CN114674474A - Hall thruster thrust density distribution measurement - Google Patents

Hall thruster thrust density distribution measurement Download PDF

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CN114674474A
CN114674474A CN202210200283.9A CN202210200283A CN114674474A CN 114674474 A CN114674474 A CN 114674474A CN 202210200283 A CN202210200283 A CN 202210200283A CN 114674474 A CN114674474 A CN 114674474A
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ion
interface
hall thruster
thrust
density
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CN114674474B (en
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龙建飞
徐禄祥
柏树
郭宁
吴铭钐
周艳波
罗威
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Hangzhou Institute of Advanced Studies of UCAS
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
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Abstract

The thrust density distribution measurement of the Hall thruster comprises the following steps: acquiring a zero potential interface of a plume region of a Hall thruster; step two, diagnosing the ion density on the interface S1; step three, diagnosing ion energy on a boundary surface S1; step four, correcting ion energy distribution on the interface S1, and loading the ion number density obtained by using a Faraday probe as weight on a normalized ion energy distribution function obtained by a retardation potential analyzer to obtain a corrected ion energy distribution function; and step five, acquiring the thrust density distribution of the Hall thruster. The method solves the problem of measurement of the thrust density distribution characteristic of the Hall thruster, reduces the loss degree of received ion current in the measurement process by measuring the key characteristic parameters of the beam current of the Hall thruster and introducing the ion loss coefficient, realizes quantitative description of the thrust density distribution characteristic measurement, and provides a foundation for optimization and evaluation of the thrust performance of the Hall thruster.

