CN106499603B - A hollow cathode installation optimization method of Hall thruster based on magnetic environment - Google Patents
A hollow cathode installation optimization method of Hall thruster based on magnetic environment Download PDFInfo
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- CN106499603B CN106499603B CN201611044860.0A CN201611044860A CN106499603B CN 106499603 B CN106499603 B CN 106499603B CN 201611044860 A CN201611044860 A CN 201611044860A CN 106499603 B CN106499603 B CN 106499603B
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- hollow cathode
- hall thruster
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- magnetic induction
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- 238000000034 method Methods 0.000 title claims abstract description 24
- 238000005457 optimization Methods 0.000 title claims abstract description 14
- 238000009434 installation Methods 0.000 title abstract description 7
- 230000006698 induction Effects 0.000 claims abstract description 20
- 239000002245 particle Substances 0.000 claims description 7
- 238000005259 measurement Methods 0.000 claims description 3
- 238000005406 washing Methods 0.000 claims description 2
- 239000000919 ceramic Substances 0.000 description 3
- 241001415145 Acnistus arborescens Species 0.000 description 1
- 241000196324 Embryophyta Species 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000010884 ion-beam technique Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000007935 neutral effect Effects 0.000 description 1
- 238000006386 neutralization reaction Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0037—Electrostatic ion thrusters
- F03H1/0062—Electrostatic ion thrusters grid-less with an applied magnetic field
- F03H1/0075—Electrostatic ion thrusters grid-less with an applied magnetic field with an annular channel; Hall-effect thrusters with closed electron drift
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0081—Electromagnetic plasma thrusters
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Electromagnetism (AREA)
- Plasma Technology (AREA)
Abstract
A hollow cathode installation optimization method of a Hall thruster based on a magnetic environment relates to a method for improving the efficiency of the Hall thruster, and aims to solve the problems that the existing method for improving the efficiency of the Hall thruster is single and the efficiency of the Hall thruster cannot be further improved. Measuring the magnetic induction intensity B corresponding to the lowest potential drop of the hollow cathode0(ii) a Determining the magnetic induction intensity of the Hall thruster to be B0The coordinate set of the magnetic field isopotential line of (a) { (r, z) }; selecting a coordinate (r) advantageous for prolonging the life of the hollow cathode from a set of coordinates { (r, z) }0,z0) (ii) a Placing the hollow cathode such that the outlet of the hollow cathode is placed at (r)0,z0) At least one of (1) and (b); adjusting the angle of the hollow cathode such that the axis of the hollow cathode is equal to (r)0,z0) The magnetic induction lines of the two parts are tangent. The invention is suitable for improving the efficiency of the Hall thruster.
Description
Technical field
The present invention relates to the methods for improving hall thruster efficiency.
Background technique
Hall thruster is a kind of plasma propulsion device for fields such as Space Vehicle position holding, deep space explorations.
Due to the attribute of plasma discharge itself, the performance of this device is very sensitive to the variation of plant bulk.It studied in the past
Center of gravity is the structure size optimized inside ceramic accelerating cavity, and hall thruster efficiency is improved by optimized dimensions.Therefore it improves
The method of hall thruster efficiency is single, can not further increase hall thruster efficiency.
Summary of the invention
The purpose of the present invention is to solve it is existing improve hall thruster efficiency method it is single, can not further increase
The problem of hall thruster efficiency, to provide a kind of hollow cathode installation optimization side of hall thruster based on magnetic environment
Method.
A kind of hollow cathode of hall thruster based on magnetic environment of the present invention installs optimization method, this method packet
Include following steps:
Measurement hollow cathode potential drop magnetic induction density B corresponding when minimum0；
The magnetic induction intensity for determining hall thruster is B0Magnetic field isophote coordinate set { (r, z) }；
It is advantageously selected for extending the coordinate (r in hollow cathode service life from coordinate set { (r, z) }0,z0)；
Hollow cathode is placed, the outlet of hollow cathode is made to be placed in (r0,z0) at；
Hollow cathode angle is adjusted, the axis and (r of hollow cathode are made0,z0) at magnetic induction line it is tangent.
Preferably, B0For 20 Gausses~30 Gausses.
