CN113200141B - Suction type lift increasing device based on Laval tubular plasma - Google Patents
Suction type lift increasing device based on Laval tubular plasma Download PDFInfo
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- CN113200141B CN113200141B CN202110580155.7A CN202110580155A CN113200141B CN 113200141 B CN113200141 B CN 113200141B CN 202110580155 A CN202110580155 A CN 202110580155A CN 113200141 B CN113200141 B CN 113200141B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
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- Y02T50/10—Drag reduction
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Abstract
The invention discloses a gas-suction type high-lift device based on Laval-shaped plasma, which comprises two fixing flat plates which are arranged in parallel, wherein two plasma discharge unit mounting tables are arranged between the two fixing flat plates, the two fixing flat plates and the two plasma discharge unit mounting tables jointly enclose a Laval-shaped cavity, plasma discharge units are arranged on the slope surfaces of the two plasma discharge unit mounting tables, one sides of the plasma discharge units are connected with a high-voltage power supply, and one sides of the plasma discharge units are grounded; the port of the tapered section of the Laplace tubular cavity is an airflow inlet, the port of the straight section of the Laplace tubular cavity is an airflow outlet, and the airflow outlet is provided with a first check valve; and each plasma discharge unit mounting table is provided with a second check valve which prevents external atmosphere from entering the hollow cavity of the Laval tile. The device changes the leading edge vortex structure and vortex fracture by delaying the flow separation of the wing section or the wing, and can achieve the purpose of high lift of the aircraft.
Description
Technical Field
The invention belongs to the technical field of aerodynamics, plasma physics and flow control, and particularly relates to a Laval-tube-shaped plasma-based air-breathing type lift-increasing device.
Background
With the development of science and technology, the consumption of fossil energy is increased, the emission of carbon is rapidly increased, and the environment is continuously worsened. Therefore, energy conservation and emission reduction become a hot spot of wide attention in all social circles. According to related researches, the method comprises the following steps: the device for improving the wing-shaped lift force is arranged on the airplane, so that the maximum lift force coefficient of the airplane can be increased, and the takeoff and landing running distance of the airplane can be shortened. The reduction of the takeoff distance and landing running distance of the airplane reduces the consumption of fuel. The investigation shows that: among the operating costs of an aircraft, the fuel costs account for approximately 30% of the total operating costs. Therefore, the maximum lift coefficient of the airplane is improved, the takeoff and landing running distance of the airplane is shortened, the energy consumption of the airplane can be saved, and the operation cost is reduced.
The research shows that: when the aircraft is at a medium and small attack angle, airflow is inevitably separated at the front edge of the wing profile and a complex front edge vortex system structure is generated, so that the maximum lift coefficient of the aircraft is influenced. The lift force increasing mechanism commonly used at present is that the flow separation of an airfoil or a wing is delayed, a leading edge vortex structure and vortex fracture are changed, and the flow is changed from an unsteady flow state to a steady flow state, so that the lift force of the airfoil is improved. Based on the control mechanism, many high-lift methods have been developed, and the high-lift technology is mainly divided into an active control technology and a passive control technology according to whether the high-lift control mode requires external energy input. Passive control technologies (such as micro-bumps, micro-pits, vortex generators and the like) are fully researched and widely applied, but the potential for improving the performance of the aircraft is limited, effective control can be realized only in a certain specific state, and the passive control technology cannot be applied to control of complex flow fields. The active flow control technology is characterized in that external energy is applied to a flow field, and the external energy is mutually coupled with the flow field on the surface of the wing to play a role in flow control. Compared with a passive control technology, the active control technology has the advantages that the flow fields in different states can be subjected to self-adaptive adjustment through closed-loop control, and the purpose of wide-range flow control is further achieved.
The air-breathing type high-lift flow control technology is one of a plurality of active control modes, and is widely researched due to the advantages of high efficiency, quick response, small additional resistance and the like. The existing air suction type control method mainly comprises a pneumatic valve, a dry powder inhaler and the like, and although most of the control methods have higher efficiency, the problems of large control system, complex mechanical structure and the like cannot be avoided, so that the further engineering application of the control method is limited.
Disclosure of Invention
The invention aims to provide a Laval-shaped-tube-shaped-plasma-based air-breathing high-lift device, which can achieve the purpose of high lift of an aircraft by delaying flow separation of airfoils or wings, changing a leading edge vortex structure and vortex rupture.
