CN115790932A - On-orbit thrust calculation method and system for plasma Hall effect thruster - Google Patents
On-orbit thrust calculation method and system for plasma Hall effect thruster Download PDFInfo
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Abstract
The invention relates to an on-orbit thrust calculation method and a system of a plasma Hall effect thruster, which comprises the following steps of firstly, capturing a magnetic field induced by Hall drift current in a channel of the plasma Hall effect thruster in a discharging process by utilizing a magnetic sensor array; then according to the magnetic field, calculating the Hall drift current density in the channel by using a static magnetic field inversion method; and finally, according to the Hall drift current density and the fixed design parameters of the thruster, giving the radial component of the magnetic field under the excitation current, and calculating the on-orbit thrust of the plasma Hall effect thruster by using an on-orbit thrust calculation model. The magnetic sensor array is utilized to measure the magnetic field intensity of the second level, the on-orbit thrust is calculated according to the magnetic field intensity of the second level, and then the real-time on-orbit thrust is obtained, so that the defect that the evaluation instantaneity is poor due to the fact that the existing on-orbit thrust evaluation method needs to be combined with satellite orbit change information or angular displacement change information to evaluate the thrust is overcome.
Description
Technical Field
The invention relates to the field of Hall effect thrusters, in particular to an on-orbit thrust calculation method and system 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 the Hall effect thruster depends on accurate regulation and control of a thrust control system, and on-orbit evaluation of thrust is a premise for optimizing the accurate regulation and control of the thrust control system of the Hall effect thruster. Therefore, on-orbit thrust evaluation is one of the research focuses of the plasma hall effect thruster.
Currently, the common on-orbit evaluation methods can be divided into two categories: orbit estimation and attitude estimation. The track estimation method establishes a relation between thruster thrust information which cannot be directly measured and measurable satellite track information by using a global satellite navigation system, and calculates the thruster thrust through satellite track change information. The attitude estimation method is a method for measuring angular motion data of a satellite by using a high-precision attitude sensitive device equipped on the satellite and further calculating the thrust. However, both of these conventional methods require calculation of thrust from displacement change information before and after satellite orbital transfer or attitude adjustment, and therefore, do not have real-time performance.
Disclosure of Invention
The invention aims to provide an on-orbit thrust calculation method and an on-orbit thrust calculation system for a plasma Hall effect thruster, which solve the problem of poor real-time performance of the currently common on-orbit thrust calculation method according to the basic principle that the Hall drift current and the radial magnetic field in a channel interact to generate thrust.
In order to achieve the purpose, the invention provides the following scheme:
an on-orbit thrust calculation method of a plasma Hall effect thruster comprises the following steps:
acquiring the magnetic field intensity induced by 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;
according to the magnetic field intensity, calculating the Hall drift current density in a discharge channel by using a static magnetic field inversion method;
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 the magnetic field under the given exciting current and the Hall drift current density distribution 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 strength under given excitation current and on-orbit thrust.
Optionally, the matrix equation of the static magnetic field inversion method is as follows:
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 H Spreading and tiling a Hall drift current density distribution condition j (r, z) to obtain a column vector; b is a vector constructed by magnetic field intensity at the positions of a plurality of sensor measuring points in the Hall drift current induced magnetic field; a is a Green matrix which links current density distribution with magnetic field intensity of each sensor measuring point; the Green matrix is determined by a calibration experiment; λ 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 a radial position coordinate in a discharge channel of the plasma Hall effect thruster; z represents an axial position coordinate in a discharge channel of the plasma Hall effect thruster; l is a radical of an alcohol rr Representing a second derivative operator obtained by performing two derivatives on the radial position in a discharge channel of the plasma Hall effect thruster; l is zz Representing a second derivative operator obtained by carrying out two derivatives on the axial position in the discharge channel of the plasma Hall effect thruster; l is rz Indicating a plasma Hall Effect thruster setAnd performing primary derivation on the radial position in the electric channel and performing primary derivation on the axial position in the discharge channel of the plasma Hall effect thruster to obtain a second derivative operator.