Preferably, the coordinate (r in hollow cathode service life is advantageously selected for from coordinate set { (r, z) }0,z0) method be,
The coordinate for washing away area positioned at high-velocity particles is screened out from coordinate set { (r, z) }, obtains the coordinate for being conducive to the hollow cathode service life
(r0,z0)。
Research finds that the design outside ceramic accelerating cavity also has more significant influence to hall thruster efficiency.Institute of the present invention
The hollow cathode being related to is exactly a subassembly outside accelerating cavity.On the basis of accelerating cavity interior optimization, pass through tune
Whole hollow cathode can advanced optimize properties of product.The present invention is pacified using the optimization hollow cathode of magnetic environment locating for hollow cathode
Holding position and angle, to improve thruster efficiency.
The present invention is suitable for improving the efficiency of hall thruster.
Detailed description of the invention
Fig. 1 is a kind of hollow cathode installation optimization of the hall thruster based on magnetic environment described in specific embodiment one
The flow chart of method；
Fig. 2 is the hollow cathode schematic view of the mounting position in specific embodiment one；
1 is the central axes of hall thruster, and 2 be magnetic induction intensity be 20 Gausses~30 Gausses magnetic field isophote, and 3 are
Hollow cathode, 4 be magnetic induction line, and 5 be magnetic pole, and 6 be magnet exciting coil, and 7 be anode (gas distributor), and 8 be ceramic accelerating cavity.
Specific embodiment
Specific embodiment 1: illustrating present embodiment, a kind of base described in present embodiment in conjunction with Fig. 1 and Fig. 2
Optimization method is installed in the hollow cathode of the hall thruster of magnetic environment, method includes the following steps:
Measurement hollow cathode potential drop magnetic induction density B corresponding when minimum0；
The magnetic induction intensity for determining hall thruster is B0Magnetic field isophote coordinate set { (r, z) }；
It is advantageously selected for extending the coordinate (r in hollow cathode service life from coordinate set { (r, z) }0,z0)；
Hollow cathode is placed, the outlet of hollow cathode is made to be placed in (r0,z0) at；
Hollow cathode angle is adjusted, the axis and (r of hollow cathode are made0,z0) at magnetic induction line it is tangent.
In the efficiency index of hall thruster, a critically important index is voltage utilization.It, which refers to, is actually used in
Accelerate the voltage of ion and the ratio of electric power output voltage, which is generally less than 1.The electricity that ion accelerating voltage, power supply export
Relationship between pressure and complete machine thrust are as follows:
In formula,
F is that particle accelerates the complete machine thrust generated, unit N；
For mass-flow rate of propellant, unit kg/s；
Z be particle band charge number, Z >=1；
E is electron charge, is equal to 1.6X10-19C；
VaccFor ion accelerating voltage, unit V
MiFor mass particle, unit kg；
Ud--- the voltage (constant pressure) of power supply output, unit V；
Δ --- the loss of voltage for needing to pay by neutral atom ionization, unit V；
Ucp--- electronics is transported to the loss of voltage required for accelerating tube i.e. hollow cathode potential drop, unit V from cathode.
Wherein, UcpMain function be that electronics is drawn out of hollow cathode, for electric discharge provide it is required ionize seed, and
The neutralization electronics of equivalent is provided for the ion beam current of ejection.As can be seen that due to power supply output voltage be it is limited and constant,
Ucp, Δ is this accelerates unrelated loss item smaller with heavy particle, then have the voltage of actual contribution bigger acceleration, accordingly
Overall efficiency is also higher.
Present embodiment is directed to Ucp, the magnetic field environment by changing hollow cathode part is proposed to reduce Ucp.It is main to think
Think to be the characteristic different using the hollow heart cathode fall of different magnetic field environment, after the sizing of thruster magnetic field, by hollow cathode
It is placed in suitable magnetic field environment.UcpInfluence factor have very much, magnetic field is that one of them is affected, and artificial controllable
Factor.More particularly to two parameters: the magnetic field strength and hollow cathode axis and magnetic induction line of hollow cathode pinhole position
Angle.
Specific embodiment 2: present embodiment is to a kind of Hall based on magnetic environment described in specific embodiment one
The hollow cathode installation optimization method of thruster is described further, in present embodiment, B0For 20 Gausses~30 Gausses.
