CN104202898A - Hypersonic speed flowing energy utilization based zero-energy-consumption zero-mass synthetic jet device - Google Patents
Hypersonic speed flowing energy utilization based zero-energy-consumption zero-mass synthetic jet device Download PDFInfo
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Abstract
The invention discloses a hypersonic speed flowing energy utilization based zero-energy-consumption zero-mass synthetic jet device. The hypersonic speed flowing energy utilization based zero-energy-consumption zero-mass synthetic jet device comprises an air source unit, a power source unit and a synthetic jet exciter; the air source unit comprises a windward concave chamber, an air collection pot and a solenoid valve; the power source unit comprises a thermoelectricity conversion module, an input circuit, a high-pressure power source, a high-pressure direct current circuit and a high-pressure pulse circuit; the synthetic jet exciter comprises an exciter casing; a main discharging electrode, an ignition positive electrode and an ignition negative electrode are arranged inside the exciter casing; an air source inlet and at least one jet outlet are formed in the exciter casing; the main discharging electrode, the ignition positive electrode and the ignition negative electrode are connected with the power source unit; the air source inlet is communicated with the magnetic valve through an air supply pipeline. The hypersonic speed flowing energy utilization based zero-energy-consumption zero-mass synthetic jet device has the advantages of being good in environmental suitability, short in exciter chamber cooling and suction recovery time, high in exciter working frequency and response speed and small and light, reducing spacecraft thermal damage, converting harmful heat into useful energy and being high in energy utilization efficiency.
Description
Technical field
The present invention relates to the active Flow Control technology of high-speed aircraft internal and external flow field, be specifically related to a kind of zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy.
Background technology
Thereby synthesizing jet-flow excitor is to produce the technology that successive jet is realized Active Flow Control by exciter outlet opening seam in flow field, rely on its response rapidly, control the advantage such as flexible and show wide application prospect.In order to realize the mobile control in high speed, ultrahigh speed flow field, U.S. John Hopkins University Experiment of Applied Physics chamber has proposed a kind of synthesizing jet-flow excitor based on plasma for 2003, and this exciter consists of a housing with outlet and anode and cathode electrode.Its work period can be divided into three phases: the first stage is the energy deposition stage, by high-voltage energy storage power supply, between two electrodes, forms sparkover, intracavity gas is ionized and be rapidly heated, boost, and forms plasma; Second stage is that jet is discharged the stage, and the gas after boosting, by outlet ejection at a high speed, is formed for the plasma jet that flow field is controlled; Phase III is air-breathing recovery phase, and exciter inside in negative pressure, makes extraneous gas backfill due to the ejection of jet, thereby prepares to enter the next work period.But this type of synthesizing jet-flow excitor is also existing following key issue aspect high-speed aircraft active Flow Control at present: a 1) air feed difficult problem.Because this type of synthesizing jet-flow excitor only depends on the negative pressure natural aspiration of exciter cavity, simultaneously the natural cooling time of housing long, cause the air-breathing recovery phase time longer, operating frequency is limited.And under the near space low atmospheric density environment of high-speed aircraft flight, exciter air inflow die-offs, and performance significantly reduces, and causes the environmental suitability of exciter poor.2) a power supply difficult problem.Because realization high speed, the moving control of hypervelocity flow field flow need plasma jet to have quite high energy level, therefore process gas discharge needs huge power input, in order to guarantee that exciter is long-time, steady operation, the volume of high-voltage energy storage power supply, weight will be excessive, are difficult to meet high-speed aircraft for miniaturization, light-weighted requirement.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of good environmental adaptability, exciter cavity is cooling and the time air-breathing recovery is short, the operating frequency of exciter and response speed is high, miniaturization, lightweight, can reduce aircraft fire damage, will be harmful to heat and change the useful energy into, the zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy that energy utilization efficiency is high.