Description

Hall thruster thrust density distribution measurement
Technical Field
The invention relates to the field of measurement of thrust density of Hall thrusters, in particular to measurement of thrust density distribution of a Hall thruster.
Background
The Hall thruster ionizes and accelerates working medium gas by using an orthogonal electromagnetic field, converts electric energy into beam kinetic energy to obtain thrust, and has the advantages of simple structure, high efficiency, long service life and the like. Compared with an ion thruster, the Hall thruster gets rid of the limitation of space charge to realize higher thrust density, but the divergence angle of the Hall thruster is larger, the non-uniformity of the output thrust density distribution of the Hall thruster is more prominent, meanwhile, the non-axial symmetry is accompanied, the eccentric effect of thrust is easy to generate and the spacecraft is caused to generate interference torque, and if the correction is not carried out, the attitude and the orbit of the spacecraft can deviate from the preset orbit for a long time. Therefore, the Hall thruster thrust distribution measurement is carried out, the thrust distribution characteristics are mastered, and the method has important significance for performance evaluation and space application.
The Hall thruster beam mainly contains multi-component particles such as monovalent ions, doubly charged ions, exchange charge ions, electrons, neutral atoms and the like. The majority of neutral atoms from the anode are ionized, and a small amount of neutral atoms which are not ionized escape from the channel outlet in a thermal diffusion motion mode; the ions generated by ionization are ejected out of the channel under the action of an accelerating electric field, and the ions possibly collide with the inner wall surface and the outer wall surface of the channel to change the direction during acceleration, and meanwhile, the high-speed ions and neutral atoms generate exchange charge collision to generate exchange charge ions; the electrons are attracted by the high voltage of the anode to move into the channel and are restrained by the magnetic field. The component particles have unique spatial distribution and show high nonuniformity in space, and the speed size and the speed direction of each component particle are greatly different, so that the thrust density of the thruster has certain complexity.
The existing thrust measurement mainly aims at measuring the total thrust of a Hall thruster, and cannot measure the thrust on a unit area, namely the thrust density distribution. The thrust distribution of a general thruster has central axial symmetry, so that the total thrust vector of the thruster still follows the central axis of the thruster, and in the application of the micro-Newton Hall electric thruster, the non-axial symmetry influences the space application of the thruster. Therefore, how to quantitatively measure the thrust density distribution of the hall thruster is a problem to be solved at present.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provide a Hall thruster thrust density distribution measurement method.
The technical scheme of the invention is as follows: the Hall thruster thrust density distribution measurement comprises the following steps,
step one, acquiring a zero potential interface of a plume region of a Hall thruster
Diagnosing the potential of the plume region by adopting a Langmuir single probe to obtain a measurement position
Figure BDA0003529100030000021
The abscissa of the inflection point of the volt-ampere characteristic curve is the space potential V of the plasma in the plume regionp0；
The Langmuir probe is installed on a stepping motor, and the stepping motor is controlled to enable the Langmuir probe to move and diagnose in a plume region of the Hall thruster, so that the potential distribution of the plume region of the Hall thruster is obtained
Figure BDA0003529100030000022
Extracting a zero potential surface of the plume field as an interface S1 on the basis;
step two, diagnosis of ion density on the interface S1
Plasma density was diagnosed using a faraday probe at interface S1. According to the Faraday probe principle, the plasma density is calculated according to the measured current value, and the calculation formula is as follows:
Figure BDA0003529100030000023
in the formula (I), the compound is shown in the specification,
Figure BDA0003529100030000024
as a Faraday probe at interface S1
Figure BDA0003529100030000025
The test current obtained at the location, q is the ionic charge, AfFor the effective collection area of the faraday probe,
Figure BDA0003529100030000026
is composed of
Figure BDA0003529100030000027
Ion density of sites, miIs the mass of the ion;
further, the method can be obtained as follows:
Figure BDA0003529100030000031
step three, ion energy diagnosis on the interface S1
Diagnosing the ion energy on the interface S1 by adopting a retardation analyzer to obtain ion energy distribution curves of different energy levels on the interface S1 of the Hall thruster; the relationship between the current obtained by the collector of the retardation potential analyzer and the ion velocity distribution is as follows:
Figure BDA0003529100030000032
in the formula (I), the compound is shown in the specification,
Figure BDA0003529100030000033
test Current obtained for the collector of the retardation potential Analyzer, ArThe area of a collector of the retarding potential analyzer is shown, q is the charge quantity of ions,
Figure BDA0003529100030000034
is ion density, U is blocking gate voltage, viIs the speed of the ions and the ion density,
Figure BDA0003529100030000035
is an ion velocity distribution function;
the relationship between ion velocity and gate voltage is:
Figure BDA0003529100030000036
The function that converts the collector current to voltage U according to equation (4) yields:
Figure BDA0003529100030000037
in the formula (I), the compound is shown in the specification,
Figure BDA0003529100030000038
as a function of ion energy distribution;
differentiating U on two sides of the equation of formula (5) respectively to obtain:
Figure BDA0003529100030000039
and further obtaining an ion energy distribution function:
Figure BDA0003529100030000041
step four, correcting the ion energy distribution on the interface S1
To characterize the extent of the loss of the retardation analyzer for the received ion current, an ion loss coefficient K is defined, which is expressed as follows:
Figure BDA0003529100030000042
in the formula (I), the compound is shown in the specification,
Figure BDA0003529100030000043
for the Faraday probe in place
Figure BDA0003529100030000044
The current of the received ions is detected,
Figure BDA0003529100030000045
the ion current received by the blocking grid at the same position of the blocking potential analyzer under the condition of suspension voltage is adopted;
the corrected ion energy distribution function is obtained as:
Figure BDA0003529100030000046
and solving the average energy of the ions according to the modified ion energy distribution function:
Figure BDA0003529100030000047
and obtaining the average velocity of the ions:
Figure BDA0003529100030000048
step five, obtaining the thrust density distribution of the Hall thruster
On the boundary surface S1
Figure BDA0003529100030000049
For a position, the average velocity is
Figure BDA00035291000300000413
Ion flow across the infinitesimal area
Figure BDA00035291000300000410
The generated axial thrust satisfies the following formula:
Figure BDA00035291000300000411
in the formula, theta represents an included angle between the ion movement speed and the axial direction of the thruster, and beta represents
Figure BDA00035291000300000412
And the included angle is formed between the normal direction and the axial direction of the thruster.
Defining the axial thrust magnitude in unit area as thrust density to obtain the axial thrust magnitude on a boundary surface S1
Figure BDA0003529100030000051
Thrust density at the location is:
Figure BDA0003529100030000052
and controlling the stepping motor to move to obtain plasma density and average speed diagnostic parameters on the interface S1 so as to obtain the thrust density distribution of the Hall thruster.
Compared with the prior art, the invention has the following characteristics:
according to the method, the Hall thruster thrust density distribution is obtained by measuring the Hall thruster beam current key characteristic parameters and combining theoretical calculation, so that quantitative description of the Hall thruster thrust density distribution characteristic measurement is realized, and conditions are provided for further optimization and evaluation of the Hall thruster thrust performance.
