CN111498089B - Device and method for realizing aircraft flow control based on plasma exciter - Google Patents
Device and method for realizing aircraft flow control based on plasma exciter Download PDFInfo
- Publication number
- CN111498089B CN111498089B CN202010331622.8A CN202010331622A CN111498089B CN 111498089 B CN111498089 B CN 111498089B CN 202010331622 A CN202010331622 A CN 202010331622A CN 111498089 B CN111498089 B CN 111498089B
- Authority
- CN
- China
- Prior art keywords
- exciter
- flow control
- plasma
- insulating medium
- electrode block
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05H—PLASMA TECHNIQUE; PRODUCTION OF ACCELERATED ELECTRICALLY-CHARGED PARTICLES OR OF NEUTRONS; PRODUCTION OR ACCELERATION OF NEUTRAL MOLECULAR OR ATOMIC BEAMS
- H05H1/00—Generating plasma; Handling plasma
- H05H1/24—Generating plasma
- H05H1/2406—Generating plasma using dielectric barrier discharges, i.e. with a dielectric interposed between the electrodes
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Aviation & Aerospace Engineering (AREA)
- Spectroscopy & Molecular Physics (AREA)
- Plasma Technology (AREA)
Abstract
本发明公开了一种基于等离子体激励器的实现飞行器流动控制的装置和方法，装置包括介质阻挡放电激励器、等离子体合成射流激励器、绝缘介质和高压电源，介质阻挡放电激励器包括高压电极块和接地电极块，等离子体合成射流激励器包括第一电极棒和第二电极棒，绝缘介质被第一孔和第二孔贯穿，高压电极块位于绝缘介质的上表面上，接地电极块位于绝缘介质内，第二孔的内部腔体形成激励器腔体，第一电极棒和第二电极棒分别自绝缘介质伸入激励器腔体内。本发明介质阻挡放电激励器所产生的射流可用于控制飞行器表面流场的分离，降低飞行阻力和提高升力；等离子体合成射流激励器所产生的射流可以用来改变飞行器的飞行姿态和提供飞行所需要的推力。
The invention discloses a device and method for realizing flow control of an aircraft based on a plasma exciter. The device includes a dielectric barrier discharge exciter, a plasma synthetic jet exciter, an insulating medium and a high-voltage power supply, and the dielectric barrier discharge exciter includes a high-voltage electrode block and ground electrode block, the plasma synthetic jet exciter includes a first electrode rod and a second electrode rod, the insulating medium is penetrated by the first hole and the second hole, the high-voltage electrode block is located on the upper surface of the insulating medium, and the ground electrode block is located on the upper surface of the insulating medium. In the insulating medium, the inner cavity of the second hole forms an exciter cavity, and the first electrode rod and the second electrode rod respectively extend into the exciter cavity from the insulating medium. The jet generated by the dielectric barrier discharge exciter of the invention can be used to control the separation of the flow field on the surface of the aircraft, reduce the flight resistance and improve the lift; the jet generated by the plasma synthetic jet exciter can be used to change the flight attitude of the aircraft and provide flight required thrust.
Description
Technical Field
The invention belongs to the field of aircraft external flow field flow control, and particularly relates to a device and a method for realizing aircraft flow control based on a plasma exciter.
Background
Various aircraft are rapidly developing today and are increasingly used in our lives. People have higher and higher performance requirements on aircrafts, and the performances of the aircrafts include high flying speed, resistance reduction, noise reduction, energy conservation, high efficiency and flexibility. The existing aircraft wing is easy to generate airflow separation when the attack angle is large, so that the wing loses enough lift force prematurely, and the safety of the aircraft is threatened. The active flow control actuator is essentially an energy conversion device, and controls an external flow field by converting input chemical energy, electric energy, mechanical energy and the like into kinetic energy or heat energy possessed by the actuator.
Prandtl in 1904 proposed a method that could delay the separation of the gas stream with a blowing/adsorbing facing, which was the earliest concept of flow control. In recent years, the concept of synthetic jet has gradually appeared to the front of people and has become a hot spot of research in the field of active flow control. The main mechanisms for controlling the aircraft surface flow field by synthetic jets are the following two points: (1) vortex structures of the separation area are enhanced by vortex pairs generated in the forming process of the synthetic jet flow, and the vortex structures interact with incoming flow to delay airflow separation. (2) The jet flow generated by the synthetic jet flow exciter generates thrust to the aircraft, so that the flight state of the aircraft is controlled. Existing flow control does not achieve well three-dimensional active flow control of an aircraft.
