CN115790932B - Method and system for calculating on-orbit thrust of plasma Hall effect thruster - Google Patents
Method and system for calculating on-orbit thrust of plasma Hall effect thruster Download PDFInfo
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Abstract
The invention relates to a method and a system for calculating on-orbit thrust of a plasma Hall effect thruster, wherein firstly, a magnetic sensor array is utilized to capture a magnetic field induced by Hall drift current in a channel of the plasma Hall effect thruster in a discharging process; then calculating the Hall drift current density in the channel by using a static magnetic field inversion method according to the magnetic field; and finally, calculating the on-orbit thrust of the plasma Hall effect thruster by using an on-orbit thrust calculation model according to the Hall drift current density and the radial component of the magnetic field under the given exciting current of the fixed design parameters of the thruster. The method can measure the second-level magnetic field intensity by utilizing the magnetic sensor array, and calculate the on-orbit thrust according to the second-level magnetic field intensity, so as to obtain real-time on-orbit thrust, and avoid the defect of poor evaluation instantaneity caused by the fact that the existing on-orbit thrust evaluation method needs to combine satellite orbit change information or angular displacement change information to perform thrust evaluation.
Description
Technical Field
The invention relates to the field of Hall effect thrusters, in particular to a method and a system for calculating on-orbit thrust of a plasma Hall effect thruster.
Background
The plasma Hall effect thruster is a functional conversion device which converts electric energy into working medium kinetic energy by utilizing the combined action of an electric field and a magnetic field. Is one of the most used electric thrusters in space propulsion. Further development of hall effect thrusters relies on precise regulation of the thrust control system, and on-orbit assessment of thrust is a precondition for optimizing the precise regulation of the hall effect thruster thrust control system. Therefore, on-orbit thrust assessment is one of the focus of research on plasma hall effect thrusters.
Currently common on-orbit assessment methods can be divided into two categories: orbit estimation method and attitude estimation method. The orbit estimation method establishes a relation between the thrust information of the thruster which can not be directly measured and the measurable satellite orbit information by using a global satellite navigation system, and calculates the thrust of the thruster through the satellite orbit change information. The attitude estimation rule is a method for measuring angular motion data of satellites by using a high-precision attitude sensing device arranged on the satellites, and further calculating thrust. However, both of these conventional methods require calculation of thrust by displacement change information before and after satellite orbit or attitude adjustment, and thus do not have real-time performance.
Disclosure of Invention
The invention aims to provide an on-orbit thrust calculation method and system for a plasma Hall effect thruster, which solve the problem of poor real-time performance of the conventional on-orbit thrust calculation method according to the basic principle that Hall drift current interacts with an in-channel radial magnetic field to generate thrust.
In order to achieve the above object, the present invention provides the following solutions:
an on-orbit thrust calculation method of a plasma Hall effect thruster, comprising:
acquiring the magnetic field intensity induced by the Hall drift current in a discharge channel of the plasma Hall effect thruster in the discharge process; the magnetic field intensity induced by the Hall drift current is captured by a magnetic sensor array;
calculating the Hall drift current density in the discharge channel by using a static magnetic field inversion method according to the magnetic field intensity;
calculating the on-orbit thrust of the plasma Hall effect thruster by using an on-orbit thrust calculation model according to the radial component distribution of a magnetic field and the Hall drift current density distribution of the fixed design parameters of the thruster under the given exciting current; the on-orbit thrust calculation model is used for expressing the relation among Hall drift current density, radial magnetic field strength under given excitation current and on-orbit thrust.
