CN102943751B - A fast-response direct force generating device - Google Patents
A fast-response direct force generating device Download PDFInfo
- Publication number
- CN102943751B CN102943751B CN201210491228.6A CN201210491228A CN102943751B CN 102943751 B CN102943751 B CN 102943751B CN 201210491228 A CN201210491228 A CN 201210491228A CN 102943751 B CN102943751 B CN 102943751B
- Authority
- CN
- China
- Prior art keywords
- jet
- igniting
- actuator body
- direct force
- main discharge
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000015572 biosynthetic process Effects 0.000 claims description 15
- 238000003786 synthesis reaction Methods 0.000 claims description 13
- 239000003990 capacitor Substances 0.000 abstract description 2
- 238000007599 discharging Methods 0.000 abstract description 2
- 230000002194 synthesizing effect Effects 0.000 description 10
- 230000015556 catabolic process Effects 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 238000006243 chemical reaction Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 4
- 230000007812 deficiency Effects 0.000 description 2
- 208000002925 dental caries Diseases 0.000 description 2
- 238000010891 electric arc Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 229910052582 BN Inorganic materials 0.000 description 1
- PZNSFCLAULLKQX-UHFFFAOYSA-N Boron nitride Chemical compound N#B PZNSFCLAULLKQX-UHFFFAOYSA-N 0.000 description 1
- 229910001080 W alloy Inorganic materials 0.000 description 1
- 238000002679 ablation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005538 encapsulation Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000002241 glass-ceramic Substances 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000001465 metallisation Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000005619 thermoelectricity Effects 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 description 1
- 229910052721 tungsten Inorganic materials 0.000 description 1
- 239000010937 tungsten Substances 0.000 description 1
- 238000002604 ultrasonography Methods 0.000 description 1
Images
Landscapes
- Plasma Technology (AREA)
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 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 inside and outside High Speed Flow Field of aircraft fast-response direct force control and 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 high-speed aircraft speed of response, improving guidance precision, increase permissible load factor and maneuverability.The relatively aerodynamic force control mode based on airvane, the direct force control based on lateral jet has advantages of that time lag is little, fast response time, high altitude environment control efficiency are high.
At present, based on the Reaction control system of lateral jet, mainly by small-sized thruster or high-pressure gas/flow container device, spray high speed gas/liquid jet generation side spray power.Also Shortcomings of these two kinds of direct force producing methods, small-sized thruster is mainly selected gas generator, mini engine or directly by master motor lateral drainage.The shortcoming of this implementation is, 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 volume of its gas-liquid fuels is bigger than normal, is inconvenient to carry, and fuel consumption during thruster work can cause the drift of aircraft barycenter.
For overcoming the deficiency of current direct force producing method, the direct force based on Novel spark discharge plasma synthesizing jet-flow excitor produces technology to be stepped up research and is advancing.
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 is lower to the transformation efficiency of gas heat energy in actuator cavity and energy of the impinging jet, therefore for forming 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 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 is also 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, the defect and the deficiency that for known technology, exist, a kind of fast-response direct force generation device is provided, while using this device, can to parameters such as its operating time, frequency of okperation, jet intensity, regulate and control according to actual needs, to meet different demands for control.
Technical solution of the present invention is, referring to accompanying drawing 1～2.As shown in accompanying drawing 1～2, above-mentioned provided a kind of fast-response direct force generation device, 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 the tubular actuator body 24 of its one end with cover plate 26, and be radially radial interval and be plugged on that main discharge electrode 21 on this actuator body 24, igniting are anodal 22, igniting negative pole 23.On described cover plate 26, have jet exit hole 25.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 described in one termination of above-mentioned charge and discharge capacitance 13 between hvdc circuit 12 and described main discharge electrode 21, the other end ground connection.