Disclosure of Invention
The invention aims to provide a device and a method for realizing aircraft flow control based on a plasma exciter so as to realize three-dimensional active flow control on an aircraft.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a device for realizing aircraft flow control based on a plasma exciter comprises a dielectric barrier discharge exciter, a plasma synthetic jet exciter, an insulating medium and a high-voltage power supply, the dielectric barrier discharge exciter comprises a high-voltage electrode block and a grounding electrode block, the plasma synthetic jet exciter comprises an exciter cavity, a first electrode bar and a second electrode bar, a through hole is arranged between the upper surface and the lower surface of the insulating medium, the high-voltage electrode block is positioned on the upper surface of the insulating medium at one side of the through hole, the grounding electrode block is positioned in the insulating medium at the other side of the through hole, the exciter cavity is connected with the lower surface of the insulating medium, the through hole is communicated with the exciter cavity, the first electrode bar and the second electrode bar respectively extend into the exciter cavity, the high-voltage power supply supplies power to the dielectric barrier discharge exciter and the plasma synthetic jet exciter.
A device for realizing aircraft flow control based on a plasma exciter comprises a dielectric barrier discharge exciter, at least one plasma synthetic jet exciter, an insulating medium and a high-voltage power supply, the dielectric barrier discharge exciter comprises a high-voltage electrode block and a grounding electrode block, the plasma synthetic jet exciter comprises a first electrode bar and a second electrode bar, the upper surface and the lower surface of the insulating medium are penetrated by a first hole and a second hole which are communicated, the high-voltage electrode block is positioned on the upper surface of the insulating medium at one side of the first hole, the grounding electrode block is positioned in the insulating medium at the other side of the first hole, the inner cavity of the second hole forms an exciter cavity, the first electrode bar and the second electrode bar respectively extend into the cavity of the exciter from an insulating medium, the high-voltage power supply supplies power to the dielectric barrier discharge exciter and the plasma synthetic jet exciter.
Further, the distance between the high-voltage electrode block and the grounding electrode block is larger than the diameter of the through hole or the first hole.
Further, the high-voltage electrode block and the grounding electrode block are placed in parallel.
Further, the number of the plasma synthetic jet actuators is more than two.
Further, the material of the insulating medium and/or the exciter cavity is quartz glass, ceramic or boron nitride.
Furthermore, the high-voltage electrode block, the grounding electrode block, the first electrode rod and the second electrode rod are made of copper or tungsten.
Furthermore, the length of the high-voltage electrode block and the length of the grounding electrode block are 50mm, the width of the high-voltage electrode block and the width of the grounding electrode block are 15mm, the horizontal distance between the high-voltage electrode block and the grounding electrode block is 2mm, the diameter of the cavity of the exciter is 4mm, the height of the cavity of the exciter is 5mm, and the diameter of the first electrode bar and the diameter of the second electrode bar are 0.5mm and the distance of the first electrode bar and the second electrode bar is 1 mm.
Further, the device is arranged at the position of the wing surface of the aircraft.
The method for realizing the aircraft flow control of the plasma exciter-based aircraft flow control device comprises three modes:
in the first mode: the dielectric barrier discharge exciter works, the plasma synthetic jet exciter is closed, and the jet flow direction generated by the dielectric barrier discharge exciter is V parallel to the surface of the insulating mediumxDirection；
In the second mode: closing the dielectric barrier discharge exciter, operating the plasma synthetic jet exciter, and generating a V-shaped jet flow in the direction vertical to the surface of the insulating mediumyDirection;
in the third mode: the jet flow direction generated by the simultaneous work of the dielectric barrier discharge exciter and the plasma synthetic jet flow exciter is V parallel to the surface of the insulating mediumxDirection and V perpendicular to the surface of the insulating mediumyAnd (4) direction.
Compared with the prior art, the invention has the remarkable advantages that:
(1) the invention has no moving part, high response speed, wide working frequency band and high reliability;
(2) the device has simple structure, can be embedded on the surface of an aircraft, occupies small space, can realize three-dimensional active flow control on the aircraft, can control the separation of a flow field on the surface of the aircraft by jet flow generated by a surface dielectric barrier discharge exciter, reduces the flight resistance and improves the lift force, can ensure that the jet flow speed generated by a plasma synthetic jet flow exciter can reach more than 300m/s, can be used for changing the flight attitude of the aircraft and can provide thrust required by flight;
(3) the ionized gas comes from the outside air without the supply of an air source, and the gas can realize automatic backfilling under the action of pressure difference;
(4) the two actuators can be conveniently and cooperatively controlled through circuit design, so that the jet flow generation processes of the two actuators are synchronous, and the jet flows generated by the two actuators can independently act on an external flow field of an aircraft.
Drawings
FIG. 1 is a schematic structural diagram of a first embodiment of the device for increasing the jet intensity of the annular electrode actuator according to the present invention.
FIG. 2 is a schematic structural diagram of a second embodiment of the device for increasing the jet intensity of the annular electrode actuator according to the present invention.
FIG. 3 is a side view of a second embodiment of the device for increasing the jet intensity of the dielectric barrier discharge stimulator with the ring electrode according to the present invention.
FIG. 4 is a top view of a second embodiment of the device for increasing the jet intensity of the annular electrode dielectric barrier discharge actuator of the present invention.
FIG. 5 is a front view of a second embodiment of the device for improving the jet intensity of the annular electrode dielectric barrier discharge actuator.
Fig. 6 is a circuit diagram for realizing the synergy of two exciters.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The following describes the implementation of the present invention in detail with reference to specific embodiments.
Example 1
With reference to fig. 1, a device for realizing aircraft flow control based on a plasma exciter comprises a dielectric barrier discharge exciter, a plasma synthetic jet exciter, an insulating medium 1 and a high voltage power supply, wherein the dielectric barrier discharge exciter comprises a high voltage electrode block 3 and a ground electrode block 4, the plasma synthetic jet exciter comprises an exciter cavity 2, a first electrode rod 5 and a second electrode rod 6, a through hole is formed between the upper surface and the lower surface of the insulating medium 1, the high voltage electrode block 3 is located on the upper surface of the insulating medium 1 at one side of the through hole, the ground electrode block 4 is located in the insulating medium 1 at the other side of the through hole, the exciter cavity 2 is connected with the lower surface of the insulating medium 1, the through hole is communicated with the exciter cavity 2, and the first electrode rod 5 and the second electrode rod 6 respectively extend into the exciter cavity 2, the high-voltage power supply supplies power to the dielectric barrier discharge exciter and the plasma synthetic jet exciter.
Example 2
With reference to fig. 2-5, a device for realizing aircraft flow control based on a plasma exciter comprises a dielectric barrier discharge exciter, at least one plasma synthetic jet exciter, an insulating medium 1 and a high voltage power supply, wherein the dielectric barrier discharge exciter comprises a high voltage electrode block 3 and a ground electrode block 4, the plasma synthetic jet exciter comprises a first electrode rod 5 and a second electrode rod 6, the upper surface and the lower surface of the insulating medium 1 are penetrated by a first hole and a second hole which are communicated with each other, the high voltage electrode block 3 is located on the upper surface of the insulating medium 1 on one side of the first hole, the ground electrode block 4 is located in the insulating medium 1 on the other side of the first hole, an exciter cavity 2 is formed by an internal cavity of the second hole, the first electrode rod 5 and the second electrode rod 6 respectively extend into the exciter cavity 2 from the insulating medium 1, a pair of electrode blocks 3 and 4 correspond to the plurality of exciter cavities 2, and the high-voltage power supply supplies power to the dielectric barrier discharge exciter and the plasma synthetic jet exciter.
Further, the distance between the high voltage electrode block 3 and the ground electrode block 4 is larger than the diameter of the through hole or the first hole, so that the ground electrode block 4 is not exposed to the air.
Further, the high voltage electrode block 3 and the grounding electrode block 4 are arranged in parallel.
Further, the number of the plasma synthetic jet actuators is more than two.
Further, the material of the insulating medium 1 and/or the exciter cavity 2 is quartz glass, ceramic or boron nitride.
Further, the high voltage electrode block 3, the grounding electrode block 4, the first electrode bar 5 and the second electrode bar 6 are made of copper or tungsten.
Further, the length of the high-voltage electrode block 3 and the length of the grounding electrode block 4 are 50mm, the width of the high-voltage electrode block is 15mm, the thickness of the high-voltage electrode block is 1mm, the horizontal distance between the high-voltage electrode block and the grounding electrode block is 2mm, the diameter of the exciter cavity 2 is 4mm, the height of the exciter cavity is 5mm, and the diameter of the first electrode rod 5 and the diameter of the second electrode rod 6 are 0.5mm and the distance of the first electrode rod is 1 mm.