Optionally, the matrix equation of the static magnetic field inversion method is:
f(J H )＝min{||AJ H -B|| 2 +λ{||L rr J H || 2 +2||L rz J H || 2 +||L zz J H || 2 }}
wherein J is H The column vector is obtained after spreading and tiling the Hall drift current density distribution j (r, z); b is a vector constructed by magnetic field intensity at a plurality of sensor measuring point positions in a Hall drift current induced magnetic field; a is a green matrix which relates current density distribution to magnetic field intensity of each sensor measuring point; the green matrix is determined through a calibration experiment; lambda is the control regularization term { ||L rr J H || 2 +2||L rz J H || 2 +||L zz J H || 2 Relative to the residual term AJ H -B|| 2 Regularization parameters of the weights; r is the radial position coordinate in the discharge channel of the plasma Hall effect thruster; z represents the axial position coordinates within the plasma hall effect thruster discharge channel; l (L) rr Representing a second derivative operator obtained by twice deriving the radial position in a discharge channel of the plasma Hall effect thruster; l (L) zz Representing a second derivative operator obtained by twice deriving the axial position in a discharge channel of the plasma Hall effect thruster; l (L) rz And the second derivative operator is obtained by carrying out one-time derivation on the radial position in the discharge channel of the plasma Hall effect thruster and carrying out one-time derivation on the axial position in the discharge channel of the plasma Hall effect thruster.
Optionally, the static magnetic field inversion method considers non-negative constraint and zero boundary constraint;
the non-negative constraint means that the azimuthal current of the acceleration channel of the plasma Hall effect thruster flows along the same azimuthal direction;
the zero boundary constraint means that the Hall drift current density on the boundary of a discharge chamber of the plasma Hall effect thruster is zero; the plasma Hall effect thruster discharge chamber boundary comprises a plasma Hall effect thruster discharge channel wall surface and a plasma Hall effect thruster anode plane.
Considering the two constraints mentioned above, a useful stable solution to the matrix equation can be obtained.
Optionally, the formula of the on-orbit thrust calculation model includes:
T＝∫ V |J H B r |dV
wherein T is on-orbit thrust; j (J) H The drift current density is Hall drift current density, and V is the volume of a discharge channel of the plasma Hall effect thruster; b (B) r For a radial component of the magnetic field at a given excitation current, the magnetic field is measured by a Gaussian meter at a given excitation current for a fixed design parameter of the thruster.
Optionally, each magnetic sensor in the magnetic sensor array is located outside the plume region, and the magnetic field gradient is greater than the region of the set threshold.
The magnetic sensor is arranged outside the plume region, and the magnetic field gradient is larger than the region with the set threshold value, so that the measurement accuracy of the Hall drift current induced magnetic field can be improved.
Optionally, the arrangement of the magnetic sensors in the magnetic sensor array includes a radial arrangement and an axial arrangement.
Optionally, the magnetic sensor array uses tunnel magnetoresistance TMR as the sensing element.
The graphite cover arranged outside the circuit board can protect the magnetic sensor from being influenced by plasma sputtering near the outlet plane of the thruster, and meanwhile, the graphite also plays a role in heat dissipation.
The invention also provides an on-orbit thrust computing system of the plasma Hall effect thruster, which comprises:
the magnetic field capturing module is used for acquiring the magnetic field intensity induced by the Hall drift current in the discharge channel of the plasma Hall effect thruster in the discharge process; the magnetic field intensity induced by the Hall drift current is captured by a magnetic sensor array;
the Hall drift current density calculation module is used for calculating the Hall drift current density in the discharge channel by using a static magnetic field inversion method according to the intensity of the Hall drift current induced magnetic field;
the on-orbit thrust calculation module is used for calculating the on-orbit thrust of the plasma Hall effect thruster by using an on-orbit thrust calculation model according to the radial magnetic field component under the given excitation current and the Hall drift current density in the fixed design parameters of the thruster; the on-orbit thrust calculation model is used for expressing the relationship among Hall drift current density, radial magnetic field components under given excitation current and on-orbit thrust.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
the invention provides a method and a system for calculating on-orbit thrust of a plasma Hall effect thruster, wherein firstly, a magnetic sensor array is utilized to capture a magnetic field induced by Hall drift current in a channel of the plasma Hall effect thruster in a discharging process; then calculating the density of the Hall drift current in the channel by using a static magnetic field inversion method according to the magnetic field induced by the Hall drift current; and finally, calculating the on-orbit thrust of the plasma Hall effect thruster by using an on-orbit thrust calculation model according to the radial magnetic field component under the given excitation current and the Hall drift current density in the fixed design parameters of the thruster. The method can measure the second-level magnetic field intensity by utilizing the magnetic sensor array, and calculate the on-orbit thrust according to the second-level magnetic field intensity, so as to obtain real-time on-orbit thrust, and avoid the defect of poor evaluation instantaneity caused by the fact that the existing on-orbit thrust evaluation method needs to combine satellite orbit change information or angular displacement change information to perform thrust evaluation.