When the fast-response direct force generation device of the present invention forming is thus used, above-mentioned high-voltage pulse circuit 11 is exported voltage up to tens of kilovolts for the puncturing of air, and sets up conductive channel and the electric arc that ignites.12 of hvdc circuits are that charge and discharge capacitance 13 uninterruptedly charges, for producing sparkover and injecting power after air breakdown.Utilize sparkover to produce energetic plasma synthesizing jet-flow, and utilize the reaction force of the energetic plasma synthesizing jet-flow of sparkover generation to generate fast-response direct force.Come therefrom, can make sparkover plasma synthesis jet-flow excitor 2 realize 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 completely, have advantages of machinery-free movable part, without high-pressure gas tank arrangement, respond rapid, simple in structure, be easy to control, a kind of rapid, reusable, big or small adjustable new direct force producing method of thrust that responds was both provided, simultaneously also for 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 voltage and current size adjustable DC power output, meets the adjustment of the different discharge voltages of main discharge, and realizes mating of discharge capacity 13 discharge frequencies and high-voltage pulse electric source frequency.Hvdc circuit 12 charges for charge and discharge capacitance 13, set up potential difference, but this potential difference is also not enough to realize interelectrode air breakdown between main discharge electrode 21 and igniting anodal 22.High-voltage pulse circuit 11 provides frequency adjustable high-voltage pulse, for the foundation of electronic current passage the electric arc that ignites.Under high-voltage pulse circuit 11 excitations, between the interior igniting of actuator body 24 anodal 22 and igniting negative pole 23, can form air breakdown, produce electronic current passage.Now between main discharge electrode 21, igniting anodal 22 and igniting negative pole 23, can there is air breakdown, set up sparkover, complete power and inject.Sparkover meeting produces gas-heated effect fast to the air in actuator body 24, and cause the interior temperature and pressure of actuator body 24 sharply to raise, the interior gas of the actuator body 24 institute jet exit hole of opening 25 ejection at a high speed from its cover plate 26 of pressurizeing heats up, form energetic plasma synthesizing jet-flow, produce reaction thrust.After energetic plasma synthesizing jet-flow has sprayed, due to the decline of actuator body 24 interior temperature and pressures, and under the ejector action of high speed energetic plasma synthesizing jet-flow, the interior meeting of actuator body 24 presents parital vacuum, now outside cold air backfill actuator body 24 cavitys, prepare formation and the generation of impulse force next time of energetic plasma synthesizing jet-flow next time.
Beneficial effect of the present invention is: compared with traditional direct force producing method, this device can regulate 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 feature, is a kind of fast-response direct force generation device based on 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 high speed internal and external flow field active Flow Control actuator and use, greatly expanded the application area of synthesizing jet-flow technology simultaneously.
Accompanying drawing explanation
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---igniting negative pole,
24---actuator body,
25---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 as shown in Figure 2, includes a tubular actuator body 24, 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, and to reduce the difficulty of processing of actuator, the diameter of cover plate 26 is mated with the barrel dliameter size of actuator body 24, thick 3mm.On cover plate 26, the institute jet exit hole 25 of opening is rounded, 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.Between cover plate 26 and actuator body 24, adopt the mode coaxial line stickup of elevated-temperature seal glue to be connected.Radially be radial interval and be plugged on main discharge electrode 21, igniting anodal 22 and the igniting negative pole 23 on actuator body 24, 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 igniting anodal 22 is that 90 °, igniting anodal 22 are also 90 ° with the interval radian of lighting a fire between negative pole 23.The spacing of lighting a fire between positive pole 22 and igniting negative pole 23 is less than the spacing between main discharge electrode 21 and igniting anodal 22, with guarantee point thermoelectricity subflow Path Setup, is lighting a fire between positive pole 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 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 line between a termination hvdc circuit 12 and the main discharge electrode 21 of charge and discharge capacitance 13, 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. a 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 its one end cover plate (26), radially be radial interval and be plugged on the main discharge electrode (21) on this actuator body (24), igniting anodal (22), igniting negative pole (23), and the spacing between igniting anodal (22) and igniting negative pole (23) is less than the spacing between main discharge electrode (21) and igniting anodal (22), on the cover plate (26) of described actuator body (24) one end, have jet exit hole (25), and described main discharge electrode (21) is connected with above-mentioned hvdc circuit (12), described igniting anodal (22), high-voltage pulse circuit (11) is connected successively with igniting negative pole (23), one end of above-mentioned charge and discharge capacitance (13) is connected to the line between described hvdc circuit (12) and 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210491228.6A CN102943751B (en) | 2012-11-27 | 2012-11-27 | A fast-response direct force generating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210491228.6A CN102943751B (en) | 2012-11-27 | 2012-11-27 | A fast-response direct force generating device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102943751A CN102943751A (en) | 2013-02-27 |
