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
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- 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
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- 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
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- H—ELECTRICITY
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- 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
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Abstract
The invention discloses a device and a method for realizing aircraft flow control based on a plasma exciter, wherein the device 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 a first electrode rod and a second electrode rod, the insulating medium is penetrated through by a first hole and a second hole, the high-voltage electrode block is positioned on the upper surface of the insulating medium, the grounding electrode block is positioned in the insulating medium, an exciter cavity is formed by the inner cavity of the second hole, and the first electrode rod and the second electrode rod respectively extend into the exciter cavity from the insulating medium. The jet flow generated by the dielectric barrier discharge exciter can be used for controlling the separation of the surface flow field of the aircraft, reducing the flight resistance and improving the lift force; the jet generated by the plasma synthetic jet actuator can be used for changing the flight attitude of the aircraft and providing the thrust required by flight.
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)
1. A method for realizing aircraft flow control of a device for realizing aircraft flow control based on a plasma 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 a high-voltage electrode block (3) and a grounding 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 positioned on the upper surface of the insulating medium (1) on one side of the through hole, the grounding electrode block (4) is positioned in the insulating medium (1) on 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), the first electrode bar (5) and the second electrode bar (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 arranged on the surface of the wing of the aircraft,
the method includes 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 medium (1)xDirection;
in the second mode: dielectric barrier discharge actuator off, VyThe plasma synthetic jet actuator works, and the jet direction generated by the plasma synthetic jet actuator is V vertical to the surface of the insulating medium (1)yDirection;
in the third mode: medium resistorThe jet flow direction generated by the simultaneous work of the discharge blocking exciter and the plasma synthetic jet flow exciter is V parallel to the surface of the insulating medium (1)xV in the direction perpendicular to the surface of the insulating medium (1)yAnd (4) direction.
2. The method for realizing the aircraft flow control of the plasma exciter-based device for realizing the aircraft flow control is characterized in that the distance between the high-voltage electrode block (3) and the grounding electrode block (4) is larger than the diameter of the through hole.
3. The method for realizing the aircraft flow control based on the plasma exciter of the device for realizing the aircraft flow control according to the claim 1, characterized in that the high voltage electrode block (3) and the grounding electrode block (4) are placed in parallel.
4. The method for realizing the aircraft flow control of the plasma exciter-based device for realizing the aircraft flow control according to claim 1, characterized in that the material of the insulating medium (1) and/or the exciter cavity (2) is quartz glass, ceramic or boron nitride.
5. The method for realizing the aircraft flow control based on the plasma exciter of the device for realizing the aircraft flow control is characterized in that the materials of the high-voltage electrode block (3), the grounding electrode block (4), the first electrode bar (5) and the second electrode bar (6) are copper or tungsten.
6. The method for realizing the aircraft flow control of the plasma exciter-based device for realizing the aircraft flow control is characterized in that the high-voltage electrode block (3) and the grounding electrode block (4) have the length of 50mm, the width of 15mm and the thickness of 1mm, the horizontal distance between the two electrode blocks 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 second electrode rod (6) is 0.5mm and the distance of 1 mm.
7. A method for realizing aircraft flow control of a device for realizing aircraft flow control based on a plasma exciter is characterized in that the device comprises a dielectric barrier discharge exciter, at least one plasma synthetic jet exciter, an insulating medium (1) and a high-voltage power supply, the dielectric barrier discharge exciter comprises a high-voltage electrode block (3) and a grounding 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, the high-voltage electrode block (3) is positioned on the upper surface of the insulating medium (1) on one side of the first hole, the grounding electrode block (4) is positioned in the insulating medium (1) on the other side of the first hole, and the inner cavity of the second hole forms an exciter cavity (2), the first electrode bar (5) and the second electrode bar (6) respectively extend into the exciter cavity (2) from an insulating medium (1), the high-voltage power supply supplies power to the dielectric barrier discharge exciter and the plasma synthetic jet exciter, the device is arranged on the surface of the wing of the aircraft,
the method includes 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 medium (1)xDirection;
in the second mode: dielectric barrier discharge actuator off, VyThe plasma synthetic jet actuator works, and the jet direction generated by the plasma synthetic jet actuator is V vertical to the surface of the insulating medium (1)yDirection;
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 medium (1)xV in the direction perpendicular to the surface of the insulating medium (1)yAnd (4) direction.
8. A method for realizing aircraft flow control based on a plasma exciter of an apparatus for realizing aircraft flow control according to claim 7, characterized in that the distance between the high voltage electrode block (3) and the ground electrode block (4) is larger than the diameter of the first hole.
9. The method for realizing the aircraft flow control based on the plasma exciter of the device for realizing the aircraft flow control is characterized in that the high-voltage electrode block (3) and the grounding electrode block (4) are arranged in parallel.
10. The method for realizing the aircraft flow control based on the device for realizing the aircraft flow control of the plasma exciter according to claim 7, wherein the number of the plasma synthetic jet exciters is more than two.
11. A method for realizing aircraft flow control based on a plasma exciter-based device according to claim 7, characterized in that the material of the insulating medium (1) and/or the exciter cavity (2) is quartz glass, ceramic or boron nitride.
12. The method for realizing the aircraft flow control based on the plasma exciter of the device for realizing the aircraft flow control is characterized in that the materials of the high-voltage electrode block (3), the grounding electrode block (4), the first electrode bar (5) and the second electrode bar (6) are copper or tungsten.
13. The method for realizing the aircraft flow control based on the plasma exciter of the device for realizing the aircraft flow control is characterized in that the high-voltage electrode block (3) and the grounding electrode block (4) have the length of 50mm, the width of 15mm and the thickness of 1mm, the horizontal distance between the two electrode blocks 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 second electrode rod (6) is 0.5mm and the distance of 1 mm.
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| CN113423168A (en) * | 2021-06-25 | 2021-09-21 | 中国人民解放军国防科技大学 | Magnetic control vector high-speed plasma synthetic jet actuator |
| 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 stall-preventing/ice-preventing 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 | Plasma synthetic jet flow vortex generating device for flow control |
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