Found by numerous studies, magnetic induction intensity be 20 Gausses~30 gauss ranges in space-time heart cathode fall most
It is small.Magnetic induction intensity is less than the section or is greater than the section, especially when magnetic field strength is in 10 Gauss, cathode fall
It dramatically increases.When the axis of hollow cathode is parallel with magnetic induction line, hollow cathode potential drop is minimum；It, should when the two is orthogonal
Potential drop will increase, and very unstable.
By the way that the outlet of hollow cathode is placed within the scope of 20 Gausses~30 Gausses magnetic induction intensity, and by hollow cathode
Axis and (r0,z0) at magnetic induction line it is tangent, can significantly reduce hollow cathode potential drop.
Specific embodiment 3: present embodiment is to a kind of Hall based on magnetic environment described in specific embodiment one
The hollow cathode installation optimization method of thruster is described further, and in present embodiment, is had from selection in coordinate set { (r, z) }
Conducive to the coordinate (r in hollow cathode service life0,z0) method be to be screened out from coordinate set { (r, z) } and wash away area positioned at high-velocity particles
Coordinate, obtain the coordinate (r for being conducive to the hollow cathode service life0,z0)。
It is obvious to a person skilled in the art that invention is not limited to the details of the above exemplary embodiments, Er Qie
In the case where without departing substantially from spirit or essential attributes of the invention, the present invention can be realized in other specific forms.Therefore, no matter
From the point of view of which point, the present embodiments are to be considered as illustrative and not restrictive, and the scope of the present invention is by appended power
Benefit requires rather than above description limits, it is intended that all by what is fallen within the meaning and scope of the equivalent elements of the claims
Variation is included within the present invention.
Although describing the present invention herein with reference to specific embodiment, it should be understood that, these realities
Apply the example that example is only principles and applications.It should therefore be understood that can be carried out to exemplary embodiment
Many modifications, and can be designed that other arrangements, without departing from spirit of the invention as defined in the appended claims
And range.It should be understood that different appurtenances can be combined by being different from mode described in original claim
Benefit requires and feature described herein.It will also be appreciated that the feature in conjunction with described in separate embodiments can be used
In other described embodiments.
Claims (3)
1. the hollow cathode of hall thruster based on magnetic environment a kind of installs optimization method, which is characterized in that this method includes
Following steps:
Measurement hollow cathode potential drop magnetic induction density B corresponding when minimum0；
The magnetic induction intensity for determining hall thruster is B0Magnetic field isophote coordinate set { (r, z) }；
It is advantageously selected for extending the coordinate (r in hollow cathode service life from coordinate set { (r, z) }0,z0)；
Hollow cathode is placed, the outlet of hollow cathode is made to be placed in (r0,z0) at；
Hollow cathode angle is adjusted, the axis and (r of hollow cathode are made0,z0) at magnetic induction line it is tangent.
2. a kind of hollow cathode of hall thruster based on magnetic environment according to claim 1 installs optimization method,
It is characterized in that, B0For 20 Gausses~30 Gausses.
3. a kind of hollow cathode of hall thruster based on magnetic environment according to claim 1 installs optimization method,
It is characterized in that, the coordinate (r in hollow cathode service life is advantageously selected for from coordinate set { (r, z) }0,z0) method be, from coordinate set
The coordinate for washing away area positioned at high-velocity particles is screened out in { (r, z) }, obtains the coordinate (r for being conducive to the hollow cathode service life0,z0)。
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102493936A (en) * | 2011-12-15 | 2012-06-13 | 哈尔滨工业大学 | Hall thrustor based on magnetic focusing |
| CN103953517A (en) * | 2014-05-13 | 2014-07-30 | 哈尔滨工业大学 | Hall thruster improving device |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP2008223655A (en) * | 2007-03-14 | 2008-09-25 | Japan Aerospace Exploration Agency | Hall type electric propulsion machine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102493936A (en) * | 2011-12-15 | 2012-06-13 | 哈尔滨工业大学 | Hall thrustor based on magnetic focusing |
| CN103953517A (en) * | 2014-05-13 | 2014-07-30 | 哈尔滨工业大学 | Hall thruster improving device |
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