Optionally, the static magnetic field inversion method considers a nonnegativity constraint and a zero boundary constraint;
the non-negative constraint means that the azimuth current of the accelerating channel of the plasma Hall effect thruster flows along the same azimuth direction;
the zero boundary constraint means that the Hall drift current density on the boundary of the discharge chamber of the plasma Hall effect thruster is zero; the boundary of the discharge chamber of the plasma Hall effect thruster comprises the wall surface of a discharge channel of the plasma Hall effect thruster and the anode plane of the plasma Hall effect thruster.
Taking into account the two constraints mentioned above, a useful stable solution of 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 is a unit of H The Hall drift current density is adopted, and V is the volume of a discharge channel of the plasma Hall effect thruster; b is r The magnetic field is measured by a gaussmeter under the condition that the fixed design parameters of the thruster set the exciting current.
Optionally, each magnetic sensor in the magnetic sensor array is located outside the plume region, and the magnetic field gradient is greater than a set threshold.
The magnetic sensor is arranged outside the plume region, and the measurement accuracy of the Hall drift current induced magnetic field can be improved in the region where the magnetic field gradient is larger than a set threshold value.
Optionally, the magnetic sensors in the magnetic sensor array are arranged in a radial direction and an axial direction.
Optionally, the magnetic sensor array uses a tunneling magneto-resistance TMR as a sensing element.
The graphite cover arranged outside the circuit board can protect the magnetic sensor from being influenced by plasma sputtering near the exit plane of the thruster, and meanwhile, the graphite also plays a role in heat dissipation.
The invention also provides an on-orbit thrust calculation 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 discharging 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 Hall drift current induced magnetic field strength;
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 and the Hall drift current density under the given exciting current in the fixed design parameters of the thruster; the on-rail thrust force calculation model is used for representing the relation among the Hall drift current density, the radial magnetic field component under the given excitation current and the on-rail thrust force.
According to the specific embodiment provided by the invention, the invention discloses the following technical effects:
the invention provides an on-orbit thrust calculation method and system of a plasma Hall effect thruster, which comprises the following steps of firstly, capturing a magnetic field induced by Hall drift current in a channel of the plasma Hall effect thruster in a discharging process by utilizing a magnetic sensor array; then according to the magnetic field induced by the Hall drift current, calculating the Hall drift current density in the channel by using a static magnetic field inversion method; 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 and the Hall drift current density under the given exciting current in the fixed design parameters of the thruster. The method can measure the magnetic field intensity of the second level by using the magnetic sensing array, and performs on-orbit thrust calculation according to the magnetic field intensity of the second level, so as to obtain real-time on-orbit thrust, thereby avoiding the defect of poor evaluation real-time performance caused by the fact that the existing on-orbit thrust evaluation method needs to combine satellite orbit change information or angular displacement change information for thrust evaluation.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings 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 it is obvious for those skilled in the art to obtain other drawings without creative efforts.
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 distribution diagram of a magnetic field radial component at a given excitation current in a fixed design parameter of a thruster in a discharge channel of a plasma hall effect thruster provided in embodiment 1 of the present invention;
fig. 4 is a contour diagram of hall drift current density distribution provided in embodiment 1 of the present invention;
fig. 5 is a structural diagram of an on-orbit thrust calculation system of a plasma hall effect thruster provided in embodiment 2 of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention aims to provide an on-orbit thrust calculation method and an on-orbit thrust calculation system for a plasma Hall effect thruster, which solve the problem of poor real-time performance of the currently common on-orbit thrust calculation method according to the basic principle that the Hall drift current and the radial magnetic field in a channel interact to generate thrust.
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in further detail below.
Example 1
The embodiment provides an on-orbit thrust calculation method of a plasma hall effect thruster, please refer to fig. 1 and 2, which includes:
s1, acquiring the magnetic field intensity induced by Hall drift current in a discharge channel of a plasma Hall effect thruster in the discharge process; the magnetic field strength induced by the hall drift current is captured by a magnetic sensor array.
Optionally, the magnetic sensor array uses a tunneling magneto-resistance TMR as a sensing element.
Specifically, the magnetic sensor element may be a TMR2701 chip of the multi-dimensional technologies of jiangsu.