Further, the depth of the grounding electrode 4 embedded into the insulating medium 1 is 2mm, the two electrode blocks are positioned at the center of the exciter cavity 2, and the exciter cavities 2 are distributed in the length direction of the electrode blocks every 10mm, and the total number is 5.
Further, the device is arranged at the position of the wing surface of the aircraft.
The high voltage power supply supplies power for the dielectric barrier discharge exciter and the plasma synthetic jet exciter, when the voltage between the high voltage electrode block 3 and the grounding electrode block 4 reaches the breakdown voltage, the high voltage electrode block ionizes in the surface of the insulating medium 1 and the through hole or the first hole to generate plasma, and the plasma can induce the fluid around the electrode block to flow along the direction (V in the figure) parallel to the insulating medium 1xDirection) of flow. When the voltage between the first electrode bar 5 and the second electrode bar 6 reaches the breakdown voltage, high-temperature and high-pressure plasma is generated in the cavity 2 of the exciter, and gas in the cavity is rapidly sprayed out under the action of the difference between the internal pressure and the external pressure to form a voltage which is vertical to the surface of the insulating medium 1 (V in the figure)yDirection) of the jet flow, and the horizontal jet flow generated by the dielectric barrier discharge exciter jointly act on the external flow field of the aircraft.
In order to synchronously supply power to the high-voltage electrode block 3, the grounding electrode block 4, the first electrode bar 5 and the second electrode bar 6, a set of circuit diagram is designed for a high-voltage power supply, and as shown in fig. 6, the whole discharge frequency is adjusted by controlling the on-off of an IGBT transistor. Meanwhile, the switches on the branches can control the dielectric barrier discharge exciter or the plasma synthetic jet exciter to act independently. Wherein the plasma synthetic jet actuator is realized by a capacitive discharge.
Specifically, a direct current power supply E is connected with an IGBT switch, the direct current power supply can be converted into alternating current through the control of the IGBT switch, and then a low-voltage pulse power supply is converted into a high-voltage pulse power supply through a transformer M, so that power is supplied to the electrode blocks 3 and 4 and the electrode rods 5 and 6 in the cavity. The direct current power supply E, the IGBT switch and the transformer jointly form a high-voltage pulse power supply, and the high-voltage pulse power supply can be directly used for replacing the high-voltage pulse power supply. Further, the high-voltage pulse power supply is connected with the two branches in parallel. The main components of the two branches are respectively a dielectric barrier discharge exciter (DBD in the figure) formed by electrode blocks 3 and 4, and a plasma synthetic jet exciter group formed by two electrode rods 5 and 6. In the branch where the dielectric barrier discharge exciter is located, the electrode blocks 3 and 4, the resistor R2 and the switch S3 are connected in series, wherein the resistor R2 mainly plays the roles of protecting the circuit and adjusting the voltage. In the branch where the plasma synthetic jet exciter group is located, there are a resistor R1, a capacitor C and exciters A1, A2, A3, etc. The capacitor C is connected in parallel with the plasma synthetic jet exciter groups A1, A2, A3 and the like, and then connected in series with the resistor R1. The capacitor C is designed to store the energy discharged by the exciter, and the resistor R1 is designed to protect the circuit and adjust the voltage. In both branches there is a switch S3 and S2, respectively, for controlling their operating state. Meanwhile, each plasma synthetic jet exciter is provided with a switch S4, S5 and S6 … … in the circuit, and the switches are used for independently controlling the exciter at each position. Therefore, the purpose of three-dimensional active flow control of the aircraft is achieved.
The following further explains how to realize three-dimensional flow control of the aircraft by controlling the working states of the plasma synthetic jet actuator and the dielectric barrier discharge actuator. The device has three working modes which are respectively as follows: dielectric barrier discharge exciter operating mode (S3 closed, S2 open), plasma synthetic jet exciter discharge mode (S3 open, S2 closed), and common operating mode (S3 closed, S2 closed). The jet flow direction generated by the dielectric barrier discharge exciter is parallel to the surface of the insulating medium 1, and the velocity direction is VxThe direction of the jet flow generated by the plasma synthetic jet actuator is V vertical to the surface of the insulating medium 1yDirection (velocity direction is V at jet ejection stage)yAnd the velocity direction of the gas backfill stage is-VyDirection) and the combination of the two can change the flow field condition of the aircraft in the X-Y plane. As shown in fig. 2, a plurality of plasma synthetic jet actuators (a1, a2, A3, etc.) may exist between the two electrode blocks 3 and 4, and the discharge parameters of each actuator may be controlled by circuit design, thereby achieving three-dimensional flow control of the aircraft external flow field. Based on the performances, the device is arranged at a position (such as the position of the surface of the wing of the aircraft) which plays a critical role in the lift-drag characteristic of the aircraft, and can play a role in achieving double effects with little effort.
The foregoing illustrates and describes the principles, general features, and advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (13)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010331622.8A CN111498089B (en) | 2020-04-24 | 2020-04-24 | Device and method for realizing aircraft flow control based on plasma exciter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010331622.8A CN111498089B (en) | 2020-04-24 | 2020-04-24 | Device and method for realizing aircraft flow control based on plasma exciter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111498089A CN111498089A (en) | 2020-08-07 |
| CN111498089B true CN111498089B (en) | 2022-03-18 |
Family
ID=71866097
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010331622.8A Active CN111498089B (en) | 2020-04-24 | 2020-04-24 | Device and method for realizing aircraft flow control based on plasma exciter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111498089B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112333910B (en) * | 2020-11-04 | 2023-03-28 | 中国人民解放军空军工程大学 | Preionization type high-efficiency plasma synthetic jet exciter |
| CN113316301B (en) * | 2021-06-08 | 2022-02-18 | 西安理工大学 | A one-way conduction plasma getter for wing drag reduction |
| CN113423168B (en) * | 2021-06-25 | 2024-09-20 | 中国人民解放军国防科技大学 | Magnetic control vector high-speed plasma synthetic jet exciter |
| CN113993266B (en) * | 2021-10-19 | 2023-08-01 | 中国人民解放军空军工程大学 | Self-air-supplementing type double-cavity plasma synthetic jet exciter |
| CN114071853B (en) * | 2021-12-03 | 2023-07-21 | 中国人民解放军空军工程大学 | Wing plasma anti-stall/anti-icing dual-mode switching system and working method |
| CN114856814A (en) * | 2022-05-17 | 2022-08-05 | 中国人民解放军海军工程大学 | A plasma synthetic jet vortex generator for flow control |
Citations (10)
| 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 |
| CN101296842A (en) * | 2005-10-17 | 2008-10-29 | 贝尔直升机特克斯特龙有限公司 | Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft |
| CN103089760A (en) * | 2013-01-21 | 2013-05-08 | 南京航空航天大学 | Dielectric barrier discharge plasma body vortex generator |
| CN106050593A (en) * | 2016-08-02 | 2016-10-26 | 中国科学院电工研究所 | Plasma synthesis jet flow serial connection discharge device based on Marx generator |
| CN108116664A (en) * | 2017-12-20 | 2018-06-05 | 南京航空航天大学 | Adaptive excitation control system based on plasma synthesis jet-flow excitor |
| CN108194461A (en) * | 2018-03-08 | 2018-06-22 | 南京理工大学 | It is a kind of to utilize piezoelectric vibration film and three electrode plasma combined type synthesizing jet-flow excitors |
| CN108811292A (en) * | 2018-06-12 | 2018-11-13 | 厦门大学 | A kind of plasma synthesis jet stream combination of stimulation device |
| CN109618481A (en) * | 2018-12-14 | 2019-04-12 | 哈尔滨工业大学 | Plasma Synthetic Jet Exciter at Low Reynolds Number |
| CN110131072A (en) * | 2019-05-28 | 2019-08-16 | 中国人民解放军空军工程大学 | Combined plasma flow control device and method for regulating inlet shock wave/boundary layer interference flow separation |
| CN110933832A (en) * | 2019-07-16 | 2020-03-27 | 中国人民解放军空军工程大学 | Single power supply driven array type plasma synthetic jet flow control device and flow control method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2007106863A2 (en) * | 2006-03-14 | 2007-09-20 | University Of Notre Dame Du Lac | Methods and apparatus for reducing noise via a plasma fairing |
-
2020
- 2020-04-24 CN CN202010331622.8A patent/CN111498089B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101296842A (en) * | 2005-10-17 | 2008-10-29 | 贝尔直升机特克斯特龙有限公司 | Plasma actuators for drag reduction on wings, nacelles and/or fuselage of vertical take-off and landing aircraft |
| 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 |
| CN103089760A (en) * | 2013-01-21 | 2013-05-08 | 南京航空航天大学 | Dielectric barrier discharge plasma body vortex generator |