In order to solve the problems of the technologies described above, the technical solution used in the present invention is:
A kind of zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy, comprise gas source unit, power subsystem and synthesizing jet-flow excitor, described gas source unit comprises cavity, air collector and electromagnetically operated valve windward, between described cavity windward, air collector and electromagnetically operated valve, by steam line, be communicated with, described cavity is windward located at the head of described high energy synthesizing jet-flow device place aircraft; Described synthesizing jet-flow excitor comprises exciter housing, in described exciter housing, be provided with and be the radial main discharge electrode of arranging successively, igniting positive pole and igniting negative pole, described exciter housing is provided with air source inlet and at least one jet exit, described main discharge electrode, igniting is anodal and igniting negative pole is connected with power subsystem respectively, between described air source inlet and electromagnetically operated valve, by steam line, is communicated with; Described power subsystem comprises thermo-electric conversion module, input circuit, high voltage source, hvdc circuit and high-voltage pulse circuit, the output of described thermo-electric conversion module is connected with high voltage source by input circuit, described high voltage source is connected with main discharge electrode by hvdc circuit, and described high voltage source is connected with igniting positive pole, igniting negative pole respectively by high-voltage pulse circuit.
Preferably, the angle between described main discharge electrode, igniting positive pole is 90 degree, and described igniting angle anodal and that light a fire between negative pole is 90 degree, and the spacing between igniting positive pole and igniting negative pole is less than the spacing between main discharge electrode, igniting positive pole.
Preferably, described thermo-electric conversion module comprises a plurality of thermoelectric power generations unit, described thermoelectric power generation unit comprises P type thermo-electric converting material unit, N-type thermo-electric converting material unit and conducting strip, described P type thermo-electric converting material unit, the N-type thermo-electric converting material unit all thermal source of relatively described high energy synthesizing jet-flow device place aircraft is arranged vertically, between described P type thermo-electric converting material unit and N-type thermo-electric converting material unit, by conducting strip, be connected, and described a plurality of thermoelectric power generations are connected by conducting strip between unit, or in parallel, or the mode that series and parallel connections mixes connects and constitutes thermo-electric conversion module.
Preferably, the lip of described cavity is windward pointed or circular.
Preferably, the tubular structure of described exciter housing for adopting glass ceramics or boron nitride ceramics to make.
Preferably, described main discharge electrode, the anodal and cylindrical structural of negative pole for adopting tungsten or tungsten alloy making to obtain of lighting a fire of lighting a fire, and the end of described main discharge electrode, igniting positive pole and igniting negative pole is wedge shape.
Preferably, described jet exit is shaped as slit shape or straight-through tubular or shrinks tubular or expansion tubular or Rafael nozzle shape.
The zero energy consumption zero mass synthesizing jet-flow device that the present invention is based on hypersonic stream energy utilization has following advantage:
1, gas source unit of the present invention comprises cavity, air collector and electromagnetically operated valve windward, between cavity, air collector and electromagnetically operated valve, by steam line, be communicated with windward, cavity is located at the head of high energy synthesizing jet-flow device place aircraft windward, make full use of cavity windward and collect outside high speed incoming flow gas (being hypersonic speed flow), in air collector, by high speed incoming flow kinetic transformation, be the potential energy of gas in tank, for synthesizing jet-flow excitor is stablized air feed supercharging, solve the difficult problem that under low density gas environment, exciter air inflow die-offs, made exciter there is better environmental suitability; Compare with negative pressure natural aspiration mode, the present invention can shorten the time of the cooling and air-breathing recovery of exciter cavity greatly, thereby increases substantially operating frequency and the response speed of exciter.
2, power subsystem of the present invention comprises thermo-electric conversion module, input circuit, high voltage source, hvdc circuit and high-voltage pulse circuit, the output of thermo-electric conversion module is connected with high voltage source by input circuit, high voltage source is connected with main discharge electrode by hvdc circuit, and high voltage source is connected with igniting positive pole, igniting negative pole respectively by high-voltage pulse circuit, without external high pressure accumulation power supply, effectively utilize the heat energy that enriches that Aerodynamic Heating in the high-speed aircraft course of work produces, be conducive to realize miniaturization, the lightweight of power supply.
3, gas source unit of the present invention and power subsystem are all the comprehensive utilizations based on hypersonic speed flow on aircraft and heat, without additional energy source and source of the gas, by total energy approach, high speed incoming flow is converted into high energy synthesizing jet-flow, by hypersonic flow motivating gas supercharge and pneumatic thermal transition function, realize the comprehensive utilization of energy, thereby solve and effectively solve above-mentioned air feed and a power supply difficult problem, utilize three electrode plasma synthesis jet-flow excitor to produce high energy synthesizing jet-flow, the active Flow Control that can be used for high-speed aircraft internal and external flow field, a kind of brand-new " zero energy consumption ", the synthesizing jet-flow technology of " zero mass ".
4, gas source unit of the present invention comprises cavity, air collector and electromagnetically operated valve windward, between cavity, air collector and electromagnetically operated valve, by steam line, be communicated with windward, cavity is located at the head of high energy synthesizing jet-flow device place aircraft windward, the cavity windward that is positioned at Vehicle nose can reduce the Aerodynamic Heating of head, reduces the fire damage of aircraft; In addition thermo-electric conversion module concentrates place also to have certain thermolysis for aircraft Aerodynamic Heating, can change the useful energy into by being harmful to heat, improves energy utilization efficiency.
Accompanying drawing explanation
Fig. 1 is the structural representation that the embodiment of the present invention is applied to Vehicle nose.
Fig. 2 is the structural representation of thermo-electric conversion module in the embodiment of the present invention.
Marginal data: 1, gas source unit; 11, cavity windward; 12, air collector; 13, electromagnetically operated valve; 14, steam line; 2, power subsystem; 21, thermo-electric conversion module; 22, input circuit; 23, high voltage source; 24, hvdc circuit; 25, high-voltage pulse circuit; 26, thermal source; 27, P type thermo-electric converting material unit; 28, N-type thermo-electric converting material unit; 29, conducting strip; 3, synthesizing jet-flow excitor; 31, exciter housing; 32, main discharge electrode; 33, igniting is anodal; 34, igniting negative pole; 35, air source inlet; 36, jet exit.
Embodiment
As depicted in figs. 1 and 2, the zero energy consumption zero mass synthesizing jet-flow device of the present embodiment based on hypersonic stream energy utilization comprises gas source unit 1, power subsystem 2 and synthesizing jet-flow excitor 3, gas source unit 1 comprises cavity 11, air collector 12 and electromagnetically operated valve 13 windward, between cavity 11, air collector 12 and electromagnetically operated valve 13, by steam line 14, be communicated with windward, cavity 11 is located at the head of high energy synthesizing jet-flow device place aircraft windward; Synthesizing jet-flow excitor 3 comprises exciter housing 31, in exciter housing 31, be provided with and be the radial main discharge electrode 32 of arranging successively, igniting anodal 33 and igniting negative pole 34, exciter housing 31 is provided with air source inlet 35 and a jet exit 36, main discharge electrode 32, igniting anodal 33 and igniting negative pole 34 are connected with power subsystem 2 respectively, between air source inlet 35 and electromagnetically operated valve 13, by steam line 14, are communicated with; Power subsystem 2 comprises thermo-electric conversion module 21, input circuit 22, high voltage source 23, hvdc circuit 24 and high-voltage pulse circuit 25, the output of thermo-electric conversion module 21 is connected with high voltage source 23 by input circuit 22, high voltage source 23 is connected with main discharge electrode 32 by hvdc circuit 24, and high voltage source 23 is connected with igniting positive pole 33, igniting negative pole 34 respectively by high-voltage pulse circuit 25.The work source of the gas that the gas source unit 1 of the present embodiment is used is not to be provided by gas cylinder, but by the hypersonic speed flow producing in aircraft flight process, by " punching press gas collection principle ", directly from upper atmosphere, obtain, cavity 11 can have different bores and aspect ratio windward, wherein aspect ratio is larger, reduction effect to Aerodynamic Heating amount is better, cavity diameter is larger, punching press gas collection amount is larger, first hypersonic speed flow is collected and is entered air collector 12 by cavity windward 11, gases at high pressure in air collector 12 must enter via electromagnetically operated valve 13 inner chamber of synthesizing jet-flow excitor 3, electromagnetically operated valve 13 is only opened at the air-breathing recovery phase of exciter, when synthesizing jet-flow device is not worked, electromagnetically operated valve 13 is in normally off, because electromagnetically operated valve 13 is in normally off, make the larger pressure differential of formation between air collector 12 and the cavity of synthesizing jet-flow excitor 3, and make high-temperature region only limit to the lip of cavity 11 windward, the temperature of cavity 11 bottoms is very low windward, therefore the wall temperature of air collector 12 can not raise yet, therefore the gas in air collector 12 can be used as the use of high pressure low temperature source of the gas, thereby realized the energy utilization of hypersonic speed flow, and owing to not needing gas cylinder, this plenum system has reduced the required weight of carrying of aircraft greatly, can reach the zero zero mass effect of energy consumption.In aircraft hypersonic flight process, some position of Vehicle nose and fuselage is because the huge Aerodynamic Heating effect of high speed incoming flow will have very high temperature, thermo-electric conversion module 21 is installed on head or the fuselage Aerodynamic Heating larger part of high energy synthesizing jet-flow device place aircraft, by thermoelectricity, change the head of aircraft or fuselage Aerodynamic Heating larger part heat energy are converted into electric energy, form electrical potential difference, and the electric energy that thermo-electric conversion module 21 is obtained is stored into high voltage source 23 by input circuit 22, 23 pairs of input signals of high voltage source boost, filtering and rectification, thereby for synthesizing jet-flow excitor 3 provides two-way power supply signal, one tunnel is the adjustable high-voltage pulse circuit of frequency 25, another road is the adjustable hvdc circuit of voltage and current 24, thereby can realize and the heat of Vehicle nose or fuselage Aerodynamic Heating larger part is carried out to comprehensive utilization be used for realizing to main discharge electrode 32, igniting anodal 33 and igniting negative pole 34 threes' power supply.
In the present embodiment, the steam line 14 between cavity 11, air collector 12 is provided with unidirectional valve 15 windward.From hypersonic the failing to be convened for lack of a quorum of cavity 11 windward, through unidirectional valve 15, enter air collector 12, due to the one-way conduction characteristic of unidirectional valve 15, therefore can prevent the reverse outflow of air collector 12 mesohigh gas, build-up of pressure loss.
In the present embodiment, angle between main discharge electrode 32, igniting anodal 33 is 90 degree, angle between igniting anodal 33 and igniting negative pole 34 is 90 degree, and the spacing between igniting anodal 33 and igniting negative pole 34 is less than the spacing between main discharge electrode 32, igniting anodal 33.
The lip of cavity 11 can be set to pointed or circular as required windward.In the present embodiment, the lip of cavity 11 is circular windward, and circular lip can be eliminated recirculating zone and reduce inside cavity and add heat; In addition, if cavity 11 adopts pointed, pointed lip Hui Vehicle nose to produce recirculating zone to reduce head outer surface Aerodynamic Heating amount windward.
In the present embodiment, the tubular structure of exciter housing 31 for adopting glass ceramics or boron nitride ceramics to make.Glass ceramics or boron nitride ceramics have good, the machinable advantage of insulation, and insulation property are reliable, easy to process.
In the present embodiment, main discharge electrode 32, igniting anodal 33 and igniting negative pole 34 are for adopting tungsten or tungsten alloy to make the cylindrical structural obtaining, tungsten or tungsten alloy arc ablation resistance, long service life, and the end of main discharge electrode 32, igniting anodal 33 and igniting negative pole 34 is wedge shape, end is wedge shape can reduce required puncture voltage, thereby lower to the requirement of power subsystem 2.
In the present embodiment, the quantity of jet exit 36 is one, in addition also can adopt as required the jet exit 36 of greater number, the shape of while jet exit 36 is selection slit shape or straight-through tubular or contraction tubular or expansion tubular or Rafael nozzle shape as required.In the present embodiment, the shape of jet exit 36 leads directly to tubular, and diameter phi 2mm can select to arrange different angles of heel or the angle of pitch as required.
As depicted in figs. 1 and 2, thermo-electric conversion module 21 comprises a plurality of thermoelectric power generations unit, thermoelectric power generation unit comprises P type thermo-electric converting material unit 27, N-type thermo-electric converting material unit 28 and conducting strip 29, P type thermo-electric converting material unit 27, the N-type thermo-electric converting material unit 28 all thermal source 26 of relative high energy synthesizing jet-flow device place aircraft is arranged vertically, between P type thermo-electric converting material unit 27 and N-type thermo-electric converting material unit 28, by conducting strip 29, be connected, and a plurality of thermoelectric power generations are connected by conducting strip 29 between unit, or in parallel, or the mode that series and parallel connections mixes connects and constitutes thermo-electric conversion module 21.The key component of power subsystem 2 is thermo-electric conversion modules 21, larger SiGe alloy or the NaCoO of thermoelectricity quality factor (ZT value) when P type thermo-electric converting material unit 27, N-type thermo-electric converting material unit 28 all adopt high temperature
4or gradient-structure thermoelectric material makes, and by different preparation technologies, obtain N-type and two kinds of dissimilar thermo-electric converting materials of P type respectively.
The focus conversion work principle of thermo-electric conversion module 21 is as follows: 28Zhong hole, N-type thermo-electric converting material unit is few son, and free electron is for how sub, and the charge carrier of conduction is mainly free electron; 27Zhong hole, P type thermo-electric converting material unit is for how sub, and free electron is few son, and the charge carrier of conduction is mainly hole.P type thermo-electric converting material unit 27, N-type thermo-electric converting material the unit 28 all thermal source 26 of relative high energy synthesizing jet-flow device place aircraft are arranged vertically, when not yet setting up the temperature difference for thermo-electric conversion module 21 two ends, the charge carrier of P type thermo-electric converting material unit 27, N-type thermo-electric converting material unit 28 is for being uniformly distributed; After once the temperature gradient at thermo-electric conversion module 21 two ends is set up, charge carrier in hot junction just has larger kinetic energy, be tending towards to cold junction diffusion and pile up at cold junction, making the charge carrier number of cold junction more than hot junction, the accumulation of this electric charge will be destroyed the electric neutrality in material.On the other hand, electric charge causes setting up a built-in field in material in the accumulation of cold junction, to stop hot junction charge carrier to the further diffusion of cold junction, when the motion of charge carrier reaches balance, in material, without the displacement of net charge, the electrical potential difference now forming at material two ends is exactly Seebeck electromotive force.For N-type thermo-electric converting material unit 28, free electron will be piled up at cold junction as charge carrier, make cold junction with negative electrical charge; For P type thermo-electric converting material unit 27, hole will be piled up at cold junction as charge carrier, make cold junction with positive charge, therefore P type thermo-electric converting material unit 27, N-type thermo-electric converting material unit 28 are positioned over to thermal source 26 places of high energy synthesizing jet-flow device place aircraft, and connect with conducting strip 29, just can utilize thermo-electric generation.
The course of work of the synthesizing jet-flow excitor 3 of the present embodiment is as follows: the first stage (energy deposition stage): high-voltage pulse circuit 25 is by positive pole 33 and igniting negative pole 34 voltage the puncturing for air of output up to tens of kilovolts of lighting a fire, set up conductive channel and the electric arc that ignites, hvdc circuit 24 is for producing sparkover and injecting power by main discharge electrode 32 after air breakdown, and sparkover meeting produces gas-heated effect fast to the air in synthesizing jet-flow excitor 3 cavitys.Second stage (jet is discharged the stage): high-speed jet is from jet exit 36 ejections.Phase III (air-breathing recovery phase): electromagnetically operated valve 13 is opened, in the cavity of the high pressure low temperature gas inject synthesizing jet-flow excitor 3 in air collector 12, make rapid denseization of gas in synthesizing jet-flow excitor 3 cavitys, greatly improve the backfill speed of cavity, ready for entering the next work period rapidly; After air-breathing recovery completes, electromagnetically operated valve 13 cuts out, and synthesizing jet-flow excitor 3 is again lighted a fire and entered the next work period.