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In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flowchart of an on-orbit thrust calculation method of a plasma Hall effect thruster provided in embodiment 1 of the present invention;
fig. 2 is a schematic diagram of an on-orbit thrust calculation method of a plasma hall effect thruster provided in embodiment 1 of the present invention;
FIG. 3 is a graph showing the radial component of the magnetic field at a given excitation current in the fixed design parameters of the thruster in the discharge channel of the plasma Hall effect thruster provided by example 1 of the present invention;
FIG. 4 is a contour diagram of the density distribution of the Hall drift current provided in embodiment 1 of the present invention;
fig. 5 is a block diagram of an on-orbit thrust computing system of a plasma hall effect thruster provided in embodiment 2 of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide an on-orbit thrust calculation method and system for a plasma Hall effect thruster, which solve the problem of poor real-time performance of the conventional on-orbit thrust calculation method according to the basic principle that Hall drift current interacts with an in-channel radial magnetic field to generate thrust.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
Example 1
The present embodiment provides a method for calculating an on-orbit thrust of a plasma hall effect thruster, referring to fig. 1 and 2, including:
s1, acquiring the magnetic field intensity induced by Hall drift current in a discharge channel of a plasma Hall effect thruster in a discharge process; the magnetic field strength induced by the hall drift current is captured by the magnetic sensor array.
Optionally, the magnetic sensor array uses tunnel magnetoresistance TMR as the sensing element.
Specifically, the magnetic induction element may be a TMR2701 chip of Jiangsu multidimensional technology company.
In the step S1, a magnetic sensor array taking a TMR2701 chip of Jiangsu multi-dimensional science and technology company as a magnetic induction element is used for capturing a magnetic field induced by Hall drift current in a channel of a plasma Hall effect thruster in a discharging process, a voltage signal on a sensor is captured through a data acquisition card of the model USB-5817 of the Ministry of China, science and technology company, and then magnetic field information of a corresponding position is obtained through an upper computer program written by Labview. The data acquisition card of the USB-5817 model is arranged outside the vacuum tank where the Hall effect thruster is arranged.
Optionally, each magnetic sensor in the magnetic sensor array is located outside the plume region, and the magnetic field gradient is greater than the region of the set threshold.
It is further noted that the magnetic sensor setting position should conform to the basic principle of the normal operation condition of the magnetic sensor, for example, the temperature of the magnetic sensor setting position should satisfy the temperature of the normal operation condition of the magnetic sensor, i.e. be lower than 80 ℃.
Optionally, the arrangement of the magnetic sensors in the magnetic sensor array includes a radial arrangement and an axial arrangement.
According to the setting conditions of the magnetic sensors, 8 magnetic sensor positions are set through numerical simulation in the embodiment, please refer to fig. 2, wherein 4 radial sensors measure the axial component of the magnetic field, and another 4 axial sensors measure the radial component of the magnetic field; the magnetic sensor array is integrally placed in the vacuum tank near the outlet plane of the thruster. The specific placement positions of the 8 magnetic sensors are as follows: setting an abscissa axis in a plane where the outer magnetic pole piece is located by taking a point on an intersection line of the outer wall of the channel and the outer magnetic pole piece as a zero point, and setting an ordinate axis in an extension plane of the outer wall of the channel, wherein the position coordinates of the 4 axial sensors are (50, 10), (30, 20), (50, 20), (45, 30), and the position coordinates of the 4 radial sensors are (20, 10), (30, 10), (40, 20);
s2, calculating the density of the Hall drift current in the discharge channel by using a static magnetic field inversion method according to the intensity of the magnetic field induced by the Hall drift current.
As an alternative embodiment, the matrix equation of the static magnetic field inversion method is:
f(J H )＝min{||AJ H -B|| 2 +λ{||L rr J H || 2 +2||L rz J H || 2 +||L zz J H || 2 }}
wherein J is H The column vector is obtained after spreading and tiling the Hall drift current density distribution j (r, z); b is a vector constructed by magnetic field intensity at a plurality of sensor measuring point positions in a Hall drift current induced magnetic field; a is a green matrix which relates current density distribution to magnetic field intensity of each sensor measuring point; the green matrix is determined through a calibration experiment; lambda is the control regularization term { ||L rr J H || 2 +2||L rz J H || 2 +||L zz J H || 2 Relative to the residual term AJ H -B|| 2 Regularization parameters of the weights; r is the radial position coordinate in the discharge channel of the plasma Hall effect thruster; z represents the axial position coordinates within the plasma hall effect thruster discharge channel; l (L) rr Representing a second derivative operator obtained by twice deriving the radial position in a discharge channel of the plasma Hall effect thruster; l (L) zz Representing a second derivative operator L obtained by twice deriving the axial position in a discharge channel of a plasma Hall effect thruster rz And the second derivative operator is obtained by carrying out one-time derivation on the radial position in the discharge channel of the plasma Hall effect thruster and carrying out one-time derivation on the axial position in the discharge channel of the plasma Hall effect thruster.
The magnetic field information captured by the magnetic sensor array and the digital acquisition device is used as a known quantity, the known magnetic field information is used for solving the distribution characteristic of the Hall drift current in the channel in the discharging process of the plasma Hall effect thruster,the magnetostatic inversion problem can be expressed as a matrix equation: f (J) H )＝min||AJ H -B|| 2 . Considering the discontinuity of the solution, adopting Tikhonov regularization to carry out smoothing treatment on the problem so as to obtain a stable and applicable Hall drift current density distribution solution; the equation to be solved of the magnetostatic inversion problem after the processing becomes f (J H )＝min{||AJ H -B|| 2 +λ{||L rr J H || 2 +2||L rz J H || 2 +||L zz J H || 2 }}。
After the inversion problem is smoothed by using the regularization constraint method, two additional constraints, namely a non-negative constraint and a zero boundary constraint, are added to obtain a useful stable solution.
As an alternative embodiment, the static magnetic field inversion method considers non-negative constraints and zero boundary constraints;
the non-negative constraint means that the azimuthal current of the acceleration channel of the plasma Hall effect thruster flows along the same azimuthal direction;
the zero boundary constraint means that the Hall drift current density on the boundary of a discharge chamber of the plasma Hall effect thruster is zero; the plasma Hall effect thruster discharge chamber boundary comprises a plasma Hall effect thruster discharge channel wall surface and a plasma Hall effect thruster anode plane.
When solving the matrix equation of the static magnetic field inversion method, firstly, determining a green matrix A for representing mathematical relationship between Hall current density distribution in a discharge channel and magnetic field intensity of each measuring point through calibration. The specific implementation scheme is as follows: copper wires with phi of 1mm are wound into 5 turns, so that the copper wires are distributed on the same axial plane in a thruster channel at equal intervals along the radial direction, the minimum diameter is 75mm, and the maximum diameter is 95mm, and therefore Hall drift current in the channel when the thruster operates is simulated; when calibration is started, firstly, the inner coil of the thruster is electrified by 2.4A, the outer coil is electrified by 1.4A, the power supply voltage of the sensor is 1.4V, and the background magnetic field B generated by the thruster at each sensor position at the moment is recorded b The method comprises the steps of carrying out a first treatment on the surface of the Then the current of 4A is respectively applied to each copper wire, and the record is again madeRecording the magnetic field B at each sensor location w Difference B between them Δ ＝B w -B b Namely, the magnetic field increment at each measuring point position excited by the simulated Hall drift current; then, the lead is moved along the axis of the thruster to the plane of the outlet of the thruster, and the calibration process is repeated, wherein each 5mm distance from the plane 15mm away from the plane of the anode of the thruster is taken as a calibration plane, and the total of 10 axial positions are taken; based on the known Hall drift current at 50 positions in the channel and the magnetic field strength at 8 measuring points in the induced magnetic field, a Green matrix A is obtained 8×50 The specific expression of the matrix is that
Constituent element BΔ (r i ，z j ，S k ) I can be 1,2,3,4,5, and represents 5 radial position coordinates; j may take 1,2,3, … …,10, representing 10 axial position coordinates; k may be 1,2,3, … …,8, representing magnetic sensors at 8 stations.
Next, solving a matrix equation, namely writing a MATLAB script by using a fmincon function to execute the regularization algorithm, wherein the initial value of the current density is given as a zero vector; solution J of Hall drift current density obtained by solving H Is a 50 x 1 column vector which is rearranged in a manner opposite to the stacking of the rows in the green matrix, thus obtaining a contour map of the hall drift current density distribution in the discharge channel. According to the method, in a specific embodiment, when the cathode flow of the Hall thruster is 3sccm, the anode flow is 30sccm, the relative angle of the cathode is 180 degrees, the excitation currents of the inner coil and the outer coil are respectively 2.4A and 1.4A, and the discharge voltage is 300V, the obtained contour diagram of the density distribution of the Hall drift current is shown in FIG. 4.
When measuring the magnetic field intensity of 8 measuring point positions, 8 sensors are respectively connected in series with a passive resistor, all the sensors share the same power bus, and the voltage drop is indirectly measured through the passive resistor; the sensor array power supply is arranged outside the vacuum tank. A graphite cover is arranged outside the circuit board of the magnetic sensor to protect the sensor from plasma sputtering near the outlet plane of the thruster, and meanwhile, graphite also plays a role in heat dissipation.
S3, calculating the on-orbit thrust of the plasma Hall effect thruster by using an on-orbit thrust calculation model according to the radial component of the magnetic field under the given excitation current and the Hall drift current density in the fixed design parameters of the thruster; the on-orbit thrust calculation model is used for expressing the relation among Hall drift current density, radial magnetic field intensity and on-orbit thrust.
In a specific embodiment, when the excitation currents of the inner coil and the outer coil are respectively 2.4A and 1.4A, the radial magnetic field component distribution under the fixed design parameters of the thruster is measured by using a Gaussian meter, and is shown in FIG. 3.
The embodiment realizes on-orbit estimation of the thrust of the plasma Hall effect thruster by combining the basic principle that the Hall drift current interacts with the radial magnetic field to generate the thrust, and the principle corresponds to an on-orbit thrust calculation model.
As an alternative embodiment, the formula of the on-orbit thrust computation model includes:
T＝∫ V |J H B r |dV
wherein T is on-orbit thrust; j (J) H The drift current density of the Hall (i.e. the solution of the matrix equation) is V, which is the volume of a discharge channel of the plasma Hall effect thruster; b (B) r The radial component of the magnetic field under a given excitation current is measured by a Gaussian meter under the given excitation current of the fixed design parameters of the thruster.
In a specific embodiment, when the cathode flow of the Hall thruster is 3sccm, the anode flow is 30sccm, the relative angle of the cathode is 180 degrees, the excitation currents of the inner coil and the outer coil are 2.4A and 1.4A respectively, and the discharge voltage is 300V, the calculated thrust value is 23.10mN; at this time, the thrust value measured with the three-wire torsional pendulum type thrust test bench was 22.45mN, and the relative error was only 2.90%.
The method can measure the second-level magnetic field intensity by utilizing the magnetic sensor array, and calculate the on-orbit thrust according to the second-level magnetic field intensity, so as to obtain real-time on-orbit thrust, and avoid the defect of poor evaluation instantaneity caused by the fact that the existing on-orbit thrust evaluation method needs to combine satellite orbit change information or angular displacement change information to perform thrust evaluation.
