CN102869181A - Electrode structure and electrode fixing structure for plasma thruster - Google Patents
Electrode structure and electrode fixing structure for plasma thruster Download PDFInfo
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- CN102869181A CN102869181A CN2012103266205A CN201210326620A CN102869181A CN 102869181 A CN102869181 A CN 102869181A CN 2012103266205 A CN2012103266205 A CN 2012103266205A CN 201210326620 A CN201210326620 A CN 201210326620A CN 102869181 A CN102869181 A CN 102869181A
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Abstract
The invention discloses an electrode structure for a plasma thruster. The electrode structure comprises a cathode and an anode, wherein the cathode is a cylindrical cathode, one end of the cathode is inserted into a tube-shaped insulator with a through hole, the other end of the insulator is provided with the anode, a hollow cavity is arranged in the anode in a same axial direction with the through hole of the tube-shaped insulator, the sectional area of the cavity is progressively increased along the axial extension direction of the tube-shaped insulator, and threads are arranged on the inner surface of the tube-shaped insulator and are single threads, double threads or multiple threads. According to the electrode structure disclosed by the invention, through a reasonable electrode structure design, better electric heating acceleration effect is obtained by utilizing the aerodynamic force generated due to difference of pressures insides and outsides a tube after discharging, thus effectively improving the thrusting effect and the working efficiency of the pulse plasma thruster. With the adoption of the electrode structure, the thrusting effect is good, and a plasma obtained after discharging is large in density and has a simple structure.
Description
Technical field
The invention belongs to the electric propulsion technology field that microsatellite is used, relate to a kind of electrode structure for plasma propeller, relate to more specifically a kind of pulsed plasma thruster of cylinder inner surface discharge of this electrode structure of application.
Background technology
For space propulsion system, studying at present more is chemical propulsion system and electric propulsion system.Traditional chemical task propulsion system is applied to microsatellite, quality and volume are large, specific impulse is little, complex structure, greatly limited its application on microsatellite, and various types of electric propulsion system can remedy this deficiency just, becomes the ideal chose of microsatellite propulsion system.In many electric propulsion systems, pulsed plasma thruster is a kind of low thrust electromagnetic thruster, has than the advantage such as leaping high, quality is little, and the attitude control, the position that can be used for microsatellite keep and drag compensation, realize precise formation flight.
Still there is the solution that requires study of many problems at present in pulsed plasma thruster, and wherein one of the most obvious problem is exactly that efficient is low, and the plasma density that be in particular in that thrust is less, produces during discharge is less etc.And the low main cause of propulsive efficiency to be the utilance of propellant low and acceleration efficiency that cause is low, and electrode structural designs is unreasonable etc.In addition, generally need to design spark plug and supply with spring for traditional pulsed plasma thruster, yet, there is certain randomness in propeller igniting discharge, and supply with spring in the space environment and understand the performance because weightlessness may be lost the job, thereby can affect the stability of pulsed plasma thruster service behaviour.
A kind of " with the pulsed plasma thruster of ceramic air spout electrode " and " side wall surface arranges the pulsed plasma thruster of ceramic nozzle " have been proposed respectively among Chinese patent CN101260873A and the CN102297105A, by at metal electrode ceramic nozzle being set, improved to a certain extent acceleration performance.But two patents all are arranged on the ceramic nozzle of insulation on the metal electrode, and the resistance that this can increase main discharge circuit reduces the discharging current under the identical discharge energy, thereby affects electromagnetism acceleration effect and the thrust effect of pulsed plasma thruster.
Summary of the invention
The present invention is directed to the defective that prior art exists, a kind of electrode structure for plasma propeller has been proposed, by rational electrode structural designs, thereby an aerodynamic force that inside and outside draught head produces obtains preferably electric heating acceleration effect after utilizing discharge, has effectively improved thrust effect and the operating efficiency of pulsed plasma thruster.
The object of the present invention is to provide that a kind of thrust effect is good, the plasma density that the obtains electrode structure that is used for plasma propeller large, simple in structure after the discharge.
