CN102943751A - Quick-response direct force generating device - Google Patents
Quick-response direct force generating device Download PDFInfo
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- CN102943751A CN102943751A CN2012104912286A CN201210491228A CN102943751A CN 102943751 A CN102943751 A CN 102943751A CN 2012104912286 A CN2012104912286 A CN 2012104912286A CN 201210491228 A CN201210491228 A CN 201210491228A CN 102943751 A CN102943751 A CN 102943751A
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Abstract
The invention discloses a quick-response direct force generating device. A power supply system (1) comprises a high-voltage pulse circuit (11), a high-voltage direct-current circuit (12) and a charging and discharging capacitor (13). A spark discharge plasma synthetic jet actuator (2) of the device comprises an actuator body (24) provided with a cover plate (26), and a main discharge electrode (21), an ignition positive electrode (22) and an ignition negative electrode (23) which are inserted in the actuator body (24) at intervals. A jet outlet (25) is opened in the cover plate (26). The main discharge electrode (21) is connected with the high-voltage direct-current circuit (12), and the ignition positive electrode (22) and the ignition negative electrode (23) are connected in parallel with the high-voltage pulse circuit (11). According to the device, the pulse jet frequency and the jet energy can be adjusted according to needs, a novel generating mode is provided for controlling quick-response direct force of a high-speed air vehicle, and the device can be used an actuator in active flow control in high-speed internal and external flow fields.
Description
Technical field
The invention belongs to the aerospace flight vehicle control field, be specifically related to a kind of fast-response direct force generation device, be applicable to the ACTIVE CONTROL of the control of aircraft fast-response direct force and the inside and outside High Speed Flow Field of aircraft.
Background technique
Along with developing rapidly of ultrasound velocity/hypersonic aircraft technology, the effective means that Direct Force Control Technology is just becoming and improving the high-speed aircraft speed of response, improving guidance precision, increase permissible load factor and maneuverability.Relatively based on the aerodynamic force control mode of airvane, based on the direct force control of lateral jet have that time lag is little, fast response time, advantage that the high altitude environment control efficiency is high.
At present, based on the Reaction control system of lateral jet, mainly spray high speed gas/liquid jet generation side spray power by small-sized thruster or high-pressure gas/flow container device.These two kinds of direct force producing methods are Shortcomings also, and small-sized thruster is mainly selected gas generator, mini engine or directly by the master motor lateral drainage.The shortcoming of this implementation is that the operating range of direct force is subject to the restriction of thruster fuel consumption, and the non-adjustable and thruster fuel consumption of thrust size can not continue to use after to the greatest extent.The high-pressure gas tank arrangement then volume of its gas-liquid fuels is bigger than normal, is inconvenient to carry, and the fuel consumption during thruster work can cause the drift of aircraft barycenter.
For overcoming the deficiency of present direct force producing method, stepping up research and advancing based on the direct force generating technique of Novel spark discharge plasma synthesizing jet-flow excitor.
And traditional sparkover plasma synthesis jet-flow excitor is proposed at the beginning of 21 century by Experiment of Applied Physics chamber, Johns Hopkins University the earliest.Because the breakdown voltage of air is higher, and input electric energy transformation efficiency of gas heat energy and energy of the impinging jet in the actuator cavity is lower, therefore for forming the energetic plasma synthesizing jet-flow, need larger power supply input power or can only adopt less actuator cavity.For this reason, the researcher Cybyk of this university has adopted the three electrode chamber structures of adding grid in the actuator design, to reduce required power, but this mode has increased the complexity of cavity processing and encapsulation, and the input power circuit that it adopts also is not easy to realize the adjustable, controlled of actuator frequency of okperation and effluxvelocity.
Summary of the invention
Technical problem to be solved by this invention is, defective and deficiency for the known technology existence, a kind of fast-response direct force generation device is provided, when using this device, can regulate and control parameters such as its operating time, frequency of okperation, jet intensity according to actual needs, to satisfy different demands for control.
Technical solution of the present invention is, referring to accompanying drawing 1～2.Shown in accompanying drawing 1～2, the above-mentioned a kind of fast-response direct force generation device that provides is comprised of a power supply system 1 and a sparkover plasma synthesis jet-flow excitor 2.Described power supply system 1 includes high-voltage pulse circuit 11, hvdc circuit 12 and charge and discharge capacitance 13.Described sparkover plasma synthesis jet-flow excitor 2, as shown in Figure 2, include an one end with the tubular actuator body 24 of cover plate 26, and radially be radial interval and be plugged on anodal 22, the igniting negative pole 23 of main discharge electrode 21 on this actuator body 24, igniting.Have jet exit hole 25 on the described cover plate 26.And described main discharge electrode 21 is connected with above-mentioned hvdc circuit 12.Described igniting anodal 22 and the igniting negative pole 23 above-mentioned high-voltage pulse circuit 11 that is connected in parallel.Line between the described hvdc circuit 12 of one termination of above-mentioned charge and discharge capacitance 13 and the described main discharge electrode 21, the other end ground connection.
When the fast-response direct force generation device of the present invention that consists of thus used, the voltage of above-mentioned high-voltage pulse circuit 11 outputs up to tens of kilovolts was used for the puncture of air, sets up conductive channel and the electric arc that ignites.12 of hvdc circuits are that charge and discharge capacitance 13 uninterruptedly charges, to be used for producing sparkover and injecting power behind the air breakdown.Utilize sparkover to produce the energetic plasma synthesizing jet-flow, and utilize the reaction force of the energetic plasma synthesizing jet-flow of sparkover generation to generate the fast-response direct force.Come therefrom, can be so that sparkover plasma synthesis jet-flow excitor 2 be realized the conversion of input electric energy-gas heat energy-energy of the impinging jet, formation speed is up to the high energy jet of hundreds of metre per second (m/s)s.This device is comprised of electronic component fully, have the machinery-free movable part, without high-pressure gas tank arrangement, rapid, simple in structure, the advantage that is easy to control of response, a kind of rapid, reusable, big or small adjustable new direct force producing method of thrust that responds both was provided, simultaneously also for the high speed internal and external flow field provide a kind of control ability strong, be applicable to multi-operating mode, be easy to integrated active control device.
Working principle of the present invention is: hvdc circuit 12 provides the voltage and current size adjustable DC power output, satisfies the adjustment of the different discharge voltages of main discharge, and realizes the coupling of discharge capacity 13 discharge frequencies and high-voltage pulse electric source frequency.Hvdc circuit 12 is charge and discharge capacitance 13 chargings, set up potential difference at main discharge electrode 21 and anodal 22 of igniting, but this potential difference also is not enough to realize interelectrode air breakdown.High-voltage pulse circuit 11 provides frequency adjustable high-voltage pulse, is used for foundation and the electric arc that ignites of electronic current passage.Under high-voltage pulse circuit 11 excitations, can form air breakdown between the 24 interior igniting anodal 22 of actuator body and the igniting negative pole 23, produce the electronic current passage.Meeting generation air breakdown between main discharge electrode 21, igniting anodal 22 and the igniting negative pole 23 is set up sparkover at this moment, finishes power and injects.The sparkover meeting produces fast gas-heated effect to the air in the actuator body 24, and cause actuator body 24 interior temperature and pressures sharply to raise, actuator body 24 interior gases at a high speed ejection of the institute jet exit hole of opening 25 from its cover plate 26 of pressurization heats up, form the energetic plasma synthesizing jet-flow, produce reaction thrust.After the ejection of energetic plasma synthesizing jet-flow is finished, because the decline of actuator body 24 interior temperature and pressures, and under the ejector action of high speed energetic plasma synthesizing jet-flow, the 24 interior meetings of actuator body present parital vacuum, this moment, outside cold air backfill actuator body 24 cavitys were prepared next time formation and the next time generation of impulse force of energetic plasma synthesizing jet-flow.
Beneficial effect of the present invention is: compare with traditional direct force producing method, this device can be regulated and control direct force size, pulsing jet frequency, jet energy and operating time as required, and respond rapid, reusable, having simple in structure, easy-to-install characteristics, is a kind of fast-response direct force generation device based on the energetic plasma synthesizing jet-flow.Because the plasma synthesis effluxvelocity of its generation is higher, control ability is stronger, except can be used as the control of high-speed aircraft fast-response direct force, also can be used as simultaneously high speed internal and external flow field active Flow Control actuator and use, greatly expanded the application area of synthesizing jet-flow technology.
Description of drawings
Fig. 1 is the structural representation of a specific embodiment of a kind of fast-response direct force of the present invention generation device;
Fig. 2 is the structural representation of sparkover plasma synthesis jet-flow excitor.
Being denoted as in above Fig. 1～2:
1---power supply system,
11---high-voltage pulse circuit,
12---hvdc circuit,
13---charge and discharge capacitance,
2---sparkover plasma synthesis jet-flow excitor,
21---main discharge electrode,
22---igniting is anodal,
23---the igniting negative pole,
24---the actuator body,
25---the jet exit hole,
26---cover plate.
Embodiment
Referring to accompanying drawing 1～2, the embodiment of a kind of fast-response direct force of the present invention generation device is comprised of power supply system 1 and sparkover plasma synthesis jet-flow excitor 2.Wherein sparkover plasma synthesis jet-flow excitor 2 includes a tubular actuator body 24 as shown in Figure 2, and the diameter of section of this actuator body 24 is Φ 16mm, highly for 20mm.This actuator body 24 and cover plate 26 thereof select commercially available good insulation preformance, machinable glass ceramic or boron nitride ceramics to make, to reduce the difficulty of processing of actuator, the barrel dliameter size coupling of the diameter of cover plate 26 and actuator body 24, thick 3mm.The institute jet exit hole 25 of opening is rounded on the cover plate 26, and its diameter is Φ 2mm.Different angles of heel or pitching angle also can be selected in this jet exit hole 25, realize the jet ejection of different direction.Jet exit hole 25 also can be slit shape or straight-through tubular shape or shrink tubular shape or expansion circle or Rafael nozzle shape.Adopting the mode coaxial line of elevated-temperature seal glue to paste between cover plate 26 and the actuator body 24 is connected.Radially be radial interval and be plugged on the main discharge electrode 21 on the actuator body 24, light a fire positive pole 22 and igniting negative pole 23, all adopt the tungsten of arc ablation resistance or the alloy of tungsten to make, electrode head is wedge to reduce required breakdown voltage.Wherein the interval radian between main discharge electrode 21 and the igniting anodal 22 is that 90 °, igniting anodal 22 also are 90 ° with the interval radian of lighting a fire between the negative pole 23.Spacing between igniting anodal 22 and the igniting negative pole 23 is less than the spacing between main discharge electrode 21 and the igniting anodal 22, with guarantee point thermoelectricity subflow Path Setup between igniting anodal 22 and igniting negative pole 23.Bonding with high-temperature plastic between main discharge electrode 21, igniting anodal 22 and igniting negative pole 23 and the actuator body 24, just as insertion.Above-mentioned power supply system 1 includes high-voltage pulse circuit 11, hvdc circuit 12 and charge and discharge capacitance 13.Wherein hvdc circuit 12 is connected with the main discharge electrode 21 of sparkover plasma synthesis jet-flow excitor 2, and high-voltage pulse circuit 11 is connected in parallel with igniting anodal 22 and the igniting negative pole 23 of sparkover plasma synthesis jet-flow excitor 2.And a termination hvdc circuit 12 of charge and discharge capacitance 13 and the line between the main discharge electrode 21, the other end ground connection.Charge and discharge capacitance 13 is selected commercially available high pressure resistant metallization film capacitor, and capacitance size can be changed, so that adjust the size of different discharging energies in actuator body 24 cavitys with it.
Claims (2)
1. fast-response direct force generation device, it is characterized in that, it is comprised of a power supply system (1) and a sparkover plasma synthesis jet-flow excitor (2), described power supply system (1) includes high-voltage pulse circuit (11), hvdc circuit (12) and charge and discharge capacitance (13), described sparkover plasma synthesis jet-flow excitor (2), include the tubular actuator body (24) of an one end cover plate (26), radially be radial interval and be plugged on main discharge electrode (21) on this actuator body (24), igniting anodal (22), igniting negative pole (23), have jet exit hole (25) on the cover plate (26) of described actuator body (24) one ends, and described main discharge electrode (21) is connected with above-mentioned hvdc circuit (12), described igniting anodal (22) and igniting negative pole (23) parallel high voltage impulse circuit (11), one of above-mentioned charge and discharge capacitance (13) is terminated at the line between described hvdc circuit (12) and the described main discharge electrode (21), the other end ground connection.
2. a kind of fast-response direct force generation device according to claim 1 is characterized in that, described jet exit hole (25) is slit shape or straight-through tubular shape or collapsible tubular shape or expansible circle or Rafael nozzle shape.