Example 2
The present embodiment provides an on-orbit thrust computing system of a plasma hall effect thruster, please refer to fig. 5, comprising:
the magnetic field capturing module M1 is used for acquiring the magnetic field intensity induced by the Hall drift current in the discharge channel of the plasma Hall effect thruster in the discharge process; the magnetic field intensity induced by the Hall drift current is captured by a magnetic sensor array;
the Hall drift current density calculation module M2 is used for calculating the Hall drift current density in the discharge channel by using a static magnetic field inversion method according to the magnetic field intensity;
the on-orbit thrust calculation module M3 is used for calculating the on-orbit thrust of the plasma Hall effect thruster by using an on-orbit thrust calculation model according to the radial component of the magnetic field under the excitation current and the Hall drift current density given by the fixed design parameters of the thruster; the on-orbit thrust calculation model is used for expressing the relationship among Hall drift current density, radial components of a magnetic field under a given excitation current and on-orbit thrust.
In the present specification, each embodiment is described in a progressive manner, and each embodiment is mainly described in a different point from other embodiments, and identical and similar parts between the embodiments are all enough to refer to each other. For the system disclosed in the embodiment, since it corresponds to the method disclosed in the embodiment, the description is relatively simple, and the relevant points refer to the description of the method section.
The principles and embodiments of the present invention have been described herein with reference to specific examples, the description of which is intended only to assist in understanding the methods of the present invention and the core ideas thereof; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (8)
1. An on-orbit thrust calculation method for a plasma hall effect thruster, comprising the steps of:
acquiring the magnetic field intensity induced by the Hall drift current in a discharge channel of the plasma Hall effect thruster in the discharge process; the magnetic field strength is captured by a magnetic sensor array;
calculating the Hall drift current density in the discharge channel by using a static magnetic field inversion method according to the magnetic field intensity;
according to the Hall drift current density and the fixed design parameters of the thruster, the radial component of the magnetic field under the given exciting current is calculated, and the on-orbit thrust of the plasma Hall effect thruster is calculated by using an on-orbit thrust calculation model; the on-orbit thrust calculation model is used for expressing the relationship among the Hall drift current density, the radial component of the magnetic field under the given exciting current and the on-orbit thrust.
2. The method of claim 1, wherein the matrix equation for the static magnetic field inversion method is:
wherein,to distribute the Hall drift current density>Spreading the column vector obtained after tiling; />The vector is formed by the magnetic field intensity at the positions of a plurality of sensor measuring points in the Hall drift current induced magnetic field; />A green matrix for correlating the current density distribution with the magnetic field strength at each sensor site; the green matrix is determined through a calibration experiment; />Is a control regularization term->Relative to residual term->Regularization parameters of the weights; r is the radial position coordinate in the discharge channel of the plasma Hall effect thruster; z represents the axial position coordinates within the plasma hall effect thruster discharge channel; l (L) rr Representing a second derivative operator obtained by twice deriving the radial position in a discharge channel of the plasma Hall effect thruster; l (L) zz Representing a second derivative operator obtained by twice deriving the axial position in a discharge channel of the plasma Hall effect thruster; l (L) rz And the second derivative operator is obtained by carrying out one-time derivation on the radial position in the discharge channel of the plasma Hall effect thruster and carrying out one-time derivation on the axial position in the discharge channel of the plasma Hall effect thruster.
3. The method of claim 2, wherein the static magnetic field inversion method considers non-negative constraints and zero boundary constraints;
the non-negative constraint means that the azimuthal current of the acceleration channel of the plasma Hall effect thruster flows along the same azimuthal direction;
the zero boundary constraint means that the Hall drift current density on the boundary of a discharge chamber of the plasma Hall effect thruster is zero; the plasma Hall effect thruster discharge chamber boundary comprises a plasma Hall effect thruster discharge channel wall surface and a plasma Hall effect thruster anode plane.
4. The method of claim 1, wherein the formulation of the on-orbit thrust calculation model comprises:
wherein T is on-orbit thrust;for Hall drift current density +.>The volume of a discharge channel of the plasma Hall effect thruster; />The radial component of the magnetic field under a given excitation current is measured by a Gaussian meter under the given excitation current of the fixed design parameters of the thruster.
5. The method of claim 1, wherein each magnetic sensor in the array of magnetic sensors is located outside of the plume region and the magnetic field gradient is greater than a set threshold.
6. The method of claim 1, wherein the arrangement of magnetic sensors in the magnetic sensor array comprises a radial arrangement and an axial arrangement.
7. The method of claim 1, wherein the magnetic sensor array has a tunneling magnetoresistance TMR as the sensing element.
8. An on-orbit thrust computing system for a plasma hall effect thruster, comprising:
the magnetic field capturing module is used for acquiring the magnetic field intensity induced by the Hall drift current in the discharge channel of the plasma Hall effect thruster in the discharge process; the magnetic field strength is captured by a magnetic sensor array;
the Hall drift current density calculation module is used for calculating the Hall drift current density in the discharge channel by using a static magnetic field inversion method according to the magnetic field intensity;
the on-orbit thrust calculation module is used for calculating the on-orbit thrust of the plasma Hall effect thruster by using an on-orbit thrust calculation model according to the Hall drift current density and the radial component of the magnetic field under the given exciting current of the fixed design parameters of the thruster; the on-orbit thrust calculation model is used for expressing the relationship among Hall drift current density, radial components of a magnetic field under a given excitation current and on-orbit thrust.
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1012055A1 (en) * | 1982-01-08 | 1983-04-15 | Kudintsev Eduard M | Device for measuring impact parameters of impact-rotating action machines |
| CN105756875A (en) * | 2016-05-12 | 2016-07-13 | 哈尔滨工业大学 | Space debris plasma propeller integrating ionization and acceleration |
| CN110705007A (en) * | 2019-08-16 | 2020-01-17 | 北京航空航天大学 | Efficiency evaluation method of plasma vortex generator |
| CN113465494A (en) * | 2021-06-29 | 2021-10-01 | 哈尔滨工业大学 | Thrust vector eccentricity calculation method for Hall thruster |
| CN114320800A (en) * | 2021-12-28 | 2022-04-12 | 哈尔滨工业大学 | Hall thruster for restraining plume by using magnetic cage and magnetic cage structure adjusting method |
| CN114674474A (en) * | 2022-03-02 | 2022-06-28 | 国科大杭州高等研究院 | Hall thruster thrust density distribution measurement |
-
2022
- 2022-11-07 CN CN202211381292.9A patent/CN115790932B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1012055A1 (en) * | 1982-01-08 | 1983-04-15 | Kudintsev Eduard M | Device for measuring impact parameters of impact-rotating action machines |
| CN105756875A (en) * | 2016-05-12 | 2016-07-13 | 哈尔滨工业大学 | Space debris plasma propeller integrating ionization and acceleration |
| CN110705007A (en) * | 2019-08-16 | 2020-01-17 | 北京航空航天大学 | Efficiency evaluation method of plasma vortex generator |
| CN113465494A (en) * | 2021-06-29 | 2021-10-01 | 哈尔滨工业大学 | Thrust vector eccentricity calculation method for Hall thruster |
| CN114320800A (en) * | 2021-12-28 | 2022-04-12 | 哈尔滨工业大学 | Hall thruster for restraining plume by using magnetic cage and magnetic cage structure adjusting method |
| CN114674474A (en) * | 2022-03-02 | 2022-06-28 | 国科大杭州高等研究院 | Hall thruster thrust density distribution measurement |
Non-Patent Citations (2)
| Title |
|---|
| 磁场强度对霍尔推力器放电特性影响的实验研究;鄂鹏;于达仁;武志文;韩轲;;物理学报;20090415(第04期);第2535-2542页 * |
| 霍尔推力器内放电等离子体数值仿真分析;赵杰;许丽;李建;王坤;王世庆;;真空;20200725(第04期);第54-59页 * |
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