| CN106050593A (en) * | 2016-08-02 | 2016-10-26 | 中国科学院电工研究所 | Plasma synthesis jet flow serial connection discharge device based on Marx generator |
| CN108116664A (en) * | 2017-12-20 | 2018-06-05 | 南京航空航天大学 | Adaptive excitation control system based on plasma synthesis jet-flow excitor |
| CN108194461A (en) * | 2018-03-08 | 2018-06-22 | 南京理工大学 | It is a kind of to utilize piezoelectric vibration film and three electrode plasma combined type synthesizing jet-flow excitors |
| CN108811292A (en) * | 2018-06-12 | 2018-11-13 | 厦门大学 | A kind of plasma synthesis jet stream combination of stimulation device |
| CN109618481A (en) * | 2018-12-14 | 2019-04-12 | 哈尔滨工业大学 | Plasma Synthetic Jet Exciter at Low Reynolds Number |
| CN110131072A (en) * | 2019-05-28 | 2019-08-16 | 中国人民解放军空军工程大学 | Combined plasma flow control device and method for regulating inlet shock wave/boundary layer interference flow separation |
| CN110933832A (en) * | 2019-07-16 | 2020-03-27 | 中国人民解放军空军工程大学 | Single power supply driven array type plasma synthetic jet flow control device and flow control method |
Non-Patent Citations (3)
| Title |
|---|
| 《Recent developments in DBD plasmaflow control》;Jin-Jun Wang;《Progress in Aerospace Sciences》;20130708;53-78 * |
| 等离子体合成射流能量效率及工作特性研究;王林等;《物理学报》;20130623;第62卷(第12期);408-417 * |
| 等离子体流动控制技术原理及典型应用;史志伟等;《高压电器》;20151031;第36卷(第04期);1474-1478 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111498089A (en) | 2020-08-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111498089B (en) | Device and method for realizing aircraft flow control based on plasma exciter | |
| EP2347637B1 (en) | Disbanded cascaded array for generating and moving plasma clusters for active airflow control and method thereof | |
| CN107091210B (en) | A kind of pulsed plasma thruster based on capillary discharging | |
| US7988103B2 (en) | Solid state supersonic flow actuator and method of use | |
| CN106640568A (en) | Bipolar solid ablation type plasma accelerator | |
| CN109618481B (en) | Plasma Synthetic Jet Exciter at Low Reynolds Number | |
| CN110933832A (en) | Single power supply driven array type plasma synthetic jet flow control device and flow control method | |
| CN110792531B (en) | Intelligent atomizing nozzle based on high-voltage discharge and spraying control system | |
| CN113316303A (en) | Device and method for exciting plasma synthetic jet array driven by direct current arc | |
| CN109296473A (en) | A kind of magnetron pulse discharge high-speed intake port auxiliary start flow control method | |
| CN107061210B (en) | A kind of pulsed plasma thruster accelerated based on electrothermal and electromagnetic mixing | |
| CN210106081U (en) | Solid ablation type magnetic plasma thruster | |
| CN111577561B (en) | Device for improving jet intensity of annular electrode exciter and working method thereof | |
| CN110529284A (en) | Thrust vector control system and method based on plasma synthesis jet-flow excitor | |
| CN107654347B (en) | A kind of high-performance solid ablative-type protective coating pulsed plasma electric propulsion device | |
| CN110784982B (en) | Plasma jet device | |
| RU2542354C1 (en) | Eroding pulse plasma accelerator | |
| CN114856814A (en) | A plasma synthetic jet vortex generator for flow control | |
| CN104202898B (en) | The zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy | |
| Sun et al. | Experimental Investigation on airfoil shock control by plasma aerodynamic actuation | |
| CN110498052A (en) | Thrust vector control system and method based on hybrid synthetic jet actuator | |
| CN103104575A (en) | Electric arc type discharging plasma vortex generator | |
| CN109413831B (en) | A plasma synthetic jet generator with controllable cavity temperature and its application | |
| CN114221569B (en) | Parallel discharge device and method for plasma high-energy synthetic jet exciter | |
| CN206171797U (en) | Spark type synthetic jet energizer based on solenoid valve |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |