CN105422401B - A kind of liquid-jet hammer device based on plasma flow control - Google Patents
A kind of liquid-jet hammer device based on plasma flow control Download PDFInfo
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- CN105422401B CN105422401B CN201510897112.6A CN201510897112A CN105422401B CN 105422401 B CN105422401 B CN 105422401B CN 201510897112 A CN201510897112 A CN 201510897112A CN 105422401 B CN105422401 B CN 105422401B
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- jet
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Abstract
The invention discloses a kind of liquid-jet hammer device based on plasma flow control, including Thrust-vectoring Nozzle and Plasma Actuator, described Thrust-vectoring Nozzle includes air intake duct, flow transition section and expansion segment, and the Thrust-vectoring Nozzle produces power stream, there is provided thrust；Described Plasma Actuator is controlled to power stream.The present invention is without external gas source and complicated airflow line, and the response speed of Plasma Actuator is faster.
Description
Technical field
The invention belongs to aircraft engine thruster vector control field, and in particular to one kind is based on plasma flow control
The liquid-jet hammer device of system.
Background technology
In the design of traditional aircraft power plant, it is believed that engine can only provide thrust forward, and aircraft is turned
It is curved, climb, dive and during the gesture stability such as roll, can only rely on pneumatic rudder face deflection produce asymmetric aerodynamic torque come it is real
It is existing.The appearance of Thrust Vectoring Technology, changes this phenomenon, and thrust vectoring device has the driftage, pitching, roll of operating aircraft
Etc. ability.Agility and post stall maneuver flight are the developing direction of following fighter plane, and thrust vectoring device can improve aircraft
Mobility and agility, or even with the maneuverability under fault speed state.Under low speed High Angle of Attack, the pneumatic rudder face of aircraft
Efficiency it is very low or be exactly to fail at all, thrust vectoring device is hardly influenceed by this, can be used for replacing part
The effect of air-operated control rudder face.At present, thrust vectoring device generally use is mechanical, including controllable register, deflection adjustment sheet and
Jet pipe integrally deflects.In actual applications, mechanical thrust vectoring device due to parts it is more, generally with hundreds and thousands of
Individual part, make aircaft configuration more complicated, add the weight and cost of aircraft, at the same it is also very unfavorable to safeguarding.
A series of problems faced for mechanical thrust vectoring device, it is proposed that the design of fluid-type thrust vectoring device
Thinking.Fluid-type thrust vectoring device is to be flowed away to influence main flow state by means of two bursts of injections of introducing, it is changed direction, enters
And realize thruster vector control.Fluid-type thrust vectoring device control program is roughly divided into several fundamental types：Shock wave vector control
Preparation method, venturi deflection method, reverse flow thruster vector control and concurrent thruster vector control, these schemes are still among research.
Fluid-type thrust vectoring device is without complicated activation part, and lighter relative to mechanical weight, reliability will also obtain very
Big raising.Meanwhile fluid-type thrust vectoring device also has some shortcomings：Need the gas flow tube of external gas source and arrangement complexity
Road.
The content of the invention
Above-mentioned the deficiencies in the prior art are directed to, it is an object of the invention to provide one kind to be based on plasma flow control
Liquid-jet hammer device, with solve in the prior art mechanical thrust vectoring device parts it is more, add aircraft
Weight and cost, while to safeguard it is also very unfavorable the problem of；And fluid-type thrust vectoring device needs external gas source and cloth
The problems such as putting the airflow line of complexity.
To reach above-mentioned purpose, a kind of liquid-jet hammer device based on plasma flow control of the invention, bag
Thrust-vectoring Nozzle and Plasma Actuator are included, described Thrust-vectoring Nozzle includes air intake duct, flow transition section and expansion
Section, and the Thrust-vectoring Nozzle produce power stream, there is provided thrust；Described Plasma Actuator is controlled to power stream.
Preferably, the upper and lower surface of entrance inwall of the expansion segment of the Thrust-vectoring Nozzle is respectively arranged plasma and swashed
Encourage device.
Preferably, described Plasma Actuator is dielectric barrier discharge plasma driver.
Preferably, described dielectric barrier discharge plasma driver includes being connected to the two of high-voltage ac power both ends
Individual electrode, two electrodes are respectively adhered on the upper and lower surface of entrance inwall of the expansion segment of Thrust-vectoring Nozzle, electrode holding pair
Claim, two electrodes are covered by insulating materials, and air, dielectric barrier discharge plasma are full of between upper and lower both sides insulating materials
Driver can form space plasma electric discharge in the porch of the expansion segment of Thrust-vectoring Nozzle, be cut in whole expansion segment entrance
Face generates high speed plasma jet.
Preferably, the electrode of described Plasma Actuator is copper electrode, two electrode sizes one of upper and lower surface
Cause.
