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The invention relates to the field of transportation technology, namely to methods for developing thrust and an apparatus with an aerodynamic cross-section wing, which can be used for movement in fluid, air and water.
Currently, the following types of propulsion devices are used for developing thrust in gas (air) and liquid (water) media:
The closest analogue (prototype) is a method for developing thrust and a vertical takeoff and landing aircraft (a flying saucer) per RF patent No. 2151717 of 03.02.1998 published 06.27.2000. This method for developing thrust is characterized by the direction of pressure jets of fluid (air flow) over (along a tangent) the upper convex surface of an aerodynamic cross-section wing (disk) for intensive airflow over the disk's upper surface.
The method for developing thrust used in the invention (the Coanda effect) is characterized by the fact that uniform air flow is created along the tangent to an aerodynamic cross-section wing (a disk with a spherical upper surface), and blowing over the wing's upper surface. According to the Bernoulli law, a rarefied space is created and vertical upward thrust is developed. Herein, a high pressure fan is installed above the wing's upper surface. The fan comprises two centrifugal rotors mirroring each other and rotating coaxially in opposite directions. In addition, the fan has a diffuser in the form of an annular choke with a helical channel for changing the thrust vector and turning it on in the mode of translational motion of the plate. Because weight gain caused by the suction effect is insignificant, the method and apparatus have low efficiency of developing thrust.
The technical objective of the claimed solutions is to increase the efficiency of developing thrust.
The stated objective is achieved by a group of inventions united by a common inventive concept. The group comprises:
The invention is based on the phenomenon, discovered by the author V. A. Kovalchuk, of reduction of pressure in the area of movement of jets that form when the jet source moves at an angle in the direction of the jet. The author has called such jet exhaust a “spread jet” (
The proposed methods for developing thrust make it possible to form helical spread jets, after the nozzles, with low pressure inside which, in centrifugal movement toward the wing perimeter, draw (capture and carry away) into vortex motion a large volume of surrounding fluid, substantially reducing the pressure under the wing (without wing movement in the medium). Thus, thrust efficiency increases, making it possible to get high motion speeds.
During exhaust of the jets and simultaneous rotation of the rotor with nozzles, and reciprocating or oscillating movement of the nozzles in the “spread jet” area, a system of infinite vortex jets moving from the nozzles to the peripheral area of the wing is generated. The vortices have a much higher energy potential than jets of fluid, and during movement, vortex strings capture and carry away large masses (amount) of ambient air resulting in reducing the air pressure under the wing. The pressure differential above and under the wing results in movement of the apparatus.
Because the apparatus has no mechanical elements acting on the medium, it simplifies the apparatus' design and results in reducing its dimensions and increasing its reliability, which makes it possible to perform takeoff and landing in any direction without risking damage in the case of contact with surrounding objects.
Patent research reveals no identical technical solutions, which infers novelty and a level of technicality of the claimed technical solutions.
The domestic industry has all necessary means (materials, technology and equipment) for the manufacture and widespread multifunctional implementation of the proposed apparatus.
The subject of the patent is a group of inventions relating to an apparatus for movement in air and water. The apparatus for movement in fluid comprises an aerodynamic cross-section wing with a convex upper surface, and a source of high pressure fluid interconnected with a means for forming pressure jets over the convex upper surface of the wing. Six embodiments of the apparatus are characterized by the design of the means for forming pressure jets. The method for developing thrust consists of using the means for forming pressure jets over the convex upper surface of the wing. Five embodiments of the method are characterized by the design of the means for forming pressure jets. The group of inventions is aimed to increase efficiency.
The essence of the inventions is explained in the drawings where:
The proposed inventions use a unique feature of gas vortices 1 during their movement to pull in (annex) very large masses of surrounding fluid 2 (
The method for developing thrust per claim 1 consists in directing fluid pressure jets 5 from the nozzles along a tangent to the convex upper surface 6 of the aerodynamic cross-section wing 4, wherein the nozzles 7 are moved at an angle relative to the direction of the fluid pressure jets 5 which capture surrounding fluid by means of vortices 1.
The apparatus per claim 2, and with movement as per the method proposed above, comprises an aerodynamic cross-section wing 4 with a convex upper surface 6 and a source 8 of high pressure fluid interconnected with a means for forming pressure jets 5 from the nozzles 7 directed along a tangent to the convex upper surface 6 of the wing 4; the source 8 has a drive for rotating the nozzles 7 made in the form of a rotor 9 installed coaxially with the wing's longitudinal axis, with a drive 10 and a hollow axle (not shown), and which is capable of forming pressure jets 5 with vortices 1 (
The source 8 of high pressure fluid is made in the form of a (centrifugal or axial) compressor.
The method for developing thrust as per claim 3 consists in directing fluid pressure jets 5 from the nozzles 7 along a tangent to the convex upper surface 6 of the aerodynamic cross-section wing and, in doing this, sequentially changing the points of exhaust of fluid pressure jets 5 that capture surrounding fluid by means of vortices 1.
The apparatus as per claim 4, for movement in fluid as per the method proposed in claim 3, comprises an aerodynamic cross-section wing 4 with a convex upper surface 6 and a source of high pressure fluid interconnected with a means for forming pressure jets 5 from the nozzles directed along a tangent to the convex upper surface 6 of the wing 4. Said means for forming pressure jets 5 is made in the form of a bank of stationary nozzles 11 which are connected to a pulsating air breathing engine 12 and which simulate a circular movement of the nozzles, and capable of forming pressure jets 5 with vortices 1 (
In the apparatus as per claims 2 and 4, an aerodynamic cross-section wing 4 can be made as a plate in the form of a spherical segment 13 (
The method for developing thrust as per claim 5 consists in directing fluid pressure jets 5 from the nozzles 7 over the convex upper surface 6 of an aerodynamic cross-section wing 4, while the nozzles 7 are set to reciprocating movement in the plane of the longitudinal axis of the wing 4 so that fluid pressure jets 5 capture surrounding fluid by means of vortices 1.
The apparatus as per claim 6, for movement in fluid as per the method proposed in claim 5, comprises an aerodynamic cross-section wing 4 with a convex upper surface 6 and a source 8 of high pressure fluid interconnected with a means for forming pressure jets 5 above the convex upper surface of the wing 4, wherein said means for forming pressure jets 5 is made in the form of a bank 16 with a hollow axle (not shown) and nozzles 7. The bank 16 is installed in the plane of the longitudinal axis of the wing 4, and the nozzles are capable of forming pressure jets 5 with vortices 1 and are connected to a reciprocating motion mechanism (not shown) (
The source 8 of high pressure fluid is made in the form of a (centrifugal or axial) compressor.
The apparatus as per claim 7, for movement in fluid as per the method proposed in claim 5, comprises an aerodynamic cross-section wing 4 with a convex upper surface 6, a means with nozzles for forming pressure jets over the convex upper surface 6 of the wing 4, wherein said means for forming pressure jets 5 is made in the form of curved nozzles 17 that are hinge-mounted, connected to a pulsating air breathing engine 12, and capable of forming pressure jets 5 with vortices 1 and reseting by means of springs 18 (
The method for developing thrust as per claim 8 consists in directing fluid pressure jets 5 from the nozzles 7 over the convex upper surface 6 of the aerodynamic cross-section wing, while simulating, in the wing's longitudinal axis plane, the point of reciprocating exhaust from the nozzles 7 of fluid pressure jets 5 that capture surrounding fluid by means of vortices 1.
The apparatus as per claim 9, for movement in fluid as per the method proposed in claim 8, comprises an aerodynamic cross-section wing 4 with a convex upper surface 6, and a means for forming pressure jets 5 over the convex upper surface 6 of the wing 4, wherein said means for forming pressure jets 5 is made in the form of a bank 19 of stationary nozzles installed in the plane of the longitudinal axis of the wing 4, the bank connected to a pulsating air breathing engine 12 capable of reciprocatingly changing the point of exhaust from the nozzles of fluid pressure jets that capture surrounding fluid by means of vortices 1 (
In the apparatus as per claim 9, an aerodynamic cross-section wing 4 can be made in the shape of a curved rectangular plate 20 with a cross-section in the form of an arc (
The method for developing thrust as per claim 10 consists in directing fluid pressure jets 5 from nozzles over the convex upper surface 6 of an aerodynamic cross-section wing 4, wherein the nozzles of fluid pressure jets 5 are set to oscillating movement in the plane parallel to the longitudinal axis of said wing 4 so that the fluid pressure jets 5 capture surrounding fluid by means of vortices 1.
The apparatus as per claim 11, for movement in fluid as per the method proposed in claim 10, comprises an aerodynamic cross-section wing 4 with a convex upper surface 6 and a source 8 of high pressure fluid interconnected with a means for forming and directing pressure jets over the convex upper surface 6 of the wing 4, wherein said means for forming pressure jets is made in the form of a rotor 22 with a hollow axle (not shown) and nozzles 23 installed perpendicularly to the wing's longitudinal axis, symmetrically, on an end face 24 at an angle to the end face 24, and capable of capturing the surrounding fluid with pressure jets 5 by means of vortices 1 (
The source 8 of high pressure fluid is made in the form of a (centrifugal or axial) compressor, while the wing can have any of the above shapes.
The apparatus for movement in fluid work as follows.
Apparatus as per claim 2 (
Apparatus as per claim 6 (
The apparatus per claim 11 (
The apparatus as per claim 4 (
In the case of simulated reciprocating movement of nozzles, the apparatus per claim 9 (
The apparatus per claim 7 (
When vortices 1 move from the center to the edge 3 of the wing 4, large masses of air 2 are captured and carried away, causing a reduction of pressure under the wing 4. The apparatus (in any of the claimed embodiments) lifts, and moves in the required direction.
The author conducted tests of laboratory models of the apparatus with various wing shapes; the tests confirmed the apparatus' ability to develop thrust and move in any direction.
Number | Date | Country | Kind |
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2008134763 | Aug 2008 | RU | national |
This application claims the benefit of the priority filing date in PCT/RU2009/000426 referenced in WIPO Publication WO2010/024726. The earliest priority date claimed is Aug. 25, 2008.
Filing Document | Filing Date | Country | Kind | 371c Date |
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PCT/RU2009/000426 | 8/25/2009 | WO | 00 | 7/11/2011 |