The invention adopts the technical scheme that the gas-suction type high-lift device based on the Laval-shaped plasma comprises two fixing flat plates which are arranged in parallel, two plasma discharge unit installation platforms are arranged between the two fixing flat plates, the longitudinal section of each plasma discharge unit installation platform is in a right-angled trapezoid shape, the two plasma discharge unit installation platforms positioned between the two fixing flat plates are arranged in a mirror symmetry mode, the two fixing flat plates and the two plasma discharge unit installation platforms jointly enclose a Laval-shaped cavity, the slope surfaces of the two plasma discharge unit installation platforms and the space enclosed by the two fixing flat plates form a tapered section of the Laval-shaped cavity, the opposite wall surfaces of the two plasma discharge unit installation platforms and the space enclosed by the two fixing flat plates form a straight section of the Laval-shaped cavity, and the slope surfaces of the two plasma discharge unit installation platforms are both provided with plasma discharge units, one side of the plasma discharge unit is connected with a high-voltage power supply, and one side of the plasma discharge unit is grounded; the port of the tapered section of the Laplace tubular cavity is an airflow inlet, the port of the straight section of the Laplace tubular cavity is an airflow outlet, and the airflow outlet is provided with a first check valve which prevents external atmosphere from entering the Laplace tubular cavity; and each plasma discharge unit mounting platform is provided with a second check valve, one end of each second check valve faces to the external atmosphere, the other end of each second check valve faces to the tile tubular cavity, and the second check valves prevent the external atmosphere from entering the tile tubular cavity.
The present invention is also characterized in that,
the plasma discharge unit comprises a plate-shaped dielectric layer, wherein a forked AlSi is arranged on one side of the plate-shaped dielectric layer3O4A mesh-shaped exposed electrode, and a plurality of plate-shaped AlSi layers arranged on the other side of the plate-shaped dielectric layer3O4A mesh-shaped cover electrode; fork-type AlSi3O4The mesh-shaped exposed electrode is connected with a high-voltage power supply and a plurality of plate-shaped AlSi3O4The mesh-shaped covering electrodes are grounded after being connected in parallel; y-type AlSi3O4The mesh-shaped exposed electrode faces to the gas flow side, and a plurality of plate-shaped AlSi electrodes3O4The mesh-shaped covering electrode is laid on the slope surface of the plasma discharge unit mounting table.
The high-voltage power supply voltage is 5kV-30kV, the waveform is fast-rising and slow-falling, and the period is 0.1ns-1 ms.
Plate type AlSi3O4The thickness of the reticular covering electrode is 0.01mm-1mm, and the width is 5-20 mm; fork-type AlSi3O4The thickness of the mesh-shaped exposed electrode is 0.01mm to 1mm, and the width of each bifurcated portion is 2 mm to 5 mm.
The plate-shaped dielectric layer is a F4BM material dielectric layer.
The fixing flat plate is made of organic glass; the plasma discharge unit mounting table is made of polytetrafluoroethylene.
The first check valve is a plate-shaped check valve; the second check valve is a conical check valve.
The invention has the beneficial effects that:
(1) the invention provides a suction type lift-increasing device structure based on a Laval tubular plasma, which is characterized in that air in a Laval tubular cavity forms negative pressure by inducing airflow in the Laval tubular cavity, a pressure difference is generated between an air exhaust opening and the external atmospheric pressure, the air is sucked into a pump cavity under the action of the pressure difference, the flow separation of wing profiles or wings is delayed, a front edge vortex structure and vortex rupture are changed, and the purpose of increasing the lift of an aircraft is achieved.
(2) The invention relates to a Laval-shaped-tube-based plasma air-breathing high-lift device, which adopts a plasma exciter to replace a traditional mechanical device to induce airflow and adopts a fast-rising and slow-falling type waveform pulse high-voltage power supply, and has the advantages of simple structure, short response time, low energy consumption and the like.
(3) The invention relates to a gas-suction type lift-increasing device based on Laval-shaped plasma, which is characterized in that a Laval-shaped cavity is applied, and according to continuity assumption and Bernoulli equation, when a power supply is started, a plasma discharge unit generates jet flow, so that the flow velocity of fluid in the Laval-shaped cavity is increased, and external gas is sucked at subsonic speed. At the same time, as the lava tubular cavity contracts, the gas is forced to accelerate. Under the same energy consumption condition, the air suction device can generate larger air suction amount, and increase the control effect on the flow separation of the wing surface, so that the flow separation point moves backwards, and the lift force of the aircraft is increased.