Plasma Actuator is arranged in the porch of the expansion segment of Thrust-vectoring Nozzle by the present invention, utilizes plasma
Driver forms space plasma electric discharge in the porch of the expansion segment of Thrust-vectoring Nozzle, is cut in the entrance of whole expansion segment
Face generates high speed plasma jet, and certain impact deflection effect is played in high-speed jet to the main flow in Thrust-vectoring Nozzle,
The supplementary function of plasma jet causes the inlet side surface of expansion segment to produce higher-pressure region, so can also spray thrust vectoring
Main flow both sides in pipe produce pressure differential, finally main flow are deflected.
Beneficial effects of the present invention：
Present invention effect is rapid, excitation frequency band is wide, without movable part, it is simple in construction, do not need external gas source and arrangement
Complicated airflow line, solves the problems such as other fluid-type thrust vectoring devices need external gas source, due to plasma
Discharge frequency is up to MHz, therefore response frequency is also much higher than conventional control mode；Meanwhile better simply behaviour can be utilized
Make mode, change the direction of nozzle exit air-flow, realize the vector quantization of motor power.
Brief description of the drawings
Fig. 1 is the side schematic perspective view of apparatus of the present invention；
Fig. 2 is the overall structure schematic top plan view of the present invention；
Fig. 3 is Fig. 2 A-A diagrammatic cross-sections；
Fig. 4 is the structural representation for the dielectric barrier discharge plasma driver that the present invention uses；
Schematic diagram when Fig. 5 does not open Plasma Actuator for the present invention；
Fig. 6 connects AC power high-pressure side lower surface electrode for upper surface electrode of the present invention and connects AC power low-pressure end, opens
Schematic diagram during Plasma Actuator；
Fig. 7 connects AC power low-pressure end lower surface electrode for upper surface electrode of the present invention and connects AC power high-pressure side, opens
Schematic diagram during Plasma Actuator；
Brief description of the drawings：1. air intake duct, 2. flow transition sections, 3. expansion segments, 4. Plasma Actuators, 5. copper electrodes, 6.
Insulating materials, 7. high-voltage ac powers.
Embodiment
For the ease of the understanding of those skilled in the art, the present invention is made further with reference to embodiment and accompanying drawing
Bright, the content that embodiment refers to not is limitation of the invention.
Shown in reference picture 1, Fig. 2 and Fig. 3, a kind of liquid-jet hammer dress based on plasma flow control of the invention
Put, including Thrust-vectoring Nozzle and Plasma Actuator 4, described Thrust-vectoring Nozzle include air intake duct 1, flow transition section
2 and expansion segment 3, three is sequentially set；Wherein, divide on the upper and lower surface of entrance inwall of the expansion segment 3 of the Thrust-vectoring Nozzle
Bu Zhi not Plasma Actuator 4.
Shown in reference picture 3, Fig. 4, the Plasma Actuator 4 is dielectric barrier discharge plasma driver, including
Two electrodes at the both ends of high-voltage ac power 7 are connected to, two electrodes are respectively adhered on entering for the expansion segment 3 of Thrust-vectoring Nozzle
The intraoral upper and lower surface of wall, electrode are copper electrode 5, and keep symmetrical, and two electrodes are covered by insulating materials 6, upper and lower
Air is full of between the insulating materials of both sides.
When aircraft carries out elevating movement, Plasma Actuator 4, as shown in Figure 6 and Figure 7, plasma excitation are opened
Two electrodes of the upper and lower surface of device 4 are connected with high-voltage ac power 7, can be in the expansion of Thrust-vectoring Nozzle
The porch of section 3 forms space plasma electric discharge, and high speed plasma jet is generated in the entrance section of whole expansion segment 3,
Under the impact of plasma jet, the direction of main flow can occur necessarily to deflect inside Thrust-vectoring Nozzle, so as to thrust vectoring
The air-flow of outside nozzle deflects so that the thrust vectoring of engine；Aircraft produces pitching moment, thus to aircraft
Pitch attitude controlled.When closing Plasma Actuator 4, flow field state is as shown in Figure 5.
By the above situation it can be seen that the mode of using plasma of the present invention flowing control controls main flow to deflect, nothing
Any external gas source and the airflow line of arrangement complexity are needed, need to only be arranged in the porch of the expansion segment 3 of Thrust-vectoring Nozzle etc.
Gas ions driver.Plasma Actuator 4 is arranged in the porch of the expansion segment 3 of Thrust-vectoring Nozzle, utilized
Gas ions driver 4 forms space plasma electric discharge in the porch of the expansion segment 3 of Thrust-vectoring Nozzle, in whole expansion segment
Certain impact is played in 3 entrance section generation high speed plasma jet, high-speed jet to the main flow in Thrust-vectoring Nozzle
Deflection acts on, and the supplementary function of plasma jet causes the inlet side surface of expansion segment to produce higher-pressure region, so can also make
Main flow both sides in Thrust-vectoring Nozzle produce pressure differential, finally main flow are deflected.
Concrete application approach of the present invention is a lot, and described above is only the preferred embodiment of the present invention, it is noted that for
For those skilled in the art, under the premise without departing from the principles of the invention, some improvement can also be made, this
A little improve also should be regarded as protection scope of the present invention.
Claims (2)
1. a kind of liquid-jet hammer device based on plasma flow control, it is characterised in that including Thrust-vectoring Nozzle
And Plasma Actuator, described Thrust-vectoring Nozzle include air intake duct, flow transition section and expansion segment, and the thrust vectoring
Jet pipe produces power stream, there is provided thrust；Described Plasma Actuator is controlled to power stream；
The upper and lower surface of entrance inwall of the expansion segment of the Thrust-vectoring Nozzle is respectively arranged Plasma Actuator；
Described Plasma Actuator is dielectric barrier discharge plasma driver；
Two electrodes of the described dielectric barrier discharge plasma driver including being connected to high-voltage ac power both ends, two
Electrode is respectively adhered on the upper and lower surface of entrance inwall of the expansion segment of Thrust-vectoring Nozzle, and electrode keeps symmetrical, and two electrodes are equal
Covered by insulating materials, air is full of between upper and lower both sides insulating materials, dielectric barrier discharge plasma driver can push away
The porch of the expansion segment of force vector jet pipe forms space plasma electric discharge, in the generation of whole expansion segment entrance section at a high speed etc.
Gas ions jet.
2. the liquid-jet hammer device according to claim 1 based on plasma flow control, it is characterised in that institute
The electrode for the Plasma Actuator stated is copper electrode, and two electrode sizes of upper and lower surface are consistent.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510897112.6A CN105422401B (en) | 2015-12-08 | 2015-12-08 | A kind of liquid-jet hammer device based on plasma flow control |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510897112.6A CN105422401B (en) | 2015-12-08 | 2015-12-08 | A kind of liquid-jet hammer device based on plasma flow control |
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| Publication Number | Publication Date |
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| CN105422401A CN105422401A (en) | 2016-03-23 |
| CN105422401B true CN105422401B (en) | 2018-03-13 |
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| CN201510897112.6A Expired - Fee Related CN105422401B (en) | 2015-12-08 | 2015-12-08 | A kind of liquid-jet hammer device based on plasma flow control |
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Families Citing this family (6)
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| CN107587989B (en) * | 2017-10-17 | 2019-01-25 | 北京理工大学 | A kind of double state solid pulsed plasma thrusters of high efficiency |
| CN109357884B (en) * | 2018-10-23 | 2020-06-05 | 南京理工大学 | Thrust measuring device for head air inlet solid fuel ramjet |
| CN111158387B (en) * | 2020-01-17 | 2021-05-25 | 南京航空航天大学 | Aircraft three-axis attitude control system and method based on active flow control |
| CN112555114B (en) * | 2020-12-01 | 2022-06-17 | 中国人民解放军战略支援部队航天工程大学 | Electromagnetic combined vector acceleration spray pipe for laser ablation propulsion |
| CN113784492A (en) * | 2021-09-14 | 2021-12-10 | 大连理工大学 | Method for generating large-volume uniform plasma in air flow or nitrogen flow |
| CN114320670A (en) * | 2021-12-22 | 2022-04-12 | 杭州热力科技有限公司 | Engine spray pipe flow control device and method using plasma |
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| JPS61164083A (en) * | 1985-01-14 | 1986-07-24 | Mitsubishi Electric Corp | Mpd propulsion device |
| RU2323137C1 (en) * | 2006-08-08 | 2008-04-27 | Сергей Николаевич Чувашев | Method and device for control of flow in nozzle of flying vehicle jet engine |
| CN102777342A (en) * | 2012-08-03 | 2012-11-14 | 北京卫星环境工程研究所 | Vector magnetic nozzle used for electric propulsion |
| CN103661929A (en) * | 2013-12-19 | 2014-03-26 | 南京航空航天大学 | Plasma unmanned aerial vehicle |
| CN205423089U (en) * | 2015-12-08 | 2016-08-03 | 南京航空航天大学 | Efflux thrust vector device based on plasma flow moves control |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2005003557A1 (en) * | 2003-06-25 | 2005-01-13 | Design Net Engineering, Llc | Laser propulsion thruster |
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2015
- 2015-12-08 CN CN201510897112.6A patent/CN105422401B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61164083A (en) * | 1985-01-14 | 1986-07-24 | Mitsubishi Electric Corp | Mpd propulsion device |
| RU2323137C1 (en) * | 2006-08-08 | 2008-04-27 | Сергей Николаевич Чувашев | Method and device for control of flow in nozzle of flying vehicle jet engine |
| CN102777342A (en) * | 2012-08-03 | 2012-11-14 | 北京卫星环境工程研究所 | Vector magnetic nozzle used for electric propulsion |
| CN103661929A (en) * | 2013-12-19 | 2014-03-26 | 南京航空航天大学 | Plasma unmanned aerial vehicle |
| CN205423089U (en) * | 2015-12-08 | 2016-08-03 | 南京航空航天大学 | Efflux thrust vector device based on plasma flow moves control |
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| CN105422401A (en) | 2016-03-23 |
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