| CN102943751B true CN102943751B (en) | 2014-05-07 |
Family
ID=47726722
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210491228.6A Active CN102943751B (en) | 2012-11-27 | 2012-11-27 | A fast-response direct force generating device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102943751B (en) |
Families Citing this family (14)
| 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 |
| 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 |
| 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 |
| CN108684130B (en) * | 2018-03-23 | 2020-09-08 | 厦门大学 | Program-controlled array type plasma jet exciter system |
| CN108541125B (en) * | 2018-04-18 | 2019-06-28 | 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 synthetic jet actuator |
| CN111577561B (en) * | 2020-04-24 | 2022-04-19 | 南京理工大学 | Device for improving jet intensity of annular electrode exciter and working method thereof |
| CN112179215B (en) * | 2020-09-21 | 2023-03-21 | 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 |
| 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 |
| CN119190354A (en) * | 2024-11-01 | 2024-12-27 | 中国人民解放军国防科技大学 | A multi-medium jet actuator for a cross-medium aircraft entering and exiting an ice layer |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101790276A (en) * | 2009-07-16 | 2010-07-28 | 武汉天和技术股份有限公司 | Plasma generating device and method thereof |
| CN102014567A (en) * | 2010-10-11 | 2011-04-13 | 中国人民解放军国防科学技术大学 | Dynamical pressure type high-energy synthetic jet actuator |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7703479B2 (en) * | 2005-10-17 | 2010-04-27 | The University Of Kentucky Research Foundation | Plasma actuator |
| KR101026459B1 (en) * | 2008-11-26 | 2011-04-01 | (주)트리플코어스코리아 | Atmospheric plasma ignition apparatus and atmospheric plasma ignition method using the same |
-
2012
- 2012-11-27 CN CN201210491228.6A patent/CN102943751B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101790276A (en) * | 2009-07-16 | 2010-07-28 | 武汉天和技术股份有限公司 | Plasma generating device and method thereof |
| CN102014567A (en) * | 2010-10-11 | 2011-04-13 | 中国人民解放军国防科学技术大学 | Dynamical pressure type high-energy synthetic jet actuator |
Non-Patent Citations (2)
| Title |
|---|
| 王林等.电火花式等离子体合成射流激励器流场特性数值模拟研究.《中国力学大会2011暨钱学森诞辰100周年纪念大会论文集》.2012,全文. |
| 电火花式等离子体合成射流激励器流场特性数值模拟研究;王林等;《中国力学大会2011暨钱学森诞辰100周年纪念大会论文集》;20121116;全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102943751A (en) | 2013-02-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102943751B (en) | A fast-response direct force generating device | |
| CN107091210B (en) | A kind of pulsed plasma thruster based on capillary discharging | |
| CN106640568B (en) | A kind of dipolar solid ablative-type protective coating plasma accelerator | |
| CN107061210B (en) | A kind of pulsed plasma thruster accelerated based on electrothermal and electromagnetic mixing | |
| CN103912466B (en) | A kind of electrical fluid power propeller | |
| CN101975122B (en) | Stabilized knocking engine with magnetic fluid energy bypath system | |
| CN105201657B (en) | A kind of low temperature plasma priming supply and ignition system | |
| CN104265506B (en) | Pulse-knocking engine | |
| CN106907272A (en) | Structure changes Rocket based combined cycle engine | |
| RU164690U1 (en) | PENDULUM-SLIDER DEVICE FOR REACTIVE DETONATION BURNING | |
| CN109630312B (en) | High-frequency response vectoring nozzle | |
| CN110792531B (en) | Intelligent atomizing nozzle based on high-voltage discharge and spraying control system | |
| CN210106081U (en) | Solid ablation type magnetic plasma thruster | |
| CN110469425A (en) | A kind of adjustable thrust formula multistage pulses solid propellant rocket | |
| CN104202898B (en) | The zero energy consumption zero mass synthesizing jet-flow device utilizing based on hypersonic stream energy | |
| CN104833475A (en) | Turbine engine jet experiment simulation device | |
| CN108811289A (en) | A kind of dynamic pressure type plasma synthesis fluidic generator | |
| RU2649494C1 (en) | Pulsed detonation rocket engine | |
| CN102705108B (en) | Periodic alternating current drive low-temperature plasma ignition method and system | |
| CN110131120A (en) | Solid ablation type magnetic plasma thruster | |
| CN111305972A (en) | A pulse detonation combustion chamber and an air turbo rocket engine based on pulse detonation | |
| CN118343313A (en) | A variable cathode arc enhanced space composite thruster | |
| CN110486244B (en) | An electromagnetic induction plasma accelerator | |
| CN118188374A (en) | Plasma jet ignition device and method using energetic doping modified working fluid | |
| CN104314692B (en) | A Microwave Surface Wave Ignition and Combustion Supporting Device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |