CN106892078A - A kind of plasma flow control device near space dirigible drag reduction - Google Patents
A kind of plasma flow control device near space dirigible drag reduction Download PDFInfo
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- CN106892078A CN106892078A CN201710077819.1A CN201710077819A CN106892078A CN 106892078 A CN106892078 A CN 106892078A CN 201710077819 A CN201710077819 A CN 201710077819A CN 106892078 A CN106892078 A CN 106892078A
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- drag reduction
- insulating barrier
- quartz glass
- flow control
- electrode
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64B—LIGHTER-THAN AIR AIRCRAFT
- B64B1/00—Lighter-than-air aircraft
- B64B1/06—Rigid airships; Semi-rigid airships
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Plasma Technology (AREA)
Abstract
The invention discloses a kind of plasma flow control device near space dirigible drag reduction, the device includes：Several drag reduction units, wire, dc source, the 3rd insulating barrier, microwave generator and first wave guide；Wherein, the drag reduction unit includes slot antenna, quartz glass plate, metal film, the first insulating barrier, the second insulating barrier, first electrode, second electrode and second waveguide；Each drag reduction unit is sequentially connected by the 3rd insulating barrier and connect；First wave guide is connected with second waveguide；Microwave generator is connected with first wave guide.The present invention launches microwave by quartz glass plate lower slit antenna, the uniform surface wave of large area is formed in quartz glass plate surface, and then excitating surface ripple plasma, have the advantages that generation plasma density is high, plane large area is uniform, height discharge stability and processing procedure are repeatable.
Description
Technical field
The present invention relates to plasma flow control field, more particularly to a kind of grade near space dirigible drag reduction from
Daughter flow control apparatus.
Background technology
Compared with aircraft or satellite, near space dirigible has that ground coverage is wide, the hang time is long, quick response energy
The many advantages such as power is strong, manufacture and operating cost are low, reusable, upgrading is fast, operation characteristic is good, with important army
Thing application prospect.Therefore, the development near space dirigible has urgency very high.The flight resistance of dirigible often reduces 1%,
Payload can about increase by 10%, can greatly improve flying speed, the increase voyage of aircraft, increase the stagnant space-time of dirigible
Between.
Plasma flow control is a kind of new flow control technique, turned into recent years in the world aerodynamics and
The emerging important research focus in aerothermodynamics field.Plasma flow control is mainly characterized by：Plasma is pneumatic to swash
It is electric field force effect to encourage, no moving component, response is rapid, act on bandwidth, be easy to real-time control, simple structure, energy consumption compared with
It is low.Plasma refers to that gas is ionized under High energy electromagnetic excitation, and electronics and the ion of generation coexist and high-speed motion
A kind of material existence, be to be different from conventional solid, the 4th class material aggregation state of liquids and gases.In extra electric field or
In the presence of autoexcitation electric field, electronics and ion in plasma do directed movement in the electric field, are touched with neutral particle
Hit, and own momentum, energy are transferred to surrounding air, so that the air near exposure electrode produces directed movement, shape
Into induced draft.The general principle of plasma flow control mainly uses the phase interaction of induced draft and aircraft boundary layer
With control boundary layer separation, suppression laminar flow -- Transitional And Turbulent Flow etc. reach the mesh that lift-rising drag reduction etc. improves flight vehicle aerodynamic performance
's.
At present, in plasma flow control technology frequently with surface DC corona discharge, atmospheric pressure homogeneous glow
The methods such as electric discharge, surface dielectric barrier discharge, have the shortcomings that the intensity of produced plasma, region are limited without exception,
The requirement of near space dirigible kayak body high surface area drag reduction cannot be met.
The content of the invention
Present invention solves the technical problem that being：Compared to prior art, there is provided one kind is used near space dirigible drag reduction
Plasma flow control device, induced draft is produced in the presence of Electrode Field by surface wave excitation plasma,
Realize that near space dirigible kayak body large area drag reduction flow is controlled.
