Method to generate thrust (versions) and apparatus to move in fluid medium (versions) |
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IPC classes for russian patent Method to generate thrust (versions) and apparatus to move in fluid medium (versions) (RU 2374133):
              
 Small-size pilotless aircraft with pulsation detonation engine and method of its operation / 2373114
Aircraft comprises airframe, wings, wings actuators and power plant with air intake, combustion chamber and nozzle apparatus. Power plant is arranged at airframe tail to make airframe the central member of circular air intake. Semi-closed detonation combustion chamber is formed by central member end face wall and nozzle apparatus inner wall and is coupled with circular air intake, adjustable circular slot-like nozzle formed byoairframe outer wall and inner wall of circular air intake. The air intake channel accommodates wings and aircraft control elements. Method of operating aircraft comprises accelerating it with subsequent switching on of engine by feeding prepared fuel mix into combustion chamber, its detonation and producing thrust. Fuel mix is fed into combustion chamber in two flows through porous end face wall and adjustable slot-like nozzle at frequency of 200 to 27000 Hz.
 Electrically driven flying vehicle / 2371355
Invention relates to aircraft engineering and can be used in fighting forest fires, escape operations etc. Proposed flying vehicle comprises fuselage, at least two air screws and one electric motor to drive aforesaid screws. Electric power for vehicle engine is arranged on the ground or aboard the vehicle, along with halyard length adjustment device, halyard one end if fastened to fuselage. Rotary element is fixed between screws on fuselage the rotary element to change direction of airflow from screws. Aforesaid rotary element is deflected by hydraulic cylinder, its working chamber communicating with device feeding working (flame damping) liquid. The latter device can also be arranged on fuselage along with fire hose with mouthpiece (communicating with fire-damping liquid source) and shielded platform with a platform with hand-rail for evacuation of victims (on perimetre of fuselage) in rescue operation. Working liquid feed via fire hose into hydraulic cylinder chamber changes airflow direction parrying the moment from damping liquid jet. That keeps up stability of flying vehicle in fire fighting. Changing airscrew RPM allows docking the flying vehicle in rescue operation.
 Centrifugal-inertial propeller for flying saucers / 2370667
Centrifugal-inertial propeller for flying saucers comprises (1), pushing surface, helical activator (2), holder with weights (9), working springs (3), arranged with the possibility of power accumulation, wheels arranged with the possibility to rotate helical activator from disk by means of Gall's chain (22) from motor (6), planks for perception of weights impact. Propeller is intended for creation of inertial force and provision of reactive force in process of action at pushing surface (15).
 Flying saucer with inertial helical actuator propeller / 2370415
Invention concerns aircrafts. Flying sauce with inertial helical actuator propeller includes light rigid transparent vault (2), inertial helical actuator propeller, low-capacity internal combustion motor, and work spring (8).
 Hypersonic airplane and rocket propulsion system of airplane / 2368540
Airplane comprises fuselage, nose conical portion, wings, stabilisers, fuel tanks, rocket propulsion system and pipelines for supply of fuel components to it. Rocket propulsion system is installed in back part of fuselage and comprises turbopump set, two combustion chambers and flat central body in between. Rocket propulsion system of airplane comprises turbopump set with impellers of oxidant and fuel installed on shaft, turbine, start-up turbine and coaxially installed gas generator and combustion chamber. Two combustion chambers have been used, and flat central body is installed in between.
 Aircraft of plate type / 2368539
Aircraft comprises plate body, cabin with control panel, installed in the body centre in its upper part. Aircraft also comprises central and lateral rocket engines, nozzles of which are inverted downwards, fuel tanks installed in peripheral zone of body, and chassis. Body of apparatus is equipped with two gravitational masses that rotate in opposite directions in single plane and interacting with inclined guide of body, and drive of rotating masses is connected to central rocket engine. Lateral rocket engines are installed with the possibility of rotation around longitudinal axis of body.