(4) According to the suction type high lift device based on the Laval-tile tubular plasma, the check valves are arranged on the upper portion and the lower portion of the Laval-tile tubular cavity, the check valve is arranged at the gas outlet, gas is prevented from being sucked backwards, and the suction efficiency is improved once.
(5) The suction type lift-increasing device based on the Laval-shaped plasma adopts electric signal control, does not have a complex control system and mechanical moving parts, has high response speed, can be matched with a closed-loop control system, adjusts the input power in real time according to the flow field state, realizes closed-loop control, reduces energy consumption and improves the control effect.
(6) The gas suction type high lift device based on the Laval-tile tubular plasma adopts a rectangular configuration, has good adaptability, and can flexibly arrange the gas suction device according to the surface structure of an airfoil and the use requirement.
(7) The device aims at reducing energy consumption and operation cost, and is a green low-carbon technology.
Drawings
FIG. 1 is a schematic structural diagram of a Laval tubular plasma-based air-breathing high-lift device of the invention;
FIG. 2 is a view of the internal structure of the high lift device based on Laval tubular plasma suction type;
FIG. 3 is a schematic structural diagram of a plasma discharge unit mounting table and a plasma discharge unit in a Laval tubular plasma based getter type high lift device according to the present invention;
FIG. 4 shows a Y-shaped AlSi in the high lift device based on Laval tubular plasma suction3O4Mesh-shaped exposed electrode, plate-shaped dielectric layer and plate-shaped AlSi3O4Schematic diagram of relative position relationship of the mesh-shaped covering electrode;
FIG. 5 is a schlieren experiment without a power supply of the Laval tube-shaped plasma suction type lift-increasing device according to the present invention;
FIG. 6 is a schlieren experiment of the open power supply of the high-lift device based on Laval tubular plasma suction;
FIG. 7 shows the piv experiment result of the high lift device based on Laval tubular plasma suction;
FIG. 8 is a waveform diagram of a pulse high-voltage power supply of the high-lift device based on Laval tubular plasma suction;
FIG. 9 is a schematic view of the installation arrangement of the high lift device based on Laval tubular plasma suction type;
FIG. 10 is a schematic view of a flow field on the surface of an airfoil of the Laval-tile-based tubular plasma air-breathing high lift device when the device is not in operation;
FIG. 11 is an experimental diagram of a flow field on the surface of an airfoil when the Laval-tile-based tubular plasma air-breathing high-lift device of the invention is not in operation;
FIG. 12 is a schematic view of a flow field on the surface of an airfoil when the Laval-tile-based tubular plasma air-breathing high-lift device is opened;
FIG. 13 is an experimental diagram of a flow field on the surface of an airfoil when the Laval-tile-based tubular plasma air-breathing high-lift device is opened and operated.