The object of the invention is achieved by the following technical programs：A kind of plasma near space dirigible drag reduction
Flow control apparatus, including：Several drag reduction units, wire, dc source, the 3rd insulating barrier, microwave generator and first wave
Lead；Wherein, the drag reduction unit includes slot antenna, quartz glass plate, metal film, the first insulating barrier, the second insulating barrier, first
Electrode, second electrode and second waveguide, wherein, metal film plating is located at lower surface, left surface and the right flank of quartz glass plate；Plating
Gap is offered located at the metal film of the lower surface of quartz glass plate, slot antenna is embedded in the gap；First insulating barrier
Metal film of the bag located at left surface；Metal film of the second insulating barrier bag located at right flank；First electrode is connected with the first insulating barrier
Connect；Second electrode is connected with the second insulating barrier；One surface of second waveguide is connected with slot antenna；First electrode is by leading
Line is connected with dc source, and second electrode is connected by wire with dc source；Each drag reduction unit passes through the 3rd insulating barrier
It is sequentially connected and connects；First wave guide is connected with second waveguide；Microwave generator is connected with first wave guide.
In the above-mentioned plasma flow control device near space dirigible drag reduction, slot antenna is located at the quartz
The center line of the lower surface of glass plate.
In the above-mentioned plasma flow control device near space dirigible drag reduction, the length direction of second waveguide with
The length direction of slot antenna is parallel.
In the above-mentioned plasma flow control device near space dirigible drag reduction, the microwave of microwave generator transmitting
It is TE moulds, microwave electric field polarization direction is parallel with slot antenna.
In the above-mentioned plasma flow control device near space dirigible drag reduction, microwave electric field field intensity be E=2 ×
36.84p(1+ω2/ν2)1/2, wherein, p is ambient atmosphere pressure, and ω is microwave frequency, and ν is ionization frequency.
In the above-mentioned plasma flow control device near space dirigible drag reduction, the width of the quartz glass plate
It it is 8 times of microwave wavelength, thickness is 0.4 times of microwave wavelength.
In the above-mentioned plasma flow control device near space dirigible drag reduction, the axial direction of first wave guide and second
The axial direction of waveguide is mutually perpendicular to.
The present invention has the advantages that compared with prior art：
(1) present invention launches microwave by quartz glass plate lower slit antenna, is formed greatly in quartz glass plate surface
The uniform surface wave of area, and then excitating surface ripple plasma, with producing, plasma density is high, plane large area is equal
The advantage of even, height discharge stability and processing procedure repeatability；
(2) present invention forms electric field using galvanic electrode is connected with surface attachment, is lured in electric field by plasma
Directed movement under leading, plays a part of control flow separation, reduces dirigible resistance in the larger context.
Brief description of the drawings
Fig. 1 is the structural representation of the plasma flow control device near space dirigible drag reduction of the invention；
Fig. 2 is cloth of the plasma flow control device near space dirigible drag reduction of the invention on dirigible surface
Put schematic diagram.
Fig. 3 is the plasma flow control device drag reduction unit spliced side near space dirigible drag reduction of the invention
Formula schematic diagram.
Specific embodiment
The present invention is described in further detail below in conjunction with the accompanying drawings：
Fig. 1 is the structural representation of the plasma flow control device near space dirigible drag reduction of the invention.
As shown in figure 1, the plasma flow control device for being used near space dirigible drag reduction includes：It is drag reduction unit, wire 4, straight
Stream power supply 5, the 3rd insulating barrier 73, microwave generator 8 and first wave guide 91.Wherein,
Drag reduction unit include slot antenna 1, quartz glass plate 2, metal film 3, the first insulating barrier 71, the second insulating barrier 72,
First electrode 61, second electrode 62 and second waveguide 92, wherein, the plating of metal film 3 is located at lower surface, the left side of quartz glass plate 2
Face and right flank；Plating offers gap located at the metal film 3 of the lower surface of quartz glass plate 2, and slot antenna 1 is embedded at the gap
It is interior；The bag of first insulating barrier 71 is located at the outside of the metal film 3 of left surface；Metal film 3 of the bag of second insulating barrier 72 located at right flank
Outside；First electrode 61 is connected with the first insulating barrier 71；Second electrode 62 is connected with the second insulating barrier 72；Second waveguide
92 surface is connected with slot antenna 1；First electrode 61 is connected by wire 4 with dc source 5, and second electrode 62 is led to
Wire 4 is crossed to be connected with dc source 5.During specific implementation, as shown in figure 1, the lower surface of quartz glass plate 2, left surface and the right side
Side three is plated with metal film 3 on surface, wherein, the metal film 3 of lower surface offers the seam equal with the width of slot antenna 1
Gap, slot antenna 1 is embedded in the gap of metal film 3.First insulating barrier 71 wraps the metal film 3 of the left surface of quartz glass plate 2
Wrap, the second insulating barrier 72 wraps up the metal film 3 of the right flank of quartz glass plate 2, so as to play a part of insulation.
First electrode 61 is connected by wire 4 with the right-hand member of dc source 5, and second electrode 62 is by wire 4 and a left side for dc source 5
End is connected.It should be noted that first electrode has various with the connected mode of the first insulating barrier, all modes of connection all exist
In the range of the present embodiment protection.Second electrode has various with the connected mode of the second insulating barrier, and all modes of connection all exist
In the range of the present embodiment protection.
First wave guide 91 is connected with second waveguide 92.Specifically, as shown in figure 1, the axial direction of first wave guide 91 and second
The axial direction of waveguide 92 is mutually perpendicular to.Each first wave guide 91 is parallel to each other.
Microwave generator 8 is connected with first wave guide 91.
The operation principle of the present embodiment：Microwave generator 8 launches microwave, and microwave is drawn by first wave guide 91 and second waveguide 92
To at quartz glass plate 2, second waveguide 92 will be provided with the waveguide surface of slit and directly be attached on quartz glass plate 2, and microwave just passes through
In air on the outside of the coupling firing of slot antenna 1 to quartz glass plate 2.The electromagnetism of air is incided from inside quartz glass plate 2
In ripple, incidence angle θ i<The part electromagnetic wave of θ c (θ c are the critical angle of incidence that electromagnetic wave is reflected by medium interface), can be by narrow
Seam enters air through quartz glass plate 2；Incidence angle θ i>θ c's (θ c are the critical angle of incidence that electromagnetic wave is reflected by medium interface)
Another part electromagnetic wave is totally reflected in quartz glass plate interface, is passed toward surrounding in quartz glass plate in the form of surface wave
Defeated, its energy is constrained in the very thin plane domain in interface both sides, and field intensity is toward interface normal direction both sides exponential damping, referred to as surface
Ripple.It is also sufficiently strong along the intensity that interface is transferred to atmospheric air in electromagnetic wave, it is sufficient to tie up if the power of incident electromagnetic wave is sufficiently large
Hold high-density plasma (1012cm-3) when, under certain air pressure, antenna pattern, uniform high density of plane large area etc.
Gas ions can be produced.
The first electrode 61 of quartz glass plate both sides is connected to dc source 5 by wire 4 respectively with second electrode 62
Two ends.In the presence of direct current, an extra electric field for stabilization is produced between first electrode 61 and second electrode 62.Outer power-up
The direction of field is vertical with the direction of microwave electric field and slot antenna, and second electrode is pointed to from first electrode.Because microwave electric field is
Quick alternation, the stable state active force of its plasma is cancelled out each other, and extra electric field is stable, the electricity in plasma
Son and ion do directed movement in extra electric field, are collided with neutral particle, and own momentum, energy are transferred into surrounding
Air, so that the air near drag reduction cell surface produces directed movement, forms induced draft.Using induced draft with fly
The interaction in row device boundary layer, control boundary layer separation, suppression laminar flow -- Transitional And Turbulent Flow etc., reaches the purpose of drag reduction.
In above-described embodiment, the quantity of drag reduction unit is several, and the quartz glass plate 2 in several drag reduction units is successively
It is connected.The quantity of the drag reduction unit shown in Fig. 1 is three, accordingly, there is three quartz glass plates 2, the quartz glass on the left side
The right-hand member of plate is connected with the left end of quartz glass plate of centre, the right-hand member of middle quartz glass plate and the quartz glass on the right
The left end of plate is connected.It should be noted that the mode of each quartz glass plate connection has various, all modes of connection are all at this
In the range of embodiment protection.
Further, each quartz glass plate 2 is equal in magnitude.Specifically, the width of each quartz glass plate 2, length
It is equal with thickness.
In above-described embodiment, slot antenna 1 is located at the center line of the lower surface of quartz glass plate 2.Specifically, slot antenna
1 is located on the center line of the lower surface of quartz glass plate 2, and quartz glass plate 2 is traversed in the direction vertical with airship flight direction.It is narrow
The seam opposite side of antenna 1 is attached to the upper surface of second waveguide 92, further, length direction and the slot antenna 1 of second waveguide 92
Length direction it is parallel.
In above-described embodiment, the microwave of the transmitting of microwave generator 8 is TE moulds, microwave electric field polarization direction and slot antenna 1
It is parallel.Microwave electric field field intensity is E=2 × 36.84p (1+ ω2/ν2)1/2, wherein, p is ambient atmosphere pressure, and ω is microwave frequency, ν
It is ionization frequency.
In above-described embodiment, the width of quartz glass plate 2 is 8 times of microwave wavelength, and thickness is 0.4 times of microwave wavelength.
When the microwave using 24GHz, quartz glass plate width is 0.1m, and thickness is 0.005m.
Fig. 2 is cloth of the plasma flow control device near space dirigible drag reduction of the invention on dirigible surface
Put schematic diagram.As shown in Fig. 2 quartz glass plate 2 collectively constitutes drag reduction together with the metal film 3 of its inner side covering with slot antenna 1
Unit, lays in dirigible by caudal surface.Laying scope is：Along dirigible 1~2m of length direction, around dirigible circumferential
Week.Equal-sized drag reduction unit is arranged in order, and the one side equipped with slot antenna 1 is attached to dirigible kayak body outside, and another side is exposed
In atmosphere.First electrode 61 and second electrode 62 are attached to dirigible kayak body outside, and first electrode 61 and second electrode 62 are led to respectively
Wire 4 is crossed to be connected on dc source 5.Wire 4, dc source 5, microwave generator 8, first wave guide 91 and second waveguide 92 are pacified
Inside dirigible kayak body.
Fig. 3 is the plasma flow control device drag reduction unit spliced side near space dirigible drag reduction of the invention
Formula schematic diagram.As shown in figure 3, the first insulating barrier 71 is arranged at the upstream of quartz glass plate 2 so that quartz glass plate 2 and first
Electrode 61 insulate.Second insulating barrier 72 is arranged at the downstream of quartz glass plate 2 so that quartz glass plate 2 is exhausted with second electrode 62
Edge.Two adjacent drag reduction units are connected by the 3rd insulating barrier 73, specifically, the second electrode 62 of the drag reduction unit on the left side
It is connected with the 3rd insulating barrier 73, the first electrode 61 of the drag reduction unit on the left side is connected with the 3rd insulating barrier 73.So as to pass through
3rd insulating barrier 73 ensures adjacent two drag reduction units insulation.
The present invention launches microwave by quartz glass plate lower slit antenna, and large area is formed in quartz glass plate surface
Uniform surface wave, and then excitating surface ripple plasma, with producing, plasma density is high, plane large area is uniform, high
The advantage of degree discharge stability and processing procedure repeatability；And the present invention is utilized and is connected with galvanic electrode in surface attachment shape
Into electric field, by directed movement of the plasma in the case where electric field is induced, control flow separation is played in the larger context, is reduced
The effect of dirigible resistance.
Embodiment described above is the present invention more preferably specific embodiment, and those skilled in the art is in this hair
The usual variations and alternatives carried out in the range of bright technical scheme all should be comprising within the scope of the present invention.
Claims (7)
1. a kind of plasma flow control device near space dirigible drag reduction, it is characterised in that including：Several subtract
Resistance unit, wire (4), dc source (5), the 3rd insulating barrier (73), microwave generator (8) and first wave guide (91)；Wherein,
The drag reduction unit includes slot antenna (1), quartz glass plate (2), metal film (3), the first insulating barrier (71), second exhausted
Edge layer (72), first electrode (61), second electrode (62) and second waveguide (92), wherein, metal film (3) plating is located at quartz glass
The lower surface of plate (2), left surface and right flank；Plating opens up seamed located at the metal film (3) of the lower surface of quartz glass plate (2)
Gap, slot antenna (1) is embedded in the gap；Metal film (3) of first insulating barrier (71) bag located at left surface；Second insulation
Metal film (3) of layer (72) bag located at right flank；First electrode (61) is connected with the first insulating barrier (71)；Second electrode (62)
It is connected with the second insulating barrier (72)；One surface of second waveguide (92) is connected with slot antenna (1)；First electrode (61) is led to
Cross wire (4) to be connected with dc source (5), second electrode (62) is connected by wire (4) with dc source (5)；
Each drag reduction unit is sequentially connected by the 3rd insulating barrier (73) and connect；
First wave guide (91) is connected with second waveguide (92)；
Microwave generator (8) is connected with first wave guide (91).
2. the plasma flow control device near space dirigible drag reduction according to claim 1, its feature exists
In：Center line of the slot antenna (1) positioned at the lower surface of the quartz glass plate (2).
3. the plasma flow control device near space dirigible drag reduction according to claim 2, its feature exists
In：The length direction of second waveguide (92) is parallel with the length direction of slot antenna (1).
4. the plasma flow control device near space dirigible drag reduction according to claim 1, its feature exists
In：The microwave of microwave generator (8) transmitting is TE moulds, and microwave electric field polarization direction is parallel with slot antenna (1).
5. the plasma flow control device near space dirigible drag reduction according to claim 4, its feature exists
In：Microwave electric field field intensity is E=2 × 36.84p (1+ ω2/ν2)1/2, wherein, p is ambient atmosphere pressure, and ω is microwave frequency, and ν is
Ionization frequency.
6. the plasma flow control device near space dirigible drag reduction according to claim 1, its feature exists
In：The width of the quartz glass plate (2) is 8 times of microwave wavelength, and thickness is 0.4 times of microwave wavelength.
7. the plasma flow control device near space dirigible drag reduction according to claim 1, its feature exists
In：The axial direction of first wave guide (91) is mutually perpendicular to the axial direction of second waveguide (92).
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| CN201710077819.1A CN106892078B (en) | 2017-02-14 | 2017-02-14 | A kind of plasma flow control device near space dirigible drag reduction |
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| CN201710077819.1A CN106892078B (en) | 2017-02-14 | 2017-02-14 | A kind of plasma flow control device near space dirigible drag reduction |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110636685A (en) * | 2019-09-10 | 2019-12-31 | 空气动力学国家重点实验室 | Wall drag reduction mechanism based on plasma generator |
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| CN110636685A (en) * | 2019-09-10 | 2019-12-31 | 空气动力学国家重点实验室 | Wall drag reduction mechanism based on plasma generator |
| CN110636685B (en) * | 2019-09-10 | 2021-09-28 | 空气动力学国家重点实验室 | Wall drag reduction mechanism based on plasma generator |
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| Publication number | Publication date |
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| CN106892078B (en) | 2019-11-29 |
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