 Military-space airplane with aviation-based fighting laser / 2366593
Airplane comprises fuselage, front and back wings, gas-turbine engines installed on wings, and rocket engine installed in back part of fuselage. On upper part of fuselage along its longitudinal axis there is aviation-based fighting laser installed, which is connected by air sampling pipelines that comprises controller valve to at least one gas-turbine engine and with rocket engine. Laser is arranged as gas-dynamic, comprises optical head and exhaust system, is connected by air sampling pipeline comprising controller valve to turbo-pump set downstream turbine.
 Flying source / 2365522
Invention relates to aircraft engineering and can be used in designing new flight vehicles. Proposed flight vehicle consists of dome-shaped compartment, partition, power plant, reduction gear, rotor, vertical shaft, bearing support, coil and three bearing wheels. A build-up ring-like wing has its fixed wing attached power plant, right below aforesaid partition ceiling. The said build-up movable wing is integrated with the rotor. Note that it has its ribs rigidly fixed to the hub and articulated with rotor blades.
 "flying stand-m" ring wing peripheral drive / 2364552
Invention relates to flying stands. Proposed flying stand peripheral drive consists of engines (2), clutch and reduction gear box and is arranged above ring wings (4). Drive output shaft supports represents gear wheel (2) of chain transmission to transmit rotation via roller chain (3) to rim (5) of ring wheel (4). Aforesaid drive element can also represent a belt drive pulley to transmit rotation via drive belt to the pulley that represents the rim of ring wheel. Drive element can represent, as well, a gear wheel transmission planar to the plane of ring wheel rotation and transmitting power to ring wheel via gear wheel that makes the rim of the said wing.
 Cargo-and-passenger flying craft with inertial helical-activator propulsor / 2363623
Invention relates to aircraft engineering. Proposed flying craft consists of the frame to throw pilot and cargo upward, internal combustion engine and propulsor. The latter comprises activator and working spring to be compressed and released by helical activator, dome and slightly bending strips designed to produce inertial force and to push air away so that to produce reactive force, when helical activator makes 3 to 5 rpm drive by ICE.
 Transport aircraft / 2287454
Proposed aircraft has fuselage, two half-wings, jet engine, vertical and horizontal stabilizers and landing gear. Each half-wing has through passages of rectangular section which are parallel relative to each other along half-wing span. Each through passage has lower passage whose inlet hole is located on lower surface of half-wing; upper passage is narrower as compared with lower passage and its outlet hole is located on upper surface of half-wing.
 Method of change of aerodynamic characteristics of subsonic flying vehicle and device for realization of this method / 2282563
Proposed method consists in taking preheated gas from gas source and bringing it to flying vehicle surface followed by blowing-out jet of preheated mixture of air and combustion products of engine plant at subsonic velocity through local blowing-out zones on lower and/or upper surfaces of flying vehicle wing into external incoming air flow. Besides that, air is taken from air intake or from engine plant compressor and is fed over hermetic mains through adjusting members at supersonic velocity through supersonic nozzles which are flat in configuration from leading edge of wing over lower surface in way of wing chord, thus overlapping the subsonic gas jets escaping from local blowing-out zones by high-velocity air flow at Mach number more than 0.7. Device proposed for realization of this method has fuselage, power plant, engine plant, fuel system, wing and control profiles. Engine plant is connected by hermetic lines with local blowing-out zones located on surfaces of wing and control profiles. Mounted on leading edge of wing lower surface are supersonic nozzles whose external surfaces are located at level of wing surface.
 Method for variation of aerodynamic characteristics of flight vehicle and device for its realization / 2274585
The device is designed for a flight vehicle having a fuselage, jet engine, fuel system, carrying planes and control sections. The device has a source of offtaken gas, which through sealed lines is connected to the zones of local blowing-out of gas to the boundary layer of air flow on the surfaces the flight vehicle. Each zone of local blowing-out of gas is made on the surface of the carrying plane or fuselage, or control sections with a penetrable porous insert with a cross-sectional area of the ducts in the porous insert within 50 to 60% of the area of the insert proper by 10-15 times less than the distance between the adjacent inserts, a flat rectangular slot for a break of the boundary layer is made before each insert and in parallel with it.
 Method of change of aerodynamic characteristics of flying vehicle control surfaces and device for realization of this method / 2272746
Proposed method includes bleeding part of preheated gas from gas source followed by delivery of bled gas to control surfaces of rudder, upper and lower surface of flying vehicle elevator.
 Vertical takeoff and landing flying vehicle / 2266846
Proposed flying vehicle is provided with jet power plant located in center of flat wing round in plan. Power plant includes turbocompressors 13, bypass valves 14, receiver 15, adjusting valves 16 and four-section jet engine used for forming circular radially diverging air jet. Sections 17 of engine are designed for independent control during operation and are separated from one another by receiver. Upper part of body is designed for performing function of wing round in plan.
 The method of controlling the flight of a managed aircraft and managed aircraft / 2165585
The invention relates to techniques for aircraft
 Mover / 2120396
 Aerodynamic profile / 2086468
The invention relates to the field of aeronautical engineering and can be used in the layout of the wing
 Way vertical travel and hang aircraft in the air / 2059534
The invention relates to aircraft and can be used when creating new aircraft vertical takeoff and landing
 Water-jet propeller for submarine vessel / 2343087
Water-jet propeller for submarine vessel contains at least one liquid flow accelerator in propeller nozzle coaxial with stern extremity of vessel and includes at least two nozzles on same axle. At least one nozzle is coaxially introduced into next nozzle in direction of fluid movement with formation of cavity in between nozzles. At that, at least one cavity is communicated with fluid supply and suction devices. At least in one cavity with fluid supply and suction devices liquid media ionisation means are located. All cavities are supplied with pressure gauges and inlet and outlet jet nozzles have speed sensors. Cavities with fluid supply and suction devices have electrodes installed for electrohydraulic impacts in liquid media.
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FIELD: aircraft engineering and ship building. SUBSTANCE: set of inventions relates to apparatuses moving in air or water. Proposed apparatus comprises aerodynamic section wheel with top convex surface, fluid medium high-pressure source communicates with high-pressure jet generator arranged above the wing convex surface. Six design versions of proposed apparatus are distinguished for by the design of aforesaid high-pressure jet generator. Method of generating thrust consists in using high-pressure jet generator arranged above the wing convex surface. Five versions of the method are distinguished for by the design of aforesaid high-pressure jet generator. EFFECT: higher efficiency. 11 cl, 16 dwg
The invention relates to the field of traffic engineering, and in particular to methods provide traction and vehicles with wing aerodynamic section, and can be used as vehicles to move in a fluid environment: air and water. At the present time to produce thrust in a gas (air) and liquid (water) environments use the propulsion of the following types: - capacity, the average density which is less than the density of the environment: airships, balloons, tanks submarines. Such thrusters are able to create only vertical rod (Archimedes law); - jet engine, which is based on the release of stored working fluid or fence, acceleration and subsequent release to the environment material (Newton's law); - fan (propellers of ships), which is based on the interaction of the inclined plane and protection during their relative movement. - wing aircraft (screws helicopters), which is based on the effect of lowering the pressure in the environment at higher speed (environment) movement caused by the geometry of the wing. To ensure low pressure above the wing of an airplane or helicopter, you need to set them in motion relative to the air (lift force can occur when the wind, but that is not controlled flight). As the nearest the tax (prototype) selected method of creating thrust and the aircraft vertical takeoff and landing (flying saucer) patent of Russian Federation №2151717 from 02.03.1998. publ. 27.06.2000. The way to create thrust is characterized by the direction of the pressure jets of fluid (air flow) over (tangent) of the upper convex surface of the wing (disk) aerodynamic section for intensive ventilation of the upper surface of the disk. Used in this invention is a method for producing thrust (Coanda effect) is characterized by the fact that the tangent of the wing aerodynamic section (disk with the upper spherical surface) create a steady stream of air that blows on the upper surface of the wing. According to the Bernoulli law is created above the apparatus evacuated space and the vertical thrust upwards. While above the upper surface of the wing has a high-pressure fan of the