In the figure, 1, a fixed flat plate, 2, a plasma discharge unit mounting table, 3, a Laval tubular cavity, 4, a first check valve, 5, a second check valve and 6, a forked AlSi3O4Mesh exposed electrode, 7. plate-shaped dielectric layer, 8. plate-shaped AlSi3O4Mesh-shaped covering electrodes, 9 bolts, 10 nuts;
A. based on a Laval-tile tubular plasma air-breathing type high-lift device, and B, an airflow guide pipe.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The invention relates to a gas-suction type high-lift device based on Laval-tube-shaped plasma, which comprises two fixed flat plates 1 arranged in parallel, wherein the distance between the fixed flat plates 1 is 50 mm; two plasma discharge unit installation platforms 2 are arranged between the two fixing flat plates 1, and the two fixing flat plates 1 and the two plasma discharge unit installation platforms 2 arranged between the two fixing flat plates are fixedly connected together through bolts 9 and nuts 10; the longitudinal section of the plasma discharge unit mounting platforms 2 is in a right trapezoid shape, the two plasma discharge unit mounting platforms 2 positioned between the two fixed flat plates 1 are arranged in a mirror symmetry mode, the two fixed flat plates 1 and the two plasma discharge unit mounting platforms 2 jointly enclose a Laval tubular cavity 3, and the taper of the tapered part of the cavity is 15 degrees; the inclined surfaces of the two plasma discharge unit installation platforms 2 and the space surrounded by the two fixing flat plates 1 form a tapered section of the Laval tubular cavity 3, the opposite wall surfaces of the two plasma discharge unit installation platforms 2 and the space surrounded by the two fixing flat plates 1 form a straight section of the Laval tubular cavity 3, the inclined surfaces of the two plasma discharge unit installation platforms 2 are provided with plasma discharge units, one side of each plasma discharge unit is connected with a high-voltage power supply, and one side of each plasma discharge unit is grounded; the port of the convergent section of the tile-shaped cavity 3 is an airflow inlet, the port of the straight section of the tile-shaped cavity 3 is an airflow outlet, the airflow outlet is provided with a first check valve 4, the first check valve 4 prevents external atmosphere from entering the tile-shaped cavity 3, and the lateral projection area of the first check valve 4 is the same as the area of the airflow outlet; every plasma discharge unit mount table 2 all is equipped with a second check valve 5, and the one end of second check valve 5 is towards external atmosphere, and the other end of second check valve 5 is towards Laval tile tubular cavity 3, and second check valve 5 prevents that external atmosphere from getting into in Laval tile tubular cavity 3.
The plasma discharge unit comprises a plate-shaped dielectric layer 7, wherein a forked AlSi is arranged on one side of the plate-shaped dielectric layer 73O4The other side of the mesh-shaped exposed electrode 6 and the plate-shaped dielectric layer 7 is provided with a plurality of plate-shaped AlSi3O4A mesh-like cover electrode 8; fork-type AlSi3O4The mesh-shaped exposed electrode 6 is connected with a high-voltage power supply and a plurality of plate-shaped AlSi3O4The mesh-shaped covering electrodes 8 are grounded after being connected in parallel; y-type AlSi3O4The mesh-shaped exposed electrode 6 faces to the airflow side, and a plurality of plate-shaped AlSi electrodes3O4The mesh-shaped cover electrode 8 is laid at the slope surface of the plasma discharge cell installation stage 2.
The high-voltage power supply voltage is 5kV-30kV, the waveform is fast-rising and slow-falling, and the period is 0.1ns-1 ms.
Plate type AlSi3O4The thickness of the reticular covering electrode 8 is 0.01mm-1mm, and the width is 5-20 mm; fork-type AlSi3O4Mesh exposureThe thickness of the electrode 6 is 0.01mm to 1mm, and the width of each bifurcated portion is 2 mm to 5 mm.
The plate-shaped medium layer 7 is a medium layer of F4BM material.
The fixing flat plate 1 is made of organic glass; the plasma discharge unit mounting table 2 is made of polytetrafluoroethylene.
The first check valve 4 is a plate-shaped check valve, the length of which is 50mm, the width of which is 20mm and the thickness of which is 5 mm; the second check valve 5 is a conical check valve, the conical degree of the conical check valve is 15 degrees, and the height is 20 mm.
The working principle of the device is as follows: switching on a pulsed high voltage power supply, fork-type AlSi3O4Mesh-shaped exposed electrode 6 and plate-shaped AlSi3O4The mesh covering electrode 8 generates a potential difference to ionize air in the Laval tubular cavity 3, and particle jet flow along the surface of the inner cavity body is generated in the Laval tubular cavity 3, and finally a confluent airflow is formed. According to the bernoulli equation, as the flow velocity of the fluid inside the lava tubular cavity 3 is increased, a negative pressure is formed inside the lava tubular cavity 3, the air outside the lava tubular cavity 3 is sucked at the subsonic speed, and as the lava tubular cavity 3 contracts, the air is forced to accelerate to enhance the suction characteristic, as shown in fig. 6. Wherein fig. 5 is a photograph of a schlieren instrument without a pulse of high voltage power supply for comparison with fig. 6. And it can be known from FIG. 7 that the maximum inspiration flow rate can reach 1.2 m/s.
And (3) anti-reflux design: when the device is used for air suction, as shown in figure 1, according to Bernoulli's equation, the external pressure is greater than the internal pressure of the Laval cavity 3, external air enters the Laval cavity 3 from the left tapered mouth of the device and the second check valve 5, and in order to prevent air flow from being sucked from the right outlet, the first check valve 4 is arranged at the right outlet to block the external air flow.
Studies have shown that, based on the high lift principle of the aircraft described in the background, the key to the high lift effect is to limit the volume of the aspirator while increasing the suction characteristics of the aspirator pump. The plasma discharge unit of the device adopts a fast-rising and slow-falling pulse high-voltage power supply, the waveform is shown in figure 8, and under the same energy consumption, the plasma discharge unit can generate stronger particle jet flow, the internal flow speed of the cavity is improved, the air suction characteristic of external air is increased, and the air suction strength can be adjusted by adjusting the power of the power supply.
As shown in fig. 9, the high lift device a based on the lava tubular plasma air suction type is vertically arranged inside the wing, and an airflow guide pipe B is connected behind the high lift device a based on the lava tubular plasma air suction type.
As shown in fig. 10-11, when the air suction device is not in operation, according to the schematic diagram of the flow field on the surface of the wing and the experimental diagram, in the state of a large attack angle, the airflow passes through the wing, and the boundary layer air of the wing gradually evolves to flow separation on the surface of the wing as the counter pressure difference force slows down, so that a complex sequence-like vortex structure appears on the surface of the wing, and the lift force of the wing profile is reduced.
As shown in fig. 12 to 13, when the air suction device starts to work, the air suction device installed below the wing generates air suction to suck the airflow above the separation region, so that the high-speed airflow attaches to the surface of the wing again, the adverse pressure gradient is reduced, the flow separation of the wing profile or the wing is delayed, the leading edge vortex structure and the vortex fracture are changed, and the purpose of increasing the lift of the aircraft is achieved.
Claims (7)
1. A gas-suction type high-lift device based on Laval-tile-shaped tubular plasma is characterized by comprising two fixing flat plates (1) which are arranged in parallel, two plasma discharge unit installation platforms (2) are arranged between the two fixing flat plates (1), the longitudinal sections of the plasma discharge unit installation platforms (2) are right-angled trapezoids, the two plasma discharge unit installation platforms (2) which are arranged between the two fixing flat plates (1) are arranged in a mirror symmetry mode, the two fixing flat plates (1) and the two plasma discharge unit installation platforms (2) jointly enclose a Laval-tile-shaped cavity (3), the slope surfaces of the two plasma discharge unit installation platforms (2) and the space enclosed by the two fixing flat plates (1) form a tapered section of the Laval-tile-shaped cavity (3), the opposite wall surfaces of the two plasma discharge unit installation platforms (2) and the space enclosed by the two fixing flat plates (1) form a straight section of the Laval-tile-shaped cavity (3), the slope surfaces of the two plasma discharge unit mounting tables (2) are respectively provided with a plasma discharge unit, one side of each plasma discharge unit is connected with a high-voltage power supply, and one side of each plasma discharge unit is grounded; a port of a reducing section of the Laval tile tubular cavity (3) is an airflow inlet, a port of a straight section of the Laval tile tubular cavity (3) is an airflow outlet, the airflow outlet is provided with a first check valve (4), and the first check valve (4) prevents external atmosphere from entering the Laval tile tubular cavity (3); all be equipped with one second check valve (5) on every plasma discharge unit mount table (2), the one end of second check valve (5) is towards external atmosphere, and the other end of second check valve (5) is towards Laval tile tubular cavity (3), and second check valve (5) prevent that external atmosphere from getting into in Laval tile tubular cavity (3).
2. The Laval-tube-shaped-based plasma air-breathing high-lift device as claimed in claim 1, wherein the plasma discharge unit comprises a plate-shaped dielectric layer (7) and forked AlSi3O4Mesh-shaped exposed electrode (6) and plate-shaped AlSi3O4A mesh-shaped covering electrode (8), and a forked AlSi is arranged on one side of the plate-shaped dielectric layer (7)3O4A mesh-shaped exposed electrode (6), and a plurality of plate-shaped AlSi layers arranged on the other side of the plate-shaped dielectric layer (7)3O4A mesh-like cover electrode (8); fork-type AlSi3O4The net-shaped exposed electrode (6) is connected with a high-voltage power supply and a plurality of plate-shaped AlSi3O4The reticular covering electrodes (8) are grounded after being connected in parallel; fork-type AlSi3O4The mesh-shaped exposed electrode (6) faces to the airflow side, and a plurality of plate-shaped AlSi electrodes3O4The reticular covering electrode (8) is laid on the slope surface of the plasma discharge unit mounting table (2).
3. The lava tubular plasma-based getter type high-lift device according to claim 2, wherein the high voltage power supply has a voltage of 5kV-30kV, a waveform of fast rise and slow fall, and a period of 0.1ns-1 ms.
4. The Laval-tile-based tubular plasma-based getter according to claim 2Lifting device, characterized in that the plate type AlSi3O4The thickness of the reticular covering electrode (8) is 0.01mm-1mm, and the width is 5-20 mm; fork-type AlSi3O4The thickness of the reticular exposed electrode (6) is 0.01mm-1mm, and the width of each branched part is 2-5 mm.
5. The lava tube based plasma suction type high lift device according to claim 2, characterized in that the plate-like dielectric layer (7) is a dielectric layer of F4BM material.
6. The lava-based tubular plasma suction type high lift device according to claim 1, wherein the fixing plate (1) is made of organic glass; the plasma discharge unit mounting table (2) is made of polytetrafluoroethylene.
7. The lava tubular plasma based getter type high lift device according to claim 1, wherein the first non-return valve (4) is a plate-shaped non-return valve; the second check valve (5) is a conical check valve.
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| CN202110580155.7A CN113200141B (en) | 2021-05-26 | 2021-05-26 | Suction type lift increasing device based on Laval tubular plasma |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102006008864A1 (en) * | 2006-02-25 | 2007-09-06 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Flow surface element for vehicle e.g. aircraft has plasma production unit arranged as dielectric obstructed unloading unit, and unit is inserted global approximately across incoming flow of element arranged by motion of vehicle |
| CN102767497A (en) * | 2012-05-22 | 2012-11-07 | 北京卫星环境工程研究所 | Fuel-free spacecraft propelling system based on spatial atomic oxygen and propelling method |
| CN103523208A (en) * | 2013-10-12 | 2014-01-22 | 中国人民解放军空军工程大学 | Method for controlling plasma flow of wing lift-rising apparatus |
| CN205559070U (en) * | 2016-03-04 | 2016-09-07 | 王力丰 | Use system and aircraft of compressed air as application of force source |
| CN108235553A (en) * | 2017-12-28 | 2018-06-29 | 西安理工大学 | Sliding discharge driver and its method for controlling plasma flow to slender bodies |
| CN110243567A (en) * | 2019-05-28 | 2019-09-17 | 中国人民解放军空军工程大学 | Plasma excitation controls Three-Dimensional Shock Wave/boundary-layer interference corner separation device and method |
| CN110901896A (en) * | 2018-09-14 | 2020-03-24 | 范念 | Lifting and pushing integrated power device and application method thereof on aircraft |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9296460B2 (en) * | 2012-02-14 | 2016-03-29 | Phillip R. Barber | Airship with internal propulsion system |
-
2021
- 2021-05-26 CN CN202110580155.7A patent/CN113200141B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102006008864A1 (en) * | 2006-02-25 | 2007-09-06 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Flow surface element for vehicle e.g. aircraft has plasma production unit arranged as dielectric obstructed unloading unit, and unit is inserted global approximately across incoming flow of element arranged by motion of vehicle |
| CN102767497A (en) * | 2012-05-22 | 2012-11-07 | 北京卫星环境工程研究所 | Fuel-free spacecraft propelling system based on spatial atomic oxygen and propelling method |
| CN103523208A (en) * | 2013-10-12 | 2014-01-22 | 中国人民解放军空军工程大学 | Method for controlling plasma flow of wing lift-rising apparatus |
| CN205559070U (en) * | 2016-03-04 | 2016-09-07 | 王力丰 | Use system and aircraft of compressed air as application of force source |
| CN108235553A (en) * | 2017-12-28 | 2018-06-29 | 西安理工大学 | Sliding discharge driver and its method for controlling plasma flow to slender bodies |
| CN110901896A (en) * | 2018-09-14 | 2020-03-24 | 范念 | Lifting and pushing integrated power device and application method thereof on aircraft |
| CN110243567A (en) * | 2019-05-28 | 2019-09-17 | 中国人民解放军空军工程大学 | Plasma excitation controls Three-Dimensional Shock Wave/boundary-layer interference corner separation device and method |
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