For solving the problems of the technologies described above, realize purpose of the present invention, technical scheme provided by the invention is: a kind of electrode structure for plasma propeller, comprise negative electrode and anode, and described negative electrode is cylindric negative electrode, the one end insertion one of negative electrode has the tubular insulator of through hole, the other end of insulator is provided with anode, and wherein, anode interior is provided with hollow cavity, the coaxial setting of the through hole of cavity and tubular insulator, and the area of section of cavity increases progressively along tubular insulator axially-extending direction.
The inner surface of described tubular insulator is provided with screw thread.Described screw thread is single thread or double thread.
Through-hole diameter in one end section of the cavity of described anode interior and the tubular insulator is identical and connect as one.
The through-bore axis of the border of described cavity and tubular insulator is formed with angle α, and angle α is between 5 °-60 °, and angle α is 20 ° among the present invention.
The cavity of described anode interior is truncated cone-shaped, and the through-hole diameter in its upper bottom surface diameter and the tubular insulator is identical, and the bottom surface diameter is identical with the overall diameter of tubular insulator.
It is a kind of for the fixing fixed structure of the electrode structure of plasma propeller that the present invention also provides, comprise rotating parts, this is rotatable to comprise that two are oppositely arranged and the semi-circular member structure of fixed distance apart, wherein, described negative electrode is fixed on the left semicircle member by supporting construction, supporting construction comprises that one is fixed on the support bar on the left semicircle member, support bar top is provided with a supported hole, be equipped with one in the supported hole and screw part, negative electrode is positioned at the outer partial fixing of tubular insulator and is screwing on the part; Described two semicircle members can be around the fixed axis rotation.
The present invention also provides a kind of plasma circuit for generating of using the plasma electrically electrode structure.
The present invention also provides a kind of plasma producing apparatus of using the plasma electrically electrode structure in addition.
The present invention contrasts prior art and has the following advantages:
The direction of motion that produces plasma after the discharge of traditional plasma propeller is vertical with injection direction, needing to change the motion of a charged particle direction by electromagnetic force realizes spraying, negative electrode, anode and polytetrafluoro insulator are axially (being injection direction) layout among the present invention, and the direction of motion that produces plasma after the discharge is namely consistent with injection direction; The helicitic texture design of cylindric insulator inner surface has increased creepage distance, and the plasma and the insulator inner surface collision frequency that produce after the discharge are increased, and the plasma density that obtains is larger; The present invention has designed nozzle-like anode, and the sectional area of anode tube becomes greatly gradually, can reduce as much as possible the local loss that produces greatly because of suddenly change of runner; Various particle encounter polytetrafluoro inner surfaces during discharge, ablated and the temperature in polytetrafluoro surface surface raises, cause polytetrafluoro cylinder internal gas pressure sharply to raise, and it is also lower in the relative cylinder of the pressure in the anode cavity, the plasma that discharge generates accelerates ejection under the pneumatic expansion force effect that inside and outside differential pressure produces, thereby can obviously improve the angle of rake thrust effect of body and operating efficiency.
And the plasma propeller size of using this electrode structure is little, lightweight, simple in structure, need not any moving component, for example supplies with spring structure and spark plug configuration, long service life, discharge stability and good reproducibility; Nozzle arrangements itself is exactly the anode of sparking electrode, has overcome the problem that increases owing to the resistance that ceramic nozzle is set makes discharge loop, has improved electromagnetism acceleration effect and the thrust effect of pulsed plasma thruster.
Description of drawings
When considered in conjunction with the accompanying drawings, by the following detailed description of reference, can more completely understand better the present invention and easily learn wherein many advantages of following, but accompanying drawing described herein is used to provide a further understanding of the present invention, consist of a part of the present invention, illustrative examples of the present invention and explanation thereof are used for explaining the present invention, do not consist of to improper restriction of the present invention, wherein:
Fig. 1 is electrode structure schematic diagram of the present invention;
Fig. 2 is the structural representation of the cylindric insulator among Fig. 1;
Fig. 3 is the structural representation after structure shown in Figure 1 arranges rotatable part;
Fig. 4 is the left view of structure shown in Figure 1;
Fig. 5 is the concrete discharge circuit figure of a kind of electrode structure for plasma propeller of the embodiment of the invention;
Fig. 6 is the system schematic that embodiment of the invention sonde method is measured plasma density;
Fig. 7 shows cylindric insulator inner surface has helicitic texture to utilize the situation of the plasma density that sonde method records with without helicitic texture the time;
Fig. 8 is the variation relation schematic diagram of maximum field intensity between interior α angle (0 °-90 °) variation of anode cavity of the present invention and electrode.
Embodiment
For above-mentioned purpose of the present invention, feature and advantage can be become apparent more, the present invention is further detailed explanation below in conjunction with the drawings and specific embodiments.
Fig. 1 is electrode structure schematic diagram of the present invention, in the present embodiment, comprising: cylindric negative electrode 1, cylindric insulator 2, anode 3, and wherein, cylindric negative electrode 1 diameter is 5mm, and length is 10mm, and the material of negative electrode can adopt the metals such as lead or aluminium.One end of cylindric negative electrode 1 inserts the inside of the cylindric insulator 2 with through hole 21 and close contact with it, and it is adjustable that cylindric negative electrode 1 enters the distance of inside of cylindric insulator 2, but should guarantee that the contact position between cylindric negative electrode 1 front end face and cylindric insulator 2 inner via holes 21 does not arrive cylindric insulator 2 inner surface screw thread 2a positions.
Fig. 2 is the structural representation of the cylindric insulator 2 among Fig. 1.In the present embodiment, cylindric insulator 2 inner surfaces of polytetrafluoro are designed with helicitic texture.Screw thread 2a can be structure as shown in Figure 2, and it can also be double thread structure or multi start thread structure, enumerates no longer one by one here.Cylindric insulator 2 connects as one with anode 3.
The axis of the through hole 21 of the border of cavity 31 and cylindric insulator 2 is formed with angle α, and angle α is between 5 °-60 °, and selecting angle α in the present embodiment is 20 °.
About the selection of angle α, the present invention uses electromagnetic field simulation software Ansoft Maxwell
This plasma propeller electrode structure has been carried out Electric Field Simulation.Along with the α angle changes, the variation of electric field strength as shown in Figure 8 between electrode.We can find out from Fig. 8, and as α during greater than 60 °, electric field strength obviously reduces, and means that the plasma density that discharge generates reduces, and the present invention then wishes the design by this electrode structure, increases the density of the plasma that generates.In addition, when α=0 ° or when too small, anode become one with the cylinder of insulator with diameter, the aerodynamic force (or aerodynamic force is very little) that does not so just exist the draught head after the discharge to produce has been run counter to innovative point of the present invention and original intention; When α was excessive, according to aerodynamics as can be known, gas flow rate can obviously reduce, and pressure and the component of wall friction power on injection direction that can cause acting on the ejection cross section reduces, and had affected greatly the thrust effect of plasma propeller.Therefore, the excursion that we select the α angle in this electrode structural designs is 5 °-60 °.According to interelectrode electric field strength simulation result, gas dynamical related content and experiment current conditions, in the present embodiment, we select the α angle is 20 °.
The present embodiment is designed to truncated cone-shaped with the cavity 31 of anode 3 inside, and its upper bottom surface diameter is identical with through hole 21 diameters of cylindric insulator 2, and the bottom surface diameter is identical with the overall diameter of cylindric insulator 2.
For satisfying plasma propeller different task needs, need to change cylindric insulator 2 diameters to regulate cylindric insulator 2 inside and outside pressure extents.In the present embodiment, cylindric insulator 2 is interior diameter 5mm, and overall diameter is 20.7mm, and length is the cylinder-like structure of 20mm.When the interior diameter of cylindric insulator 2 changed, the diameter of negative electrode 1 was also answered respective change, to guarantee cylindric negative electrode 1 and cylindric insulator 2 close contacts.
In the present embodiment, the material of anode 3 can adopt the metals such as steel or aluminium.It is truncated cone-shaped that anode 3 adopts opening shape, and wherein, the upper bottom surface circular diameter is 12.8mm, and the bottom surface circular diameter is 20.7mm.
Fig. 3 is structure setting shown in Figure 1 and the structural representation of rotatable part.The other end that cylindric negative electrode 1 does not enter cylindric insulator 2 is fixed in (as shown in Figure 4, wherein Fig. 4 is the left view of Fig. 3) on the cathode support member 6 by bolt 4.Cathode support member 6 is made by stainless steel metal, on its surface screw thread can be set, and is convenient to the length that Wehnelt cathode enters insulator, to satisfy angle of rake different requirement.The embodiment of the invention also comprises rotating parts, and as shown in Figure 3, rotating parts comprises that two are oppositely arranged the also semicircle member of fixed distance apart, are respectively metal semicircle member 5a and polytetrafluoro semicircle member 5b.Wherein, cylindric negative electrode 1 places the part that screws that screws part 4(the present embodiment to adopt bolt) in and be fixed on the metal semicircle member 5a by cathode support member 6.Two semicircle members can drive two electrodes and carry out 360 ° of rotations in the vacuum discharge chamber, and then the plasma that drives axially generation scans different zones, become possibility so that utilize plasma to carry out the large tracts of land material processed, be convenient to process the work of space diverse location.
Fig. 5 is the concrete discharge circuit figure of embodiment of the invention pulsed plasma thruster.It is 13us that discharge power supply adopts the duration, and discharging current is in the pulse form of power of 100-300A.The specific works principle is: the 220V AC power, the process transformer boosts, rectification multiple pressuring circuit charges to the capacitor C 2 of 0.1 μ F.When applying firing pulse for 3 gaps 7,3 gap conductings, capacitor C 2 is applied to the electrode two ends by 27 Ω resistance, 160 μ H inductance with negative high voltage, and the discharge generation plasma occurs between electrode.Negative electrode connects the power supply high-pressure side by binding post, and anode is by 1 Ω grounding through resistance.
Fig. 6 is the system schematic that embodiment of the invention sonde method is measured plasma density.Adopt in the present embodiment Langmuir probe article on plasma volume density to measure, P1, P2 are measuring probe, and each probe diameter is 1mm, and length is 8.5mm, and the distance between probe and sparking electrode is adjustable.Electrode and measuring probe all place among the vacuum chamber 8.Apply certain voltage at probe, can detect time dependent saturated electrons current waveform.By changing voltage, for example electric probe is pressed and is got respectively 0V, 5V, 10V in the present embodiment ... 60V, continuous 5 discharges are read the saturated electrons current peak and are asked its mean value as measured value by oscilloscope 9 under each magnitude of voltage.In order to record stable electronic current, at DC power supply (DC1, DC2) and sampling resistor (R1, R2) two ends parallel voltage-stabilizing branch road (C3 and R2 series connection part, C4 and R4 series connection part).
Fig. 7 shows the situation that polytetrafluoro insulator inner surface design helicitic texture utilizes the plasma density that sonde method records with without helicitic texture the time.In the present embodiment, by adopting the Langmuir probe method can record the situation of polytetrafluoro insulator inner surface design helicitic texture plasma density with without helicitic texture the time.Measured result shows, under the electrode structure of the present embodiment, the plasma density that polytetrafluoro insulator inner surface records when being designed with helicitic texture is the plasma density when not having helicitic texture obviously, illustrates that polytetrafluoro insulator inner surface is designed with helicitic texture and can obtains highdensity plasma.
Aerodynamic force and Lorentz force mainly can be divided in the thrust source of pulsed plasma thruster, and acceleration mechanism is divided into the electric heating acceleration and electromagnetism accelerates.Angle of rake accelerator mainly is divided into two stages: the phase I mainly occurs in polytetrafluoro surface (being region of discharge), and this process is called as the electric heating stage; Second stage refers to after plasma leaves the region of discharge district, because the magnetic field that motion of a charged particle produces.Charged particle accelerates under the effect of magnetic field force (being Lorentz force), and electric field force accounts for the leading position of acceleration, and this stage is called as the electromagnetism boost phase.
This angle of rake course of work is as follows: as shown in Figure 5, when applying firing pulse for 3 gaps 7,3 gap conductings, capacitor C 2 is applied to the electrode two ends by 27 Ω resistance, 160 μ H inductance with negative high voltage, and the discharge generation plasma occurs between electrode.Various particles this moment (comprising electronics, ion and neutral particle) frequently clash into the polytetrafluoro surface, and the polytetrafluoro surface is ablated, ionization, and temperature is more and more higher, forms gradually plasma slab.Increasing rapidly of plasma slab particle causes near pressure sharply to rise.Pressure is also lower with respect to plasma slab in the cavity of rear surface anode, and the particle that the polytetrafluoro discharge generates accelerates ejection under the effect of the pneumatic expansion force that inside and outside differential pressure produces.This is the phase I that propeller accelerates.Discharge occuring between electrode can form an axial main discharge current, thereby produces helical magnetic field.Charged particle after electric heating accelerates arrives anode region, and charged particle is subject to J * B Lorentz force effect and is again accelerated in this zone, and this is the second stage that propeller accelerates.Under the acting in conjunction of aerodynamic force and electromagnetic force, plasma and the neutral gas of discharge generation are accelerated, and the ejection of expanding produces thrust.
Although the present invention with preferred embodiment openly as above; but it is not to limit the present invention; any those skilled in the art without departing from the spirit and scope of the present invention; can make possible change and modification, so protection scope of the present invention should be as the criterion with the scope that claim of the present invention was defined.As mentioned above, embodiments of the invention are explained, but as long as not breaking away from fact inventive point of the present invention and effect can have a lot of distortion, this will be readily apparent to persons skilled in the art.Therefore, such variation also all is included within protection scope of the present invention.
Claims (10)
1. electrode structure that is used for plasma propeller, comprise negative electrode and anode, it is characterized in that, described negative electrode is cylindric negative electrode, and the end insertion one of negative electrode has the tubular insulator of through hole, and the other end of insulator is provided with anode, wherein, anode interior is provided with hollow cavity, the coaxial setting of through hole of cavity and tubular insulator, and the area of section of cavity increases progressively along tubular insulator axially-extending direction.
2. the electrode structure for plasma propeller according to claim 1 is characterized in that, the inner surface of described tubular insulator is provided with screw thread.
3. the electrode structure for plasma propeller according to claim 2 is characterized in that, described screw thread is single thread or double thread.
4. the electrode structure for plasma propeller according to claim 1 is characterized in that, the through-hole diameter in an end section of the cavity of described anode interior and the tubular insulator is identical and connect as one.
5. the electrode structure for plasma propeller according to claim 4 is characterized in that, the through-bore axis of the border of described cavity and tubular insulator is formed with angle α, and angle α is between 5 °-60 °.
6. the electrode structure for plasma propeller according to claim 5 is characterized in that, described angle α is 20 °.
7. the electrode structure for plasma propeller according to claim 1, it is characterized in that, the cavity of described anode interior is truncated cone-shaped, and the through-hole diameter in its upper bottom surface diameter and the tubular insulator is identical, and the bottom surface diameter is identical with the overall diameter of tubular insulator.
8. fixing fixed structure of each described electrode structure for plasma propeller of claim 1 to 8, it is characterized in that, comprise rotating parts, this is rotatable to comprise that two are oppositely arranged and the semi-circular member structure of fixed distance apart, wherein, described negative electrode is fixed on the left semicircle member by supporting construction, supporting construction comprises that one is fixed on the support bar on the left semicircle member, support bar top is provided with a supported hole, be equipped with one in the supported hole and screw part, negative electrode is positioned at the outer partial fixing of tubular insulator and is screwing on the part; Described two semicircle members can be around the fixed axis rotation.
9. plasma circuit for generating of using the described electrode structure of above-mentioned 1 to 8 arbitrary claim.
10. plasma producing apparatus of using the described electrode structure of above-mentioned 1 to 8 arbitrary claim.
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| CN102869181B (en) | 2016-04-13 |
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