two mirror located to each other centrifugal screw rotation coaxially in opposite directions. In addition, the fan is equipped with a diffuser in the form of an annular damper with a spiral channel to change the thrust vector and inclusion in work mode of translational motion of the plates. Due to the fact that the increase in mass due to the suction effect is negligible, the method and apparatus have low efficiency create a thrust. The technical objective of the proposed solutions is to increase the efficiency to create thrust. The problem is solved by a group of inventions, the combined single image is defined by the plan. The group consists of: - a way to create thrust, namely in the direction of the nozzle pressure jets of fluid tangentially to the upper convex surface of the wing aerodynamic section, in which according to the invention moves the nozzle at an angle relative to the direction of pressure jets of fluid that vortices capture the surrounding fluid environment; apparatus for moving in a fluid medium containing the wing aerodynamic cross-section with an upper convex surface, a source of high pressure fluid, interconnected with means for forming a pressure jets from nozzles directed tangentially to the upper convex surface of the wing, which according to the invention it is provided with a rotation drive nozzles mentioned means, which is made in the form of fixed coaxially to the longitudinal axis of the wing rotor with a hollow axle with the possibility of the formation pressure jets with eddies; - a way to create thrust, namely in the direction of the nozzle pressure jets of fluid tangentially to the upper convex surface of the wing aerodynamic section, in which according to the invention sequentially change the place of expiration pressure jets of fluid that vortices capture the surrounding fluid environment; apparatus for moving in a fluid medium containing wing aerodyn the economic section and an upper convex surface, the source of high pressure fluid, interconnected with means for forming a pressure jets from nozzles directed tangentially to the upper convex surface of the wing, which according to the invention the said means in the form of block stationary nozzles connected to a pulsed air jet engine and simulates the movement of the nozzles around the circumference of the possibility of forming a pressure jets with eddies; - a way to create thrust, namely in the direction of the nozzle pressure jets of fluid over the upper convex surface of the wing aerodynamic section, in which according to the invention move the nozzle back and forth in the plane of the longitudinal axis of the wing so that the pressure of the jet of fluid vortices capture the surrounding fluid environment; apparatus for moving in a fluid medium containing the wing aerodynamic cross-section with an upper convex surface, a source of high pressure fluid, interconnected with means for forming a pressure jets over the upper convex surface of the wing, which according to the invention the means for forming a pressure jets made in the form prescribed in the plane of the longitudinal axis of the wing unit with hollow shaft and nozzles made with the possibility of the formation pressure jets with eddies and United the and mechanism for reciprocating movement; apparatus for moving in a fluid medium containing the wing aerodynamic cross-section with an upper convex surface, means for forming a pressure jets over the upper convex surface of the wing, which according to the invention the means for forming a pressure jets made in the form of hinged and connected to a pulsed air jet curved nozzles made with the possibility of the formation pressure jets with eddies and return to its original position by means of springs; - a way to create thrust, namely in the direction of the nozzle pressure jets of fluid over the upper convex surface of the wing aerodynamic section, in which according to the invention mimic in the plane of the longitudinal axis of the wing place of the reciprocating discharge from nozzles pressure jets of fluid that vortices capture the surrounding fluid environment; apparatus for moving in a fluid medium containing the wing aerodynamic cross-section with an upper convex surface, the tool with nozzles for forming the pressure of the jets over the upper convex surface of the wing, which according to the invention the means for forming a pressure jets made in the form prescribed in the plane of the longitudinal axis of the wing unit stationary nozzles connected with pulsating in which USNO-reactivity engine with the possibility of reciprocating to change the place of discharge from nozzles pressure jets of fluid, which vortices capture the surrounding fluid environment; - a way to create thrust, namely in the direction of the nozzle pressure jets of fluid over the upper convex surface of the wing aerodynamic section, in which according to the invention the nozzles pressure jets of fluid