The detailed structure of the present invention will be further described with reference to the accompanying drawings and the detailed description.
Drawings
FIG. 1 is a flow chart for measuring thrust density distribution of a Hall thruster;
FIG. 2 is a diagram illustrating a measurement of a potential at a plume region of a Hall thruster in an embodiment I;
FIG. 3 is a diagram illustrating measurement of ion density in a plume region of a Hall thruster in an embodiment I;
FIG. 4 is a diagram illustrating measurement of ion energy in a plume region of a Hall thruster in an embodiment I;
fig. 5 is a thrust density distribution measurement diagram of the hall thruster in the first embodiment.
Detailed Description
In the first embodiment, as shown in fig. 1 to 5, the measurement of thrust density distribution of the hall thruster, taking a 200W hall thruster as an example, includes the following steps:
step one, acquiring a zero potential interface of a plume region of a Hall thruster
Adopting Langmuir probe to diagnose the potential of the plume region and obtaining the measurement position according to the working principle of the Langmuir probe
Figure BDA0003529100030000053
The voltage-current characteristic curve between the measurement voltage and the current has an inflection point at the combination position of the transition region and the electron saturation region, and the abscissa of the inflection point is the space potential V of the plasma in the plume regionp0。
The Langmuir probe is installed on a stepping motor, the stepping motor is controlled to enable the Langmuir probe to move in the plume region of the thruster according to the plume region of the Hall thruster, and the potential distribution of the plume region of the Hall thruster is obtained according to the diagnosis parameters
Figure BDA0003529100030000061
Fig. 2 shows a potential measurement diagram of the plume region of the hall thruster.
On the basis of obtaining the potential distribution, a zero potential surface is extracted to serve as an interface S1, and as the potential of the anode of the Hall thruster is high potential, the typical value is 300V, and the potential is gradually reduced along the axial direction from the outlet of the discharge channel, and the high potential distribution still exists in the plume near-field region, a strong accelerating electric field exists in the plume near-field region, the ejected beam ions are continuously accelerated, namely interaction still exists between the ejected high-speed ion flow and the Hall thruster body, and a large error exists when the thrust in the region is measured by using the high-speed ion flow speed. Therefore, a zero potential interface in the near field region of the plume of the Hall thruster is defined as an interface S1, so that the high-speed ion flow on the interface is thoroughly separated from the Hall thruster body, and the interaction between the high-speed ion flow and the Hall thruster body is avoided to ensure the accuracy of the result.
Step two, diagnosis of ion density on the interface S1
Plasma density was diagnosed using a faraday probe at interface S1. And calculating the plasma density according to the measured current value, wherein the calculation formula is as follows:
Figure BDA0003529100030000062
in the formula (I), the compound is shown in the specification,
Figure BDA0003529100030000063
as a Faraday probe at interface S1
Figure BDA0003529100030000064
The test current obtained at the location, q is the ionic charge, AfFor the effective collection area of the faraday probe,
Figure BDA0003529100030000065
is composed of
Figure BDA0003529100030000066
Ion density of sites, miIs the ion mass.
Further, the method can be obtained as follows:
Figure BDA0003529100030000071
since the collector of the faraday probe is always in a negative bias state, electrons can be shielded, but ion energy cannot be distinguished, and therefore ions including all energy are received by the collector. Fig. 3 shows an ion density measurement diagram of the plume region of the hall thruster.
Step three, ion energy diagnosis on the interface S1
And diagnosing the ion energy on the interface S1 by adopting a Retardation Potential Analyzer (RPA) to obtain ion energy distribution curves of different energy levels on the Hall thruster interface S1. According to the working principle of a retardation potential analyzer, the relationship between the current obtained by a collector and the ion speed distribution is as follows:
Figure BDA0003529100030000072
in the formula (I), the compound is shown in the specification,
Figure BDA0003529100030000073
test Current obtained for the collector of the retardation potential Analyzer, A rThe area of a collector of the retarding potential analyzer is q is the charge quantity of ions,
Figure BDA0003529100030000074
is ion density, U is blocking gate voltage, viIs the speed of the ions and the ion density,
Figure BDA0003529100030000075
as a function of ion velocity distribution.
The relationship between ion velocity and gate voltage is:
Figure BDA0003529100030000076
the function that converts the collector current to voltage U according to equation (4) yields:
Figure BDA0003529100030000077
in the formula (I), the compound is shown in the specification,
Figure BDA0003529100030000078
as a function of ion energy distribution.
Differentiating U on two sides of the equation of formula (5) respectively to obtain:
Figure BDA0003529100030000081
and further obtaining an ion energy distribution function:
Figure BDA0003529100030000082
as can be seen from equation (7), the energy distribution function of the ions can be calculated by directly deriving the bias voltage from the ion current signal measured by the retardation potential analyzer.
Step four, correcting ion energy distribution on the interface S1
Further analysis of equation (7) reveals that the ion energy distribution function will be affected by the ion density distribution and needs to be modified. Generally, four layers of grids are arranged in front of a collector of a retardation analyzer, and in an ion incidence process, part of ions are captured by the grids, so that corresponding ion loss is caused, and the loss distorts collected ion number density information, so that correction is needed.
In order to characterize the degree of loss of the retardation analyzer for the received ion current, an ion loss coefficient K is defined by calculating the same position
Figure BDA0003529100030000083
By the ionic current received by the Faraday probe
Figure BDA0003529100030000084
Ion current received by the ion blocking grid suspension voltage condition with the blocking potential analyzer
Figure BDA0003529100030000085
The ion loss coefficient K is obtained as follows:
Figure BDA0003529100030000086
therefore, the corrected ion energy distribution function can be obtained as:
Figure BDA0003529100030000087
based on the corrected ion energy distribution function, the average energy of the ions can be calculated.
And solving the average energy of the ions according to the modified ion energy distribution function:
Figure BDA0003529100030000091
fig. 4 shows a diagram of measuring ion energy in a plume region of a hall thruster.
And obtaining the average velocity of the ions:
Figure BDA0003529100030000092
step five, obtaining the thrust density distribution of the Hall thruster
At the interface S1
Figure BDA0003529100030000093
At a position with an average velocity of
Figure BDA0003529100030000099
Ion flow across the infinitesimal area
Figure BDA0003529100030000094
The generated axial thrust satisfies the following formula:
Figure BDA0003529100030000095
in the formula, theta represents an included angle between the ion movement speed and the axial direction of the thruster, and beta represents
Figure BDA0003529100030000096
The included angle between the normal direction and the axial direction.
Defining the axial thrust magnitude in unit area as thrust density to obtain the axial thrust magnitude on a boundary surface S1
Figure BDA0003529100030000097
The thrust density at the location is:
Figure BDA0003529100030000098
controlling the stepping motor to move, selecting a reasonable measuring area according to engineering requirements, and obtaining plasma density and average speed diagnosis parameters on an interface S1 so as to obtain the thrust density distribution of the Hall thruster, such as the thrust density distribution measuring diagram of the 200W Hall thruster shown in FIG. 5.
The thrust density distribution of the Hall thruster at different positions obtained through the steps is applied to performance evaluation and optimization during actual operation of the Hall thruster, so that the space orbit is maintained at a correct position, the deviation is corrected in time, and the control of the spacecraft is influenced very importantly.

