CN111577561B - Device for improving jet intensity of annular electrode exciter and working method thereof - Google Patents
Device for improving jet intensity of annular electrode exciter and working method thereof Download PDFInfo
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- CN111577561B CN111577561B CN202010331282.9A CN202010331282A CN111577561B CN 111577561 B CN111577561 B CN 111577561B CN 202010331282 A CN202010331282 A CN 202010331282A CN 111577561 B CN111577561 B CN 111577561B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a device for improving jet intensity of a ring electrode exciter and a working method thereof, the device comprises a dielectric barrier discharge exciter, a plasma synthetic jet exciter, an insulating medium and a high-voltage power supply, wherein the dielectric barrier discharge exciter comprises a ring high-voltage electrode and a ring grounding electrode, the plasma synthetic jet exciter comprises an exciter cavity, a first electrode and a second electrode, a through hole is formed between the upper surface and the lower surface of the insulating medium, the ring high-voltage electrode is positioned on the upper surface of the insulating medium, the ring grounding electrode is positioned in the insulating medium, and the first electrode and the second electrode respectively extend into the exciter cavity. The annular dielectric barrier discharge exciter can generate subsonic jet flow, the plasma synthetic jet flow exciter can generate supersonic jet flow, the two exciters are used cooperatively, and three working modes can be realized, so that the flow of the aircraft in various speed states is controlled, the use is flexible, and the application range is wide.
Description
Technical Field
The invention belongs to the field of fluid control, and particularly relates to a device for improving jet intensity of an annular electrode exciter and a working method thereof.
Background
The method has important practical application value in controlling the external flow field of the aircraft, and the efficient flow control system not only can remarkably improve the working performance of the aircraft, but also can save a large amount of fuel consumption. This makes flow control technology the leading edge and hot spot of fluid mechanics research. In flow control, plasma control has the advantages of no moving parts, simple structure, wide operating frequency band, high response speed and the like as a method for active flow control, and has attracted extensive attention from research institutions in various countries around the world. In particular to a dielectric barrier discharge exciter and a plasma synthetic jet exciter which are respectively suitable for the active flow control of a low-speed aircraft and a supersonic aircraft. The dielectric barrier discharge exciter is composed of a surface exposed electrode, a buried electrode and an intermediate insulating medium. A ring electrode dielectric barrier discharge exciter designed by Santhanakrishnan is characterized in that an upper surface ring electrode is connected with a high-voltage output end of a high-voltage pulse power supply, a lower surface ring electrode is connected with a grounding end of the pulse power supply, when the voltage at two ends of the electrode exceeds breakdown voltage, air near the electrode is broken down and ionized to form plasma, charged particles in the plasma collide with neutral gas molecules to induce macroscopic acceleration of near-wall gas to form near-wall gas jet flow, and the flow control effect is achieved in the working process of an aircraft.
However, due to the limitation of the working principle, the induced jet velocity of the dielectric barrier discharge exciter is not high (less than 30m/s), and the jet velocity far reaching the jet velocity playing a control role in the surface flow field of a high-speed aircraft is not achieved. In order to obtain large-area, low-energy-consumption and high-density plasma jet suitable for flow control of a high-speed aircraft, a great deal of research work is mainly carried out at home and abroad around the structural parameters, insulating media, electrode materials and shapes of exciters. Summarizing the method for improving the jet velocity mainly comprises the following points: firstly, optimizing the exciter structure; secondly, a three-electrode dielectric barrier discharge exciter is adopted to improve the jet speed; and thirdly, the surface sliding flash discharge is generated by utilizing a dual-power supply mode, so that the generation of large-area plasma is facilitated, and the jet speed and the thrust can be improved. But the existing annular electrode dielectric barrier discharge exciter still has the problem of low jet intensity.
Disclosure of Invention
The invention aims to provide a device for improving jet intensity of a ring electrode exciter and a working method thereof.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a device for improving jet intensity of a ring electrode exciter comprises a dielectric barrier discharge exciter, a plasma synthetic jet exciter, an insulating medium and a high-voltage power supply, wherein the dielectric barrier discharge exciter comprises a ring-shaped high-voltage electrode and a ring-shaped grounding electrode, the plasma synthetic jet exciter comprises an exciter cavity, a first electrode and a second electrode, a through hole is formed between the upper surface and the lower surface of the insulating medium, the ring-shaped high-voltage electrode is positioned on the upper surface of the insulating medium, the ring-shaped grounding electrode is positioned in the insulating medium, the central axis of the through hole penetrates through central holes of the ring-shaped high-voltage electrode and the ring-shaped grounding electrode, the exciter cavity is connected with the lower surface of the insulating medium, the through hole is communicated with the exciter cavity, and the first electrode and the second electrode 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 improving jet intensity of a ring electrode exciter comprises a dielectric barrier discharge exciter, a plasma synthetic jet exciter, an insulating medium and a high-voltage power supply, wherein the dielectric barrier discharge exciter comprises a ring-shaped high-voltage electrode and a ring-shaped grounding electrode, the plasma synthetic jet exciter comprises a first electrode and a second electrode, the upper surface and the lower surface of the insulating medium are penetrated through by a first hole and a second hole which are communicated, the ring-shaped high-voltage electrode is positioned on the upper surface of the insulating medium, the ring-shaped grounding electrode is positioned in the insulating medium, the first hole penetrates through the central hole of the ring-shaped grounding electrode, the central axis of the first hole penetrates through the central hole of the ring-shaped high-voltage electrode, the inner cavity of the second hole forms an exciter cavity, and the first electrode and the second electrode respectively extend into the exciter cavity from the insulating medium, the high-voltage power supply supplies power to the dielectric barrier discharge exciter and the plasma synthetic jet exciter.
Further, the central axis of the through hole or the first hole coincides with the central axes of the annular high-voltage electrode and the annular grounding electrode.
Further, the annular high-voltage electrode and the annular grounding electrode are arranged in parallel.
Further, the outer diameter of the annular grounding electrode is equal to the inner diameter of the annular high-voltage electrode.
Further, the insulating medium and/or the exciter cavity are made of polytetrafluoroethylene, ceramic or boron nitride.
Further, the annular high-voltage electrode, the annular grounding electrode, the first electrode and the second electrode are made of copper or tungsten.
Further, the insulating medium is cylindrical, the diameter of the bottom surface of the insulating medium is 30mm, the height of the insulating medium is 10mm, the inner diameter of the annular grounding electrode is 2mm, the outer diameter of the annular grounding electrode is 10mm, the outer diameter of the annular high-voltage electrode is 25mm, the aperture of the through hole or the first hole of the insulating medium is 1mm, 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 and the diameter of the second electrode are 0.5mm and the distance of the first electrode and the second electrode is 1 mm.
The working method of the device for improving the jet intensity of the annular electrode exciter is used for flow control of an aircraft, and comprises three modes:
in the first mode: when the aircraft flies at subsonic speed, the dielectric barrier discharge exciter works, the plasma synthetic jet exciter is closed, and low-speed jet flow generated by the work of the dielectric barrier discharge exciter can play a control role;
in the second mode: when the aircraft flies at transonic speed, the dielectric barrier discharge exciter is closed, the plasma synthetic jet exciter works, and high-speed jet flow generated by the working of the plasma synthetic jet exciter can meet the requirement of flow control;
in the third mode: when the aircraft flies at supersonic speed or hypersonic speed, the dielectric barrier discharge exciter and the plasma synthetic jet exciter work simultaneously to realize the flow control of the external flow field of the aircraft.
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 position, can be used for the aircraft with various flight speeds, can be used for the flow control of a low-speed aircraft due to the jet velocity generated by a dielectric barrier discharge exciter, can be used for the flow control of a high-speed aircraft due to the fact that the velocity generated by a plasma synthetic jet exciter can reach more than 300m/s, and can be used for the flow control of a high-speed aircraft due to the common use of two exciters;
(3) the gas source is not required to supply, the gas is sourced from outside air, the gas can be automatically backfilled under the action of pressure difference, and the jet flows generated by the two plasma exciters belong to zero-mass-flux jet flows;
(4) the dielectric barrier discharge exciter and the plasma synthetic jet exciter can share one power supply through circuit design, so that the two exciters can be better coordinately controlled, and the jet generation processes of the two exciters are synchronous.
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 an isometric view of the device for increasing the jet intensity of the annular electrode dielectric barrier discharge exciter of the invention.
FIG. 4 is a top view of the device for improving the jet strength of the annular electrode dielectric barrier discharge actuator of the invention.
FIG. 5 is a side view of the device for improving the jet intensity of the annular electrode dielectric barrier discharge actuator of the invention.
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
Referring to fig. 1, a device for improving the jet intensity of a ring electrode 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 ring-shaped high voltage electrode 3 and a ring-shaped ground electrode 4, the plasma synthetic jet exciter comprises an exciter cavity 2, a first electrode 5 and a second electrode 6, a through hole is formed between the upper surface and the lower surface of the insulating medium 1, the ring-shaped high voltage electrode 3 is positioned on the upper surface of the insulating medium 1, the ring-shaped ground electrode 4 is positioned in the insulating medium 1, the inner diameter of the ring-shaped ground electrode 4 embedded in the insulating medium 1 is larger than the diameter of the through hole, so that the ring-shaped ground electrode 4 is ensured not to be exposed in the air, and the central axis of the through hole passes through the central holes of the ring-shaped high voltage electrode 3 and the ring-shaped ground electrode 4, 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, the first electrode 5 and the second electrode 6 respectively extend into the exciter cavity 2, and 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 improving the jet intensity of a ring electrode 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 ring-shaped high voltage electrode 3 and a ring-shaped grounding electrode 4, the plasma synthetic jet exciter comprises a first electrode 5 and a second electrode 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 ring-shaped high voltage electrode 3 is positioned on the upper surface of the insulating medium 1, the ring-shaped grounding electrode 4 is positioned in the insulating medium 1, the inner diameter of the ring-shaped grounding electrode 4 embedded in the insulating medium 1 is larger than the diameter of the first hole, so as to ensure that the ring-shaped grounding electrode 4 is not exposed to the air, and the first hole penetrates through the central hole of the ring-shaped grounding electrode 4, the central axis of the first hole penetrates through the central hole of the annular high-voltage electrode 3, the inner cavity of the second hole forms an exciter cavity 2, the first electrode 5 and the second electrode 6 respectively extend into the exciter cavity 2 from the insulating medium 1, and the high-voltage power supply supplies power to the dielectric barrier discharge exciter and the plasma synthetic jet exciter.
Further, the central axis of the through-hole or first hole coincides with the central axis of the annular high voltage electrode 3 and the annular ground electrode 4.
Further, the annular high voltage electrode 3 and the annular grounding electrode 4 are arranged in parallel.
Further, the outer diameter of the annular ground electrode 4 is equal to the inner diameter of the annular high voltage electrode 3.
Further, the material of the insulating medium 1 and/or the exciter cavity 2 is polytetrafluoroethylene, ceramic or boron nitride.
Further, the material of the annular high voltage electrode 3, the annular grounding electrode 4, the first electrode 5 and the second electrode 6 is copper or tungsten.
Further, the insulating medium 1 is cylindrical, the diameter of the bottom surface is 30mm, the height of the bottom surface is 10mm, the inner diameter of the annular grounding electrode 4 is 2mm, the outer diameter of the annular grounding electrode 4 is 10mm, the inner diameter of the annular high-voltage electrode 3 is 10mm, the outer diameter of the annular high-voltage electrode 3 is 25mm, the aperture of the through hole or the first hole of the insulating medium 1 is 1mm, the diameter of the exciter cavity 2 is 4mm, the height of the exciter cavity is 5mm, and the diameter of the first electrode 5 and the diameter of the second electrode 6 are 0.5mm and the distance of the first electrode 5 and the second electrode 6 is 1 mm.
The high-voltage power supply supplies power for the dielectric barrier discharge exciter and the plasma synthetic jet exciter, when the voltage between the annular high-voltage electrode 3 and the annular grounding electrode 4 reaches the breakdown voltage, plasma is generated on the surface of the insulating medium 1, the plasma can induce fluid around the electrode ring to flow towards the direction vertical to the surface of the insulating medium 1, and meanwhile, thrust opposite to the inducing direction is generated. When the voltage between the first electrode 5 and the second electrode 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 quickly sprayed out under the action of the difference between the internal pressure and the external pressure to form high-speed jet flow perpendicular to the surface of the insulating medium 1, and the high-speed jet flow and jet flow generated by the dielectric barrier discharge exciter act on the aircraft together.
In order to realize synchronous power supply of the annular high-voltage electrode 3, the annular grounding electrode 4 and the first electrode 5 and the second electrode 6, a set of circuit diagram is designed for the high-voltage power supply, and as shown in fig. 6, the overall discharge frequency is adjusted by controlling the on-off of the 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 is 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 annular high-voltage electrode 3, the annular grounding electrode 4, the first electrode 5 and the second electrode 6 in the cavity. Thus, the switch of the dc power supply E, IGBT and the transformer M together constitute a high voltage pulsed power supply. Next, the right circuit will be described. The high-voltage pulse power supply is connected with the two branches in parallel. The two branches are respectively a dielectric barrier discharge exciter and a plasma synthetic jet exciter. In the branch where the dielectric barrier discharge exciter is located, an electrode ring DBD formed by the annular high-voltage electrode 3 and the annular grounding electrode 4, a resistor R2 and a switch S3 are connected in series, and the resistor R2 mainly plays a role in protecting a circuit and adjusting the voltage. Similarly, in the branch where the plasma synthetic jet actuator is located, there is also a resistor R1, a capacitor C and a plasma synthetic jet actuator a. In which a capacitor C is connected in parallel with an actuator a and then in series with a 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. There is a switch in each of the two branches for controlling their operating states, thereby implementing three operating modes. The three operating modes are: a first mode dielectric barrier discharge actuator working mode (S3 closed, S2 open), a second mode plasma synthetic jet actuator discharge mode (S3 open, S2 closed) and a third mode jet enhancement mode (S3 closed, S2 closed).
In the first mode: when the aircraft flies at subsonic speed, the dielectric barrier discharge exciter works, the plasma synthetic jet exciter is closed, and low-speed jet flow generated by the work of the dielectric barrier discharge exciter can play a control role;
in the second mode: when the aircraft flies at transonic speed, the dielectric barrier discharge exciter is closed, the plasma synthetic jet exciter works, and high-speed jet flow generated by the working of the plasma synthetic jet exciter can meet the requirement of flow control;
in the third mode: when the aircraft flies at supersonic speed or hypersonic speed, the dielectric barrier discharge exciter and the plasma synthetic jet exciter work simultaneously to realize the flow control of the external flow field of the aircraft.
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 (14)
1. The working method of the device for improving the jet intensity of the annular electrode exciter is characterized by comprising 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 an annular high-voltage electrode (3) and an annular grounding electrode (4), the plasma synthetic jet exciter comprises an exciter cavity (2), a first electrode (5) and a second electrode (6), a through hole is formed between the upper surface and the lower surface of the insulating medium (1), the annular high-voltage electrode (3) is positioned on the upper surface of the insulating medium (1), the annular grounding electrode (4) is positioned in the insulating medium (1), the central axis of the through hole penetrates through central holes of the annular high-voltage electrode (3) and the annular grounding electrode (4), and 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), the first electrode (5) and the second electrode (6) respectively extend into the exciter cavity (2), the high-voltage power supply supplies power for the dielectric barrier discharge exciter and the plasma synthetic jet exciter,
the device is used for flow control of an aircraft, and the working method comprises three modes:
in the first mode: when the aircraft flies at subsonic speed, the dielectric barrier discharge exciter works, the plasma synthetic jet exciter is closed, and low-speed jet flow generated by the work of the dielectric barrier discharge exciter can play a control role;
in the second mode: when the aircraft flies at transonic speed, the dielectric barrier discharge exciter is closed, the plasma synthetic jet exciter works, and high-speed jet flow generated by the working of the plasma synthetic jet exciter can meet the requirement of flow control;
in the third mode: when the aircraft flies at supersonic speed or hypersonic speed, the dielectric barrier discharge exciter and the plasma synthetic jet exciter work simultaneously to realize the flow control of the external flow field of the aircraft.
2. The working method of the device for improving the jet intensity of the ring electrode exciter according to claim 1, characterized in that the central axis of the through hole is coincident with the central axes of the ring high-voltage electrode (3) and the ring grounding electrode (4).
3. The working method of the device for improving the jet intensity of the annular electrode exciter according to claim 2, characterized in that the annular high-voltage electrode (3) and the annular grounding electrode (4) are placed in parallel.
4. Method of operating a device for increasing jet intensity of a ring electrode actuator according to claim 2, characterized in that the outer diameter of the ring ground electrode (4) is equal to the inner diameter of the ring high voltage electrode (3).
5. The working method of the device for improving the jet intensity of the annular electrode exciter according to claim 2, characterized in that the material of the insulating medium (1) and/or the exciter cavity (2) is polytetrafluoroethylene, ceramic or boron nitride.
6. The working method of the device for improving the jet intensity of the ring electrode exciter according to claim 2, characterized in that the materials of the ring electrode high-voltage electrode (3), the ring electrode ground electrode (4), the first electrode (5) and the second electrode (6) are copper or tungsten.
7. The working method of the device for improving the jet intensity of the annular electrode exciter according to claim 2 is characterized in that the insulating medium (1) is cylindrical, the bottom surface of the insulating medium is 30mm in diameter and 10mm in height, the annular grounding electrode (4) is 2mm in inner diameter and 10mm in outer diameter, the annular high-voltage electrode (3) is 10mm in inner diameter and 25mm in outer diameter, the hole diameter of the through hole of the insulating medium (1) is 1mm, the exciter cavity (2) is 4mm in diameter and 5mm in height, and the first electrode (5) and the second electrode (6) are 0.5mm in diameter and 1mm apart.
8. The working method of the device for improving the jet intensity of the annular electrode exciter is characterized by comprising 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 an annular high-voltage electrode (3) and an annular grounding electrode (4), the plasma synthetic jet exciter comprises a first electrode (5) and a second electrode (6), the upper surface and the lower surface of the insulating medium (1) are penetrated through by a first hole and a second hole which are communicated with each other, the annular high-voltage electrode (3) is positioned on the upper surface of the insulating medium (1), the annular grounding electrode (4) is positioned in the insulating medium (1), the first hole penetrates through a central hole of the annular grounding electrode (4), and the central axis of the first hole penetrates through the central hole of the annular high-voltage electrode (3), the inner cavity of the second hole forms an exciter cavity (2), the first electrode (5) and the second electrode (6) respectively extend into the exciter cavity (2) from the insulating medium (1), the high-voltage power supply supplies power for the dielectric barrier discharge exciter and the plasma synthetic jet exciter,
the device is used for flow control of an aircraft, and the working method comprises three modes:
in the first mode: when the aircraft flies at subsonic speed, the dielectric barrier discharge exciter works, the plasma synthetic jet exciter is closed, and low-speed jet flow generated by the work of the dielectric barrier discharge exciter can play a control role;
in the second mode: when the aircraft flies at transonic speed, the dielectric barrier discharge exciter is closed, the plasma synthetic jet exciter works, and high-speed jet flow generated by the working of the plasma synthetic jet exciter can meet the requirement of flow control;
in the third mode: when the aircraft flies at supersonic speed or hypersonic speed, the dielectric barrier discharge exciter and the plasma synthetic jet exciter work simultaneously to realize the flow control of the external flow field of the aircraft.
9. The working method of the device for improving the jet intensity of the annular electrode exciter according to claim 8, characterized in that the central axis of the first hole is coincident with the central axes of the annular high-voltage electrode (3) and the annular grounding electrode (4).
10. The working method of the device for improving the jet intensity of the annular electrode exciter according to claim 9, characterized in that the annular high-voltage electrode (3) and the annular grounding electrode (4) are placed in parallel.
11. Method of operating a device for increasing jet intensity of a ring electrode actuator according to claim 9, characterized in that the outer diameter of the ring ground electrode (4) is equal to the inner diameter of the ring high voltage electrode (3).
12. Method of operating a device for increasing jet intensity of a ring electrode actuator according to claim 9, characterized in that the material of the insulating medium (1) and/or the actuator cavity (2) is polytetrafluoroethylene, ceramic or boron nitride.
13. The working method of the device for improving the jet intensity of the ring electrode exciter according to claim 9, characterized in that the materials of the ring electrode high-voltage electrode (3), the ring electrode ground electrode (4), the first electrode (5) and the second electrode (6) are copper or tungsten.
14. The working method of the device for improving the jet intensity of the annular electrode exciter according to claim 9, is characterized in that the insulating medium (1) is cylindrical, the bottom surface of the insulating medium is 30mm in diameter and 10mm in height, the annular grounding electrode (4) is 2mm in inner diameter and 10mm in outer diameter, the annular high-voltage electrode (3) is 10mm in inner diameter and 25mm in outer diameter, the aperture of a first hole of the insulating medium (1) is 1mm, the exciter cavity (2) is 4mm in diameter and 5mm in height, and the first electrode (5) and the second electrode (6) are 0.5mm in diameter and 1mm apart.
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