are reported oscillatory movement in a plane parallel to the longitudinal axis referred to the wing so that the pressure of the jet of fluid vortices capture the surrounding fluid environment; apparatus for moving in a fluid medium containing the wing aerodynamic cross-section with an upper convex surface, a source of high pressure fluid, interconnected with means for forming a pressure jets and direction over the upper convex surface of the wing, which according to the invention the means for forming a pressure jets and designed in the form of fixed perpendicular to the longitudinal axis of the wing rotor with a hollow axle and nozzles, mounted symmetrically on the top and at an angle to the end face with the ability to capture vortices surrounding the fluid jet. The invention is based on the open author Kovalchuk VA phenomenon lowering the pressure in the area of movement of the jets formed by the motion of the source of the jet at an angle to its direction. This after jet the author called " the expanded stream"(figure 1). "Expanded jet is formed at the source of the jet, and the sequential change its expiry i.e. when "imaginary" motion of the source. The proposed methods provide traction allows to form nozzles for deployed twisted into a spiral jet of low pressure inside, which when the centrifugal movement to the perimeter of the wing involve (seize and carry away) a large volume of surrounding fluid in a swirling motion, greatly reducing the pressure above the wing (without its movement in the environment). Thus, increasing the efficiency of traction, providing the possibility of obtaining high speeds of movement. After the jets and simultaneous rotation of rotor nozzles, reciprocating or oscillating motion of the nozzles in the area of the expanded jet generation is a system of infinite vortex cord, moving from the nozzle to the peripheral portion of the wing. Vortices have a much greater potential energy than jet of fluid, and when the movement of the vortex cords seize and carry away large mass (number) of the surrounding air, resulting in lower air pressure above the wing. The pressure difference above and below the wing leads to the motion of the vehicle. The absence of mechanical elements impact the design of the device simplifies the design and results is it to reduce size and increase reliability, that provides the opportunity to make takeoff and landing and movement in any direction without the risk of damage due to contact with surrounding objects. Conducted patent research did not reveal identical technical solutions that allows to draw a conclusion about the novelty and technical level of the proposed technical solutions. The domestic industry has all the tools (materials, technology, equipment)required to manufacture multifunctional and wide use of the present apparatus. The essence of the invention is illustrated by drawings, where: figure 1 - scheme of education "deployed" jets; figure 2 - diagram of the formation of vortices (top view); figure 3 - diagram of the formation of vortices (longitudinal section); figure 4 is a General view of the means for the formation of vortices (with the rotor and the radial location of the nozzles); figure 5 - General view of the means for forming a vortex jets (with the rotor and location of the nozzles at an angle); figure 6 - General view of the apparatus with the unit stationary nozzles, imitating the movement of the nozzles around the circumference; 7 is a General view of the means for the formation of vortices (with a reciprocating nozzles); on Fig - General view of the means for the formation of vortices (with imitation reciprocating motion of the nozzles); figure 9 is a General view among the STV for the formation of vortices (with a reciprocating curved nozzle with spring); figure 10 is a General view of the means for the formation of vortices (with oscillatory movement of the nozzles inclined to the end face of the rotor); figure 11 is a General view of the wing in the form of a spherical segment; on Fig - General view of the wing in the form of a spherical segment with a hole in the Central part; on Fig diagram of the direction of pressure jets when performing a wing in the form of a spherical segment with a hole in the Central part; on Fig - General view of the wing in the form of two spherical segments; on Fig - General view of the apparatus with the wing in the form of a rectangular curved plate (with arcuate bend in section); on Fig - General view of the apparatus with the wing in the form of a triangular curved plates with arcuate bend in section). In the proposed invention uses a unique property of the gas vortices 1 draw (attach) when moving very large mass of the surrounding fluid medium 2 (figure 2 and 3), which is caused by the presence of sparse space in the Central part of the vortex 1. When vortices move 1 from the center to the edge 3 of the wing 4 is the capture and entrainment of large masses of air 2, which leads to lower pressure above the wing 4. The effect of the occurrence of thrust occurs at the source pressure of the jet 5 in one direction (along the circle), and reciprocating in the plane of the longitudinal axis of the wing 4 and the oscillating jet, the assets in the plane parallel to the longitudinal axis of the wing 4. The method of creation of thrust according to claim 1 of the formula is in the direction of the nozzle pressure of the jet 5 of fluid tangentially to the upper convex surface 6 of the wing aerodynamic section 4, and the nozzle 7 is moved at an angle relative to the direction of pressure of the jet 5 of fluid that vortices 1 capture the surrounding fluid environment. The apparatus according to claim 2 of the formula to move in a fluid medium using the above-proposed method contains the wing aerodynamic section 4 with the upper convex surface 6, a source of high pressure 8 fluid, interconnected with means for forming a pressure jets 5 of the nozzle 7 is directed tangentially to the upper convex surface 6 of the wing 4, provided with a rotation drive nozzles 7, which is made in the form of fixed coaxially to the longitudinal axis of the wing rotor 9 actuator 10 and a hollow shaft (not shown), with the possibility of the formation pressure jets 5 vortices 1 (figure 4 and 5). The source of high pressure 8 fluid made in the form of compressor (centrifugal or axial). The method of creation of thrust according to claim 3 of the formula is in the direction of the nozzles 7 of the pressure jet 5 of fluid tangentially to the upper convex surface 6 of the wing aerodynamic section, and sequentially change the place of expiration pressure jet 5 of fluid that war the mi 1 capture the surrounding fluid environment. The apparatus according to claim 4 of the formula to move in a fluid environment on the proposed in section 3 the method comprises a wing aerodynamic section 4 with the upper convex surface 6, a source of high pressure fluid, interconnected with means for forming a pressure jets 5 of nozzles directed tangentially to the upper convex surface 6 of the wing 4. The above-mentioned means for forming a pressure jets 5 made in the form of a block fixed nozzle 11 connected to a pulsed air jet engine 12 and simulating the movement of the nozzles around the circumference of the possibility of forming a pressure jets 5 vortices 1 (Fig.6). In the apparatus according to claim 2 and claim 4 of the formula wing aerodynamic section 4 may be performed according to the type plate in the form of a spherical segment 13 (11), the spherical segment 13 with an opening 14 in the Central part (Fig and 13) or in the form of two spherical segments 15 (Fig). The method of creation of thrust according to claim 5 of the formula is in the direction of the nozzles 7 of the pressure jet 5 of fluid over the upper convex surface 6 of the wing aerodynamic section 4, while moving the nozzle 7 reciprocating in the plane of the longitudinal axis of the wing 4 so that the pressure of the jet 5 of fluid vortices 1 capture the surrounding fluid environment. The apparatus according to claim 6 of the formula to move in a fluid environment on the proposed VP method contains the wing aerodynamic section 4 with the upper convex surface 6, the source of high pressure fluid medium 8 is connected with means for forming a pressure jets 5 over the upper convex surface of the wing 4, wherein the said means for forming a pressure jets 5 made in the form prescribed in the plane of the longitudinal axis of the wing 4 of block 16 with a hollow shaft (not shown) and the nozzles 7, made with the possibility of formation pressure jets 5 vortices 1 and connected to the mechanism for reciprocating movement (not shown) (Fig.7). The source of high pressure 8 fluid made in the form of compressor (centrifugal or axial). The apparatus according to claim 7 of the formula to move in a fluid environment on offer in claim 5, the method comprises a wing 4 aerodynamic cross-section with an upper convex surface, the tool with nozzles for forming the pressure of the jets over the upper convex surface 6 of the wing 4, wherein the said means for forming a pressure jets 5 made in the form of hinged and connected to a pulsed air jet engine 12 curved nozzles 17 which has a capability of forming a high pressure jets 5 vortices 1 and return to its original position by means of springs 18 (Fig.9). A method of creating a draught of claim 8, the formula is in the direction of the nozzles 7 of the pressure jet 5 of fluid above the upper convex the surface 6 of the wing aerodynamic section, thus mimic in the plane of the longitudinal axis of the wing place reciprocating the expiration of the nozzles 7 of the pressure jet 5 of fluid that vortices 1 capture the surrounding fluid environment. The apparatus according to claim 9 of the formula to move in a fluid environment on the proposed in item 8, the method comprises a wing aerodynamic section 4 with the upper convex surface 6, the means for forming a pressure jets 5 over the upper convex surface 6 of the wing 4, wherein the said means for forming a pressure jets 5 made in the form prescribed in the plane of the longitudinal axis of the wing 4 block 19 fixed nozzles connected to a pulsed air jet engine 12 with the possibility of reciprocating to change the place of discharge from nozzles pressure jet 5 of fluid that vortices 1 capture the surrounding fluid environment (Fig). In the apparatus according to claim 9 wing aerodynamic section 4 may be made in the form of a rectangular curved plate 20 with the cross-section in the form of an arc and block 12 (Fig) or in the form of a triangular plate 21 with a curved bend in the cross section (Fig). In addition, you can run the wing in the form of a spherical segment 13 (11), a spherical segment with a hole in the Central part 14 (Fig and 13) or in the form of two spherical segments 15 (Fig). A method of creating a draught of claim 10 formalizable in the direction of the nozzle pressure jet 5 of fluid over the upper convex surface 6 of the wing aerodynamic section 4, in this case, the nozzles pressure jet 5 of fluid inform oscillatory movement in a plane parallel to the longitudinal axis mentioned wing 4 so that the pressure of the jet 5 of fluid vortices 1 capture the surrounding fluid environment. The apparatus according to claim 11, formulas to move in a fluid environment on the proposed method in clause 10 contains the wing aerodynamic section 4 with the upper convex surface 6, a source of high pressure 8 fluid, interconnected with means for forming a pressure jets and sending them over the top of the convex surface 6 of the wing 4, wherein the said means for forming a pressure jets and designed in the form of fixed perpendicular to the longitudinal axis of the wing rotor 22 with a hollow shaft (not shown) and the nozzles 23, mounted symmetrically on the end face 24 at an angle to the end face 24 with the ability to capture vortices 1 environmental fluid jet 5 (figure 10). The source of high pressure 8 fluid made in the form of compressor (centrifugal or axial), and the wing may be of any shape mentioned above. The apparatus to move in a fluid environment are as follows. The apparatus according to claim 2 of the formula (4). Include the source of the high pressure 8 and the rotor 10 with nozzles 7. The pressure of the jet 5 of fluid (air or water) flows to the nozzles 7 of the apparatus. The result is e for moving the nozzles are formed pressure jet 5 vortices 1. The apparatus according to claim 6 of the formula (7). Include the source of the high pressure 8 and the mechanism for reciprocating movement of the nozzles (not shown). The pressure of the jet 5 of fluid (air or water) flows to the nozzles 7 of the apparatus. As a result, movable nozzles 7 are formed pressure jet 5 vortices 1. The apparatus according to claim 11 of formula (figure 10). Include the source of the high pressure 8, interconnected with inclined nozzles 23, mounted symmetrically on the end face 24 of the rotor. The pressure of the jet at the end of the nozzles perform the rotation of the rotor 22, the nozzle 23 undergo vibrational motion relative to the wing 4. As a result, movable nozzles are formed pressure jet 5 vortices 1. The apparatus 4 of the formula (6) when simulating the movement of the nozzles around the circumference of the works in the following way. Included pulsing jet engine 12, and is formed of a jet under pressure in a given sequence are sent to the unit stationary nozzles 11 located on the cylindrical surface of the block. As a result, nozzles, imitating the movement of the nozzles around the circumference, are formed in the pressure of the jet 5 vortices 1. The apparatus 9 of the formula (Fig, 15 and 16) when simulating the reciprocating movement of the nozzles are as follows. Included pulsing jet engine, and the priori jet pressure is directed to the block 19 (Fig) or blocks (Fig and 16) fixed nozzles, located on the same line (linear), where sequence changes the place of expiration pressure jets from the nozzles. In the pressure of the jet 5 are formed with vortices 1. The apparatus according to claim 7 of the formula (Fig.9) Included a pulsing jet engine 12 connected to the curved nozzles 17, configured to return to its original position by means of springs 18. In the nozzle do reciprocating motion, which ensures formation pressure jet 5 vortices 1. When vortices move 1 from the center to the edge 3 of the wing 4 is the capture and entrainment of large masses of air 2, which leads to lower pressure above the wing 4. The apparatus, in any of the stated options) rises and moves in the right direction. The author conducted laboratory tests of models with various forms of the wing, which confirm the efficiency of the apparatus to create traction and displacement in any direction. If necessary, the author may submit photos and videos. 