The above is only the preferred embodiment of the present invention, and protection scope of the present invention is also not only confined to above-described embodiment, and all technical schemes belonging under thinking of the present invention all belong to protection scope of the present invention.It should be pointed out that for those skilled in the art, some improvements and modifications without departing from the principles of the present invention, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (8)
1. the zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy, it is characterized in that: comprise gas source unit (1), power subsystem (2) and synthesizing jet-flow excitor (3), described gas source unit (1) comprises cavity (11), air collector (12) and electromagnetically operated valve (13) windward, between described cavity windward (11), air collector (12) and electromagnetically operated valve (13), by steam line (14), be communicated with, described cavity windward (11) is located at the head of described high energy synthesizing jet-flow device place aircraft; Described synthesizing jet-flow excitor (3) comprises exciter housing (31), in described exciter housing (31), be provided with and be the radial main discharge electrode (32) of arranging successively, igniting anodal (33) and igniting negative pole (34), described exciter housing (31) is provided with air source inlet (35) and at least one jet exit (36), described main discharge electrode (32), igniting anodal (33) and the negative pole (34) of lighting a fire are connected with power subsystem (2) respectively, between described air source inlet (35) and electromagnetically operated valve (13), by steam line (14), are communicated with; Described power subsystem (2) comprises thermo-electric conversion module (21), input circuit (22), high voltage source (23), hvdc circuit (24) and high-voltage pulse circuit (25), the output of described thermo-electric conversion module (21) is connected with high voltage source (23) by input circuit (22), described high voltage source (23) is connected with main discharge electrode (32) by hvdc circuit (24), and described high voltage source (23) is connected with igniting anodal (33), igniting negative pole (34) respectively by high-voltage pulse circuit (25).
2. the zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy according to claim 1, is characterized in that: the steam line (14) between described cavity windward (11), air collector (12) is provided with unidirectional valve (15).
3. the zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy according to claim 2, it is characterized in that: the angle between described main discharge electrode (32), igniting anodal (33) is 90 degree, angle between described igniting anodal (33) and igniting negative pole (34) is 90 degree, and the spacing between igniting anodal (33) and igniting negative pole (34) is less than the spacing between main discharge electrode (32), igniting anodal (33).
4. the zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy according to claim 3, it is characterized in that: described thermo-electric conversion module (21) comprises a plurality of thermoelectric power generations unit, described thermoelectric power generation unit comprises P type thermo-electric converting material unit (27), N-type thermo-electric converting material unit (28) and conducting strip (29), described P type thermo-electric converting material unit (27), N-type thermo-electric converting material unit (28) all thermal source (26) of relatively described high energy synthesizing jet-flow device place aircraft is arranged vertically, between described P type thermo-electric converting material unit (27) and N-type thermo-electric converting material unit (28), by conducting strip (29), be connected, and by conducting strip (29), connect between described a plurality of thermoelectric power generations unit, or in parallel, or the mode that series and parallel connections mixes connects and constitutes thermo-electric conversion module (21).
5. according to the zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy described in any one in claim 1～4, it is characterized in that: the lip of described cavity windward (11) is pointed or circular.
6. the zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy according to claim 5, is characterized in that: the tubular structure of described exciter housing (31) for adopting glass ceramics or boron nitride ceramics to make.
7. the zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy according to claim 6, it is characterized in that: described main discharge electrode (32), igniting anodal (33) and igniting negative pole (34) are for adopting tungsten or tungsten alloy to make the cylindrical structural obtaining, and the end of described main discharge electrode (32), igniting anodal (33) and igniting negative pole (34) is wedge shape.
8. the zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy according to claim 7, is characterized in that: being shaped as slit shape or straight-through tubular or shrinking tubular or expand tubular or Rafael nozzle shape of described jet exit (36).
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| CN108543486A (en) * | 2018-03-12 | 2018-09-18 | 中国人民解放军国防科技大学 | Supersonic mixing layer control method |
| CN108860663A (en) * | 2018-07-24 | 2018-11-23 | 中国人民解放军国防科技大学 | Frequency-controllable self-maintaining high-speed jet flow exciter |
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| CN105514792A (en) * | 2015-11-25 | 2016-04-20 | 南京航空航天大学 | High-energy jet-flow exciter |
| CN105514792B (en) * | 2015-11-25 | 2018-11-09 | 南京航空航天大学 | A kind of high energy jet stream exciter |
| CN108543486A (en) * | 2018-03-12 | 2018-09-18 | 中国人民解放军国防科技大学 | Supersonic mixing layer control method |
| CN108543486B (en) * | 2018-03-12 | 2020-06-02 | 中国人民解放军国防科技大学 | Supersonic mixing layer control method |
| CN108860663A (en) * | 2018-07-24 | 2018-11-23 | 中国人民解放军国防科技大学 | Frequency-controllable self-maintaining high-speed jet flow exciter |
| CN114136583A (en) * | 2021-11-29 | 2022-03-04 | 中国人民解放军国防科技大学 | Zero-energy-consumption oscillating jet actuator for high-speed flow field control |
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