Claims (1)

1. The Hall thruster thrust density distribution measurement is characterized in that: comprising the following measuring steps of the method,
step one, acquiring a zero potential interface of a plume region of a Hall thruster
Diagnosing the potential of the plume region by adopting a Langmuir single probe to obtain a measurement position
Figure FDA0003529100020000018
The abscissa of the inflection point of the volt-ampere characteristic curve is the space potential V of the plasma in the plume regionp0；
The Langmuir probe is installed on a stepping motor, and the stepping motor is controlled to enable the Langmuir probe to move and diagnose in a plume region of the Hall thruster, so that the potential distribution of the plume region of the Hall thruster is obtained
Figure FDA0003529100020000011
Extracting a zero potential surface of the plume field as an interface S1 on the basis;
step two, diagnosis of ion density on the interface S1
And diagnosing the plasma density on the interface S1 by using a Faraday probe, and calculating according to the measured current value to obtain the plasma density, wherein the calculation formula is as follows:
Figure FDA0003529100020000012
In the formula (I), the compound is shown in the specification,
Figure FDA0003529100020000013
as a Faraday probe at interface S1
Figure FDA0003529100020000014
The test current obtained at the location, q is the ionic charge, AfFor the effective collection area of the faraday probe,
Figure FDA0003529100020000015
is composed of
Figure FDA0003529100020000016
Ion density of sites, miIs the mass of the ion;
further, the method can be obtained as follows:
Figure FDA0003529100020000017
step three, ion energy diagnosis on the interface S1
Diagnosing the ion energy on the interface S1 by adopting a retardation analyzer to obtain ion energy distribution curves of different energy levels on the interface S1 of the Hall thruster; the relationship between the current obtained by the collector of the retardation potential analyzer and the ion velocity distribution is as follows:
Figure FDA0003529100020000021
in the formula (I), the compound is shown in the specification,
Figure FDA0003529100020000022
test Current obtained for the collector of the retardation potential Analyzer, ArThe area of a collector of the retarding potential analyzer is shown, q is the charge quantity of ions,
Figure FDA0003529100020000023
is ion density, U is blocking gate voltage, viWhich is the velocity of the ions, is,
Figure FDA0003529100020000024
is an ion velocity distribution function;
the relationship between ion velocity and gate voltage is:
Figure FDA0003529100020000025
the function that converts the collector current to voltage U according to equation (4) yields:
Figure FDA0003529100020000026
in the formula (I), the compound is shown in the specification,
Figure FDA0003529100020000027
as a function of ion energy distribution;
differentiating U on two sides of the equation of formula (5) respectively to obtain:
Figure FDA0003529100020000028
and further obtaining an ion energy distribution function:
Figure FDA0003529100020000029
step four, correcting the ion energy distribution on the interface S1
To characterize the extent of the loss of the retardation analyzer for the received ion current, an ion loss coefficient K is defined, which is expressed as follows:
Figure FDA00035291000200000210
in the formula (I), the compound is shown in the specification,
Figure FDA0003529100020000031
for the Faraday probe in place
Figure FDA0003529100020000032
The current of the received ions is detected,
Figure FDA0003529100020000033
the ion current received by the blocking potential analyzer under the condition of blocking grid suspension voltage at the same position;
the corrected ion energy distribution function is obtained as:
Figure FDA0003529100020000034
and solving the average energy of the ions according to the modified ion energy distribution function:
Figure FDA0003529100020000035
and obtaining the average velocity of the ions:
Figure FDA0003529100020000036
step five, obtaining the thrust density distribution of the Hall thruster
At the interface S1
Figure FDA0003529100020000037
At a position where the ion flow with a mean velocity v passes through the infinitesimal area
Figure FDA0003529100020000038
The generated axial thrust satisfies the following formula:
Figure FDA0003529100020000039
in the formula, theta represents an included angle between the ion movement speed and the axial direction of the thruster, and beta represents
Figure FDA00035291000200000310
An included angle is formed between the normal direction and the axial direction of the thruster;
defining the axial thrust magnitude in unit area as thrust density to obtain the axial thrust magnitude on a boundary surface S1
Figure FDA00035291000200000311
The thrust density at the location is:
Figure FDA00035291000200000312
and controlling the stepping motor to move to obtain plasma density and average speed diagnostic parameters on the interface S1 so as to obtain the thrust density distribution of the Hall thruster.
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CN115682919A (en) * 2022-10-28 2023-02-03 哈尔滨工业大学 Hall thruster thrust vector eccentricity calculation method based on curved surface integration
CN115790932A (en) * 2022-11-07 2023-03-14 哈尔滨工业大学 On-orbit thrust calculation method and system for plasma Hall effect thruster
CN117425259A (en) * 2023-12-19 2024-01-19 哈尔滨工业大学 Device and method for measuring spatial distribution of propeller plume ion energy spectrum
CN117451238A (en) * 2023-12-19 2024-01-26 哈尔滨工业大学 On-orbit optical detection method and device for propeller thrust fluctuation based on neural network
CN118067398A (en) * 2024-04-19 2024-05-24 哈尔滨工业大学 On-orbit optical monitoring method for thrust distribution of multichannel Hall thruster

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Publication number Priority date Publication date Assignee Title
CN115682919A (en) * 2022-10-28 2023-02-03 哈尔滨工业大学 Hall thruster thrust vector eccentricity calculation method based on curved surface integration
CN115682919B (en) * 2022-10-28 2023-08-11 哈尔滨工业大学 Hall thruster thrust vector eccentricity calculation method based on curved surface integration
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CN115790932B (en) * 2022-11-07 2024-03-29 哈尔滨工业大学 Method and system for calculating on-orbit thrust of plasma Hall effect thruster
CN117425259A (en) * 2023-12-19 2024-01-19 哈尔滨工业大学 Device and method for measuring spatial distribution of propeller plume ion energy spectrum
CN117451238A (en) * 2023-12-19 2024-01-26 哈尔滨工业大学 On-orbit optical detection method and device for propeller thrust fluctuation based on neural network
CN117451238B (en) * 2023-12-19 2024-04-09 哈尔滨工业大学 On-orbit optical detection method and device for propeller thrust fluctuation based on neural network
CN117425259B (en) * 2023-12-19 2024-04-23 哈尔滨工业大学 Device and method for measuring spatial distribution of propeller plume ion energy spectrum
CN118067398A (en) * 2024-04-19 2024-05-24 哈尔滨工业大学 On-orbit optical monitoring method for thrust distribution of multichannel Hall thruster

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