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| CN201210491228.6A CN102943751B (en) | 2012-11-27 | 2012-11-27 | Quick-response direct force generating device |
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| CN201210491228.6A CN102943751B (en) | 2012-11-27 | 2012-11-27 | Quick-response direct force generating device |
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| CN102943751B CN102943751B (en) | 2014-05-07 |
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Cited By (13)
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| CN103912466A (en) * | 2014-04-10 | 2014-07-09 | 王文东 | Electric hydrodynamic force propeller |
| CN104202898A (en) * | 2014-07-09 | 2014-12-10 | 中国人民解放军国防科学技术大学 | Hypersonic speed flowing energy utilization based zero-energy-consumption zero-mass synthetic jet device |
| CN104571117A (en) * | 2013-10-29 | 2015-04-29 | 北京精密机电控制设备研究所 | Multichannel servo system controlled by direct force |
| CN107364583A (en) * | 2017-07-05 | 2017-11-21 | 方剑 | Miniature jet aircraft based on synthesizing jet-flow technology |
| CN108194461A (en) * | 2018-03-08 | 2018-06-22 | 南京理工大学 | It is a kind of to utilize piezoelectric vibration film and three electrode plasma combined type synthesizing jet-flow excitors |
| CN108541125A (en) * | 2018-04-18 | 2018-09-14 | 南京航空航天大学 | A kind of interior visible plasma synthesis jet-flow excitor |
| CN108684130A (en) * | 2018-03-23 | 2018-10-19 | 厦门大学 | A kind of program-controlled array plasma jet exciter system |
| CN108811292A (en) * | 2018-06-12 | 2018-11-13 | 厦门大学 | A kind of plasma synthesis jet stream combination of stimulation device |
| CN110498052A (en) * | 2019-08-01 | 2019-11-26 | 南京理工大学 | Thrust vector control system and method based on hybrid power synthesizing jet-flow excitor |
| CN111577561A (en) * | 2020-04-24 | 2020-08-25 | 南京理工大学 | Device for improving jet intensity of annular electrode exciter and working method thereof |
| CN112179215A (en) * | 2020-09-21 | 2021-01-05 | 西安理工大学 | Flight guidance weapon control device based on plasma jet technology |
| CN112432150A (en) * | 2020-12-18 | 2021-03-02 | 天津大学 | Adjustable ejector system applied to ethanolamine tower reboiler |
| CN114221569A (en) * | 2021-12-21 | 2022-03-22 | 中国人民解放军国防科技大学 | Parallel discharge device and method for plasma high-energy synthetic jet actuator |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104571117A (en) * | 2013-10-29 | 2015-04-29 | 北京精密机电控制设备研究所 | Multichannel servo system controlled by direct force |
| CN103912466A (en) * | 2014-04-10 | 2014-07-09 | 王文东 | Electric hydrodynamic force propeller |
| CN103912466B (en) * | 2014-04-10 | 2016-06-22 | 西安若水电气设备有限公司 | A kind of electrical fluid power propeller |
| CN104202898A (en) * | 2014-07-09 | 2014-12-10 | 中国人民解放军国防科学技术大学 | Hypersonic speed flowing energy utilization based zero-energy-consumption zero-mass synthetic jet device |
| CN104202898B (en) * | 2014-07-09 | 2016-05-11 | 中国人民解放军国防科学技术大学 | The zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy |
| CN107364583A (en) * | 2017-07-05 | 2017-11-21 | 方剑 | Miniature jet aircraft based on synthesizing jet-flow technology |
| CN108194461A (en) * | 2018-03-08 | 2018-06-22 | 南京理工大学 | It is a kind of to utilize piezoelectric vibration film and three electrode plasma combined type synthesizing jet-flow excitors |
| CN108684130A (en) * | 2018-03-23 | 2018-10-19 | 厦门大学 | A kind of program-controlled array plasma jet exciter system |
| CN108541125A (en) * | 2018-04-18 | 2018-09-14 | 南京航空航天大学 | A kind of interior visible plasma synthesis jet-flow excitor |
| CN108811292A (en) * | 2018-06-12 | 2018-11-13 | 厦门大学 | A kind of plasma synthesis jet stream combination of stimulation device |
| CN110498052A (en) * | 2019-08-01 | 2019-11-26 | 南京理工大学 | Thrust vector control system and method based on hybrid power synthesizing jet-flow excitor |
| CN111577561A (en) * | 2020-04-24 | 2020-08-25 | 南京理工大学 | Device for improving jet intensity of annular electrode exciter and working method thereof |
| CN112179215A (en) * | 2020-09-21 | 2021-01-05 | 西安理工大学 | Flight guidance weapon control device based on plasma jet technology |
| CN112432150A (en) * | 2020-12-18 | 2021-03-02 | 天津大学 | Adjustable ejector system applied to ethanolamine tower reboiler |
| CN114221569A (en) * | 2021-12-21 | 2022-03-22 | 中国人民解放军国防科技大学 | Parallel discharge device and method for plasma high-energy synthetic jet actuator |
| CN114221569B (en) * | 2021-12-21 | 2023-12-01 | 中国人民解放军国防科技大学 | Parallel discharge device and method for plasma high-energy synthetic jet exciter |
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