In the step S1, a magnetic sensor array using a TMR2701 chip of the multi-dimensional science and technology company of Jiangsu as a magnetic induction element is used to capture a magnetic field induced by a hall drift current in a channel of a plasma hall effect thruster in the discharging process, a voltage signal on the sensor is captured by a data acquisition card of the model USB-5817 of the research science and technology (China) Limited company, and magnetic field information of a corresponding position is obtained by an upper computer program written by Labview. A data acquisition card of a USB-5817 model is placed outside a vacuum tank where the Hall effect thruster is located.
Optionally, each magnetic sensor in the magnetic sensor array is located outside the plume region, and the magnetic field gradient is greater than a set threshold.
It should also be noted that the magnetic sensor installation position should comply with the basic principle of the normal operating conditions of the magnetic sensor, for example, the temperature of the magnetic sensor installation position should meet the temperature of the normal operating conditions of the magnetic sensor, i.e., be lower than 80 ℃.
Optionally, the arrangement manner of the magnetic sensors in the magnetic sensor array includes radial arrangement and axial arrangement.
According to the setting conditions of the magnetic sensors, through numerical simulation, the present embodiment sets 8 magnetic sensor positions, please refer to fig. 2, in which 4 radial sensors measure the axial component of the magnetic field, and the other 4 axial sensors measure the radial component of the magnetic field; the magnetic sensor array is integrally close to the plane of the outlet of the thruster and is placed in a vacuum tank. Specific placement positions of the 8 magnetic sensors are as follows: taking a point on an intersection line of the outer wall of the channel and the outer magnetic pole piece as a zero point, setting an abscissa axis in a plane where the outer magnetic pole piece is located, and setting an ordinate axis in an extension plane of the outer wall of the channel, so that 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);
and S2, calculating the Hall drift current density in the discharge channel by using a static magnetic field inversion method according to the magnetic field intensity 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 H Spreading and tiling a Hall drift current density distribution condition j (r, z) to obtain a column vector; b is a vector constructed by the magnetic field intensity at the positions of a plurality of sensor measuring points in the Hall drift current induced magnetic field; a is a Green matrix which links current density distribution with magnetic field intensity of each sensor measuring point; the Green matrix is determined by a calibration experiment; λ 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 a radial position coordinate in a discharge channel of the plasma Hall effect thruster; z represents an axial position coordinate in a discharge channel of the plasma Hall effect thruster; l is rr Representing a second derivative operator obtained by carrying out two derivatives on the radial position in the discharge channel of the plasma Hall effect thruster; l is zz Represents a second derivative operator L obtained by carrying out two derivatives on the axial position in the discharge channel of the plasma Hall effect thruster rz And the second derivative operator is obtained by performing first derivation on the radial position in the discharge channel of the plasma Hall effect thruster and performing first derivation on the axial position in the discharge channel of the plasma Hall effect thruster.
It should be noted that, magnetic field information captured by the magnetic sensor array and the digital acquisition device is a known quantity, and the hall drift current distribution characteristic in the channel during the discharge process of the plasma hall effect thruster is solved through the known magnetic field information, and the magnetostatic inverse problem can be expressed as a matrix equation: f (J) H )＝min||AJ H -B|| 2 . In consideration of the discontinuity of the solution, smoothing the problem by using Tikhonov regularization to obtain a stable and applicable Hall drift current density distribution solution; the equation to be solved for the magnetostatic inversion problem becomes f (J) after processing H )＝min{||AJ H -B|| 2 +λ{||L rr J H || 2 +2||L rz J H || 2 +||L zz J H || 2 }}。
After smoothing the inverse problem with the regularization constraint method, two additional constraints, namely a non-negativity constraint and a zero boundary constraint, need to be added in order to obtain a useful stable solution.
As an alternative embodiment, the static magnetic field inversion method takes into account non-negativity constraints and zero boundary constraints;
the non-negative constraint means that the azimuth current of the acceleration channel of the plasma Hall effect thruster flows along the same azimuth direction;
the zero boundary constraint means that the Hall drift current density on the boundary of the discharge chamber of the plasma Hall effect thruster is zero; the boundary of the discharge chamber of the plasma Hall effect thruster comprises the wall surface of a discharge channel of the plasma Hall effect thruster and the anode plane of the plasma Hall effect thruster.
When solving the matrix equation of the static magnetic field inversion method, firstly, the method needs to be carried outAnd determining a Green matrix A representing the mathematical relationship between the Hall current density distribution in the discharge channel and the magnetic field intensity of each measuring point through calibration. The specific implementation scheme is as follows: winding copper wires with the diameter of phi 1mm into 5 turns, and enabling the copper wires to be radially and equidistantly distributed on the same axial plane in a thruster channel, wherein the minimum diameter is 75mm, and the maximum diameter is 95mm, so that Hall drift current in the channel when the thruster runs 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 (ii) a Then 4A of current is applied to each copper wire, and the magnetic field B at each sensor position is recorded again w The difference B between them Δ ＝B w -B b The magnetic field increment at each measuring point position excited by the simulated Hall drift current is obtained; then moving the wire to the exit plane of the thruster along the axis of the thruster and repeating the calibration process, and taking a calibration plane at intervals of 5mm from the plane 15mm away from the anode plane of the thruster, wherein the total number of the calibration planes is 10; according to the Hall drift currents with known magnitudes at 50 positions in the channel and the magnetic field strengths at 8 measuring points in the induction magnetic field, a Green matrix A is obtained 8×50 The specific expression of the matrix is
Constituent element B.DELTA.r i ，z j ，S k ) Wherein i can take 1,2,3,4,5 to represent 5 radial position coordinates; j may take 1,2,3, \8230; \ 8230;, 10, representing 10 axial position coordinates; k can take 1,2,3, \8230;, 8, representing magnetic sensors at 8 measurement points.
Solving a matrix equation, writing an MATLAB script by utilizing an fmincon function to execute the regularization algorithm, and assigning an initial value of current density as a zero vector; solving the solution J of the obtained Hall drift current density H Is a 50 x 1 column vector that is rearranged, aligned, and stacked with rows in a green matrixIn contrast, a contour diagram of the hall drift current density distribution in the discharge channel is thus obtained. According to the method, in the specific embodiment, when the cathode flow rate of the Hall thruster is 3sccm, the anode flow rate is 30sccm, the cathode relative angle is 180 degrees, the exciting currents of the inner coil and the outer coil are respectively 2.4A and 1.4A, and the discharge voltage is 300V, the contour diagram of the Hall drift current density distribution is obtained as shown in FIG. 4.
When the magnetic field intensity of 8 measuring point positions is measured, 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 power supply of the sensor array is arranged outside the vacuum tank. A graphite cover is arranged outside a circuit board of the magnetic sensor to protect the sensor from being influenced by plasma sputtering near the exit 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 exciting current and the Hall drift current density in the fixed design parameters of the thruster; the on-orbit thrust calculation model is used for representing the relation between the Hall drift current density, the radial magnetic field strength and the on-orbit thrust.
In a specific embodiment, when the exciting currents of the inner and outer coils are respectively 2.4A and 1.4A, the distribution of the radial magnetic field component under the fixed design parameters of the thruster is measured by a gauss meter as shown in fig. 3.
The embodiment is used for realizing on-orbit evaluation on the thrust of the plasma Hall effect thruster by combining the basic principle that the Hall drift current and the radial magnetic field interact 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 calculation model includes:
T＝∫ V |J H B r |dV
wherein, T is on-orbit thrust; j. the design is a square H Is the Hall drift current density (i.e. the solution of the above matrix equation), and V is the discharge channel volume of the plasma Hall effect thruster; b is r For a given excitation currentAnd the radial component of the lower magnetic field is measured by a gauss meter under the condition that the excitation current is given by 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 cathode relative angle is 180 degrees, the exciting currents of the inner coil and the outer coil are respectively 2.4A and 1.4A, and the discharge voltage is 300V, the calculated thrust value is 23.10mN; at this time, the thrust value measured by 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 magnetic field intensity of the second level by using the magnetic sensing array, and performs on-orbit thrust calculation according to the magnetic field intensity of the second level, so as to obtain real-time on-orbit thrust, thereby avoiding the defect of poor evaluation real-time performance caused by the fact that the existing on-orbit thrust evaluation method needs to combine satellite orbit change information or angular displacement change information for thrust evaluation.
Example 2
The present embodiment provides an on-orbit thrust calculation system of a plasma hall effect thruster, please refer to fig. 5, which includes:
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 calculating module M2 is used for calculating the Hall drift current density in the discharge channel by utilizing a static magnetic field inversion method according to the magnetic field intensity;
the on-orbit thrust calculation module M3 is used for giving the radial component of the magnetic field under the excitation current and the Hall drift current density according to the fixed design parameters of the thruster and calculating the on-orbit thrust of the plasma Hall effect thruster by using an on-orbit thrust calculation model; the on-track thrust calculation model is used for representing the relation among the Hall drift current density, the radial component of the magnetic field under the given excitation current and the on-track thrust.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the description of the method part.
The principles and embodiments of the present invention have been described herein using specific examples, which are provided only to help understand the method and the core concept of the present invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.
Claims (8)
1. An on-orbit thrust calculation method of a plasma Hall effect thruster is characterized by comprising the following steps of:
acquiring the magnetic field intensity induced by 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;
according to the magnetic field intensity, calculating the Hall drift current density in a discharge channel by using a static magnetic field inversion method;
according to the Hall drift current density and the radial component of the magnetic field under the given exciting current of the thruster fixed design parameters, calculating the on-orbit thrust of the plasma Hall effect thruster by using an on-orbit thrust calculation model; the on-orbit thrust calculation model is used for representing the relation between the Hall drift current density, the radial magnetic field strength and the on-orbit thrust.
2. The method of claim 1, wherein 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 H To spread out the Hall drift current density profile j (r, z)Column vectors obtained after tiling; b is a vector constructed by the magnetic field intensity at the positions of a plurality of sensor measuring points in the Hall drift current induced magnetic field; a is a Green matrix which links current density distribution with magnetic field intensity of each sensor measuring point; the Green matrix is determined by a calibration experiment; λ 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 a radial position coordinate in a discharge channel of the plasma Hall effect thruster; z represents an axial position coordinate in a discharge channel of the plasma Hall effect thruster; l is a radical of an alcohol rr Representing a second derivative operator obtained by carrying out two derivatives on the radial position in the discharge channel of the plasma Hall effect thruster; l is zz Represents a second derivative operator L obtained by carrying out two derivatives on the axial position in the discharge channel of the plasma Hall effect thruster rz And the second derivative operator is obtained by performing first derivation on the radial position in the discharge channel of the plasma Hall effect thruster and performing first 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 takes into account non-negativity constraints and zero boundary constraints;
the non-negative constraint means that the azimuth current of the accelerating channel of the plasma Hall effect thruster flows along the same azimuth direction;
the zero boundary constraint means that the Hall drift current density on the boundary of the discharge chamber of the plasma Hall effect thruster is zero; the boundary of the discharge chamber of the plasma Hall effect thruster comprises the wall surface of a discharge channel of the plasma Hall effect thruster and the anode plane of the plasma Hall effect thruster.
4. The method of claim 1, wherein the formula of the on-orbit thrust calculation model comprises:
T＝∫ V |J H B r |dV
wherein T is on-orbit thrust; j is a unit of H The Hall drift current density is adopted, and V is the volume of a discharge channel of the plasma Hall effect thruster; b is r And measuring the radial component of the magnetic field under the given excitation current by a Gauss 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 a plume region and the magnetic field gradient is greater than a set threshold.
6. The method of claim 1, wherein the magnetic sensors of the magnetic sensor array are arranged in a manner that includes a radial arrangement and an axial arrangement.
7. The method of claim 1, wherein the magnetic sensor array has a tunneling magnetoresistive TMR as a sensing element.
8. An in-orbit thrust calculation system of 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 discharging 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 utilizing 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-rail thrust force calculation model is used for representing the relation among the Hall drift current density, the radial component of the magnetic field under the given exciting current and the on-rail thrust force.
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| 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 |
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