1. The way to create thrust, namely in the direction of the nozzle pressure jets of fluid tangentially to the upper convex surface of the wing aerodynamic section, wherein moving the nozzle at an angle relative to the direction of pressure jets of fluid that vortices zahwah is to see the surrounding fluid environment. 2. The apparatus to move in a fluid medium containing the wing aerodynamic cross-section with an upper convex surface, a source of high pressure fluid, interconnected with means for forming a pressure jets from nozzles directed tangentially to the upper convex surface of the wing, characterized in that it is provided with a rotation drive nozzles mentioned means, which is made in the form of fixed coaxially to the longitudinal axis of the wing rotor with a hollow axle with the possibility of the formation pressure jets with eddies. 3. The way to create thrust, namely in the direction of the nozzle pressure jets of fluid tangentially to the upper convex surface of the wing aerodynamic section, characterized in that sequentially change the place of expiration pressure jets of fluid that vortices capture the surrounding fluid environment. 4. The apparatus to move in a fluid medium containing the wing aerodynamic cross-section with an upper convex surface, a source of high pressure fluid, interconnected with means for forming a pressure jets from nozzles directed tangentially to the upper convex surface of the wing, characterized in that the said means is made in the form of a block fixed nozzles connected to a pulsed air jet engine and they shall arousih movement of the nozzles around the circumference of the possibility of forming a pressure jets with eddies. 5. The way to create thrust, namely in the direction of the nozzle pressure jets of fluid over the upper convex surface of the wing aerodynamic section, characterized in that the moving nozzle reciprocating in the plane of the longitudinal axis of the wing so that the pressure of the jet of fluid vortices capture the surrounding fluid environment. 6. The apparatus to move in a fluid medium containing the wing aerodynamic cross-section with an upper convex surface, a source of high pressure fluid, interconnected with means for forming a pressure jets over the upper convex surface of the wing, wherein the means for forming a pressure jets made in the form prescribed in the plane of the longitudinal axis of the wing unit with hollow shaft and nozzles made with the possibility of the formation pressure jets with eddies and connected to the mechanism for reciprocating movement. 7. The apparatus to move in a fluid medium containing the wing aerodynamic cross-section with an upper convex surface, the tool with nozzles for forming the pressure of the jets over the upper convex surface of the wing, wherein the means for forming a pressure jets made in the form of hinged and connected to a pulsed air jet curved Zopa is, made with the possibility of formation pressure jets with eddies and return to its original position by means of springs. 8. The way to create thrust, namely in the direction of the nozzle pressure jets of fluid over the upper convex surface of the wing aerodynamic section, wherein the mimic in the plane of the longitudinal axis of the wing place of the reciprocating discharge from nozzles pressure jets of fluid that vortices capture the surrounding fluid environment. 9. The apparatus to move in a fluid medium containing the wing aerodynamic cross-section with an upper convex surface, means for forming a pressure jets over the upper convex surface of the wing, wherein the means for forming a pressure jets made in the form prescribed in the plane of the longitudinal axis of the wing unit stationary nozzles connected to a pulsed air-breathing engine with the possibility of reciprocating to change the place of discharge from nozzles pressure jets of fluid that vortices capture the surrounding fluid environment. 10. The way to create thrust, namely in the direction of the nozzle pressure jets of fluid over the upper convex surface of the wing aerodynamic section, characterized in that the nozzles discharge jets of fluid inform vibrations is positive movement in a plane parallel to the longitudinal axis mentioned wing so that pressure jet of fluid vortices capture the surrounding fluid environment. 11. The apparatus to move in a fluid medium containing the wing aerodynamic cross-section with an upper convex surface, a source of high pressure fluid, interconnected with means for forming a pressure jets and direction over the upper convex surface of the wing, wherein the means for forming a pressure jets and designed in the form of fixed perpendicular to the longitudinal axis of the wing rotor with a hollow axle and nozzles, mounted symmetrically on the top and at an angle to the end face with the ability to capture vortices surrounding the fluid jet.
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