).

The implementation of the invention.

The adaptive wing is made in the form of a self-balancing flying wing 1 with a disk-shaped (variant - ellipsoidal) outline, with the coordinates of the surface on the lines of rotation 2, in the form of circles, ovals, ellipses, etc., moreover, the plane 3 in which the line of rotation lies 2, is perpendicular to plane 4 of the longitudinal profile 5, and the intersection line of the planes 6 coincides with the diameter 7 of the rotation line 2 so that one end of the diameter is located in the bow of the apparatus 8, and the other 9 on the line of intersection with the contour of the longitudinal profile 5.

The power plant is equipped with an engine - solid propellant rocket 10 (1 option), or air-jet 11 (2 option), mainly direct-flow, which is integrated with a centrifugal compressor 12 and a super flywheel 13 (1 option) or with a centrifugal compressor 12 and an electric motor, motor-generator , pneumatic actuator 14 (2, 3, 4 options), with the possibility of unwinding the super flywheel 13 from its own 14 or external drive 15, as well as by intensively blowing through the nozzles of the grooves of the super flywheel 13 with a stream of air drawn into the chamber of the super flywheel and formation of a vacuum in the narrow part 16 of the nozzle 17, or venturi 18 (variant with the solid rocket motor) during the passage therethrough of working gases flow.

The centrifugal compressor 12 is equipped with a nozzle 19 with shutters 20, which provide the possibility of changing the thrust vector from vertical to translational, and the boundary layer is controlled by the slots 21 in the split wing 22 in the upper part of the apparatus 1, which are used as the air intake of the specified centrifugal compressor.

The controls of the device are well-known - a flat controlled nozzle 23, integrated with a centrifugal compressor 12 and combined with ailerons, flaps and elevator, provides the ability to control the device according to roll and pitch. The device can be equipped with a tail unit 24, through which air is also pumped from centrifugal compressors, as well as brake flaps and other equipment.

In addition, the device can be equipped with satellite or radio navigation 25, special reconnaissance equipment 26, as well as an electric current generator 27 driven by a super flywheel 13 - to ensure the operation of all systems and the aircraft as a whole, as a functional component of the aviation complex, as well as a fuel tank 28 .

The design of the apparatus in the form of a flying wing with a round or ellipsoidal outline with surface coordinates on the lines of rotation greatly simplifies the production of the diskette, and the integration of the ramjet with a centrifugal compressor provides increased air pressure in the ramjet diffuser and makes it possible to use these lightweight, simple, economical engines both at the start and in flight mode to the object of interest.

Preparing the device for flight consists of entering data on the flight route, visual inspection of the device, selecting the launch site, installing a clip of solid propellant rocket micromotors and turning on the ignition or supplying fuel and turning on the ignition of the jet engine or supplying current to the motor generator.

Starting a light-motor unmanned vehicle “from hand”.

When the apparatus is launched using solid-propellant rocket micromotors 10, the climb is combined with the unwinding of the super-flywheel 13 from vacuum. Maneuvering on takeoff and landing is best done using radio control. Flight on a given route can be carried out according to the program through satellite systems GPS or GLONASS.

If necessary, vertical take-off and landing “from the surface” include a mechanism for changing the thrust vector, which is equipped with a centrifugal compressor 12 in the form of a nozzle 19 with shutters 20 (Fig. 4).

The flight in the area of interest is carried out with the jet (rocket) engine turned off, at low noise, from the super-flywheel 13 and the centrifugal compressor 12 integrated with it, or from the centrifugal compressor 12 with an electric or other drive 14.

The control element for maneuvering the apparatus by roll and pitch is a controlled flat nozzle 23. It is also a jet nozzle for translational movement of the apparatus.

If necessary, include the operation of the tail 24 or other known controls.

The landing is “soft” using an air cushion created by the air flow from the centrifugal compressor 12 through the nozzle 19.

The device is serviced by a single operator and can significantly reduce the number of losses among military personnel.

Claims (1)

A vertical take-off and landing diskette, mainly unmanned, with an adaptive wing and a power plant, including engines and centrifugal compressors, configured to change the thrust vector by appropriate mechanisms and control the boundary layer, characterized in that the adaptive wing is made with a round or oval outline, with the coordinates of the surface on the lines of the second order, and the plane in which each line lies is perpendicular to the plane of the contour of the longitudinal profile of the wing, and the intersection These lines are located in the bow of the diskette, the power plant includes an air-jet engine, which is integrated through a power take-off device and an air duct with a pneumatic drive of a centrifugal compressor, which is equipped with a motor generator or a super-flywheel and a nozzle with flaps for changing the thrust vector from vertical to translational, In this case, the upper part of the diskette has slits in the split wing, which are used as air intakes of centrifugal compressors and for controlling the boundary layer.

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