Spacecraft multi-layer near-field method magnetic moment calculation method and device

Abstract

The embodiment of the invention provides a spacecraft multi-layer near field method magnetic moment calculation method and device, and the method comprises the steps: determining the characteristics of a spacecraft, and determining the experiment arrangement of a magnetometer based on the characteristics of the spacecraft; wherein the magnetometer experiment arrangement comprises at least two layers; determining a magnetic moment conversion matrix based on magnetometer experimental arrangement; determining a magnetic moment result through a multi-layer near field method based on magnetometer experimental arrangement; a magnetic moment measurement is determined based on the magnetic moment conversion matrix and the magnetic moment result. Based on the multilayer near-field method and the magnetic dipole magnetic field model, optimization of the spacecraft multilayer near-field method magnetic moment calculation method can be realized, so that the magnetic characteristics of the spacecraft can be evaluated.

Description

Technical Field

[0001] The embodiments of this specification relate to the field of aerospace technology, and in particular to a method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method. Background Art

[0002] The error factors and accuracy assessment of spacecraft magnetic measurements are closely related to the spacecraft's structural dimensions, magnetic moment magnitude, internal magnetic distribution characteristics, and the magnetic testing methods and equipment used. Among commonly used magnetic testing methods, the spherical mapping method's errors are primarily due to non-dipole fields, while the near-field analysis method (also known as the equatorial mapping method)'s errors primarily depend on the magnetic testing conditions and test layout. Whole-vessel magnetic testing of small and medium-sized spacecraft can be conducted in a zero-magnetic environment or in the geomagnetic field, while whole-vessel magnetic testing of medium-sized and larger spacecraft can only be conducted in the geomagnetic field. For large spacecraft, especially tall and slender ones, the presence of height-dependent magnetic source eccentricity can affect the measurement accuracy of spacecraft magnetic testing. In such cases, the use of a multi-layer near-field method can effectively improve measurement accuracy. However, since each layer produces a magnetic moment calculation result, the question of how to use the moment calculation results of each layer to derive the true magnetic moment value of the spacecraft is pressing. Summary of the Invention

[0003] In view of this, embodiments of this specification provide a method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method. One or more embodiments of this specification also provide an apparatus for calculating the magnetic moment of a spacecraft using the multi-layer near-field method, a computing device, a computer-readable storage medium, and a computer program to address technical deficiencies in the prior art.

[0004] According to a first aspect of the embodiments of this specification, a method for calculating magnetic moments of a spacecraft using a multi-layer near-field method is provided, comprising:

[0005] determining a spacecraft characteristic, and determining a magnetometer experiment arrangement based on the spacecraft characteristic; wherein the magnetometer experiment arrangement includes at least two layers;

[0006] Determine the magnetic moment conversion matrix based on the magnetometer experimental arrangement;

[0007] Based on the magnetometer experimental arrangement, the magnetic moment results are determined by the multi-layer near-field method;

[0008] The magnetic moment measurement results are determined based on the magnetic moment conversion matrix and the magnetic moment results.

[0009] In one possible implementation, determining a magnetometer experiment arrangement based on spacecraft characteristics includes:

[0010] determining at least two sets of magnetometer probes based on spacecraft characteristics;

[0011] Determine the number of layers based on the magnetometer height of the magnetometer probe;

[0012] A right-handed coordinate system is established based on the distance between the magnetometer probe and the spacecraft.

[0013] In one possible implementation, based on a magnetometer experimental arrangement, determining a magnetic moment conversion matrix includes:

[0014] Constructing a mathematical model based on the magnetometer experimental arrangement;

[0015] The magnetic moment conversion matrix is ​​determined based on the mathematical model.

[0016] In one possible implementation, a mathematical model is constructed based on the magnetometer experimental arrangement, including:

[0017] Determine virtual magnetic sources based on the magnetometer experimental arrangement;

[0018] The magnetic field data is determined based on the virtual magnetic source and the corresponding magnetic field formula.

[0019] In one possible implementation, determining a magnetic moment conversion matrix based on a mathematical model includes:

[0020] Determine the magnetic moment value corresponding to each layer based on magnetic field data and distance parameters;

[0021] A magnetic moment conversion matrix is ​​determined based on the magnetic moment values.

[0022] In one possible implementation, determining the magnetic moment value corresponding to each layer based on the magnetic field data and the distance parameter includes:

[0023] Determine the magnetic moment values ​​from the nth layer to the last layer based on the magnetic field data and the distance parameter; wherein the value of n ranges from 1 to the last layer;

[0024] A vector value is determined based on the magnetic moment value.

[0025] In one possible implementation, determining the magnetic moment measurement result based on the magnetic moment conversion matrix and the magnetic moment result includes:

[0026] The magnetic moment measurement results of the x, y and z axes are determined based on the magnetic moment conversion matrix and the magnetic moment results.

[0027] According to a second aspect of the embodiments of this specification, a spacecraft multi-layer near-field method magnetic moment calculation device is provided, comprising:

[0028] a magnetometer arrangement module configured to determine a spacecraft characteristic and determine a magnetometer experiment arrangement based on the spacecraft characteristic;

[0029] a matrix determination module configured to determine a magnetic moment conversion matrix based on a magnetometer experimental arrangement;

[0030] a magnetic moment result determination module configured to determine the magnetic moment result by a multi-layer near-field method based on the magnetometer experimental arrangement;

[0031] The measurement result determination module is configured to determine the magnetic moment measurement result based on the magnetic moment conversion matrix and the magnetic moment result.

[0032] According to a third aspect of an embodiment of this specification, a computing device is provided, including:

[0033] memory and processor;

[0034] The memory is used to store computer-executable instructions, and the processor is used to execute the computer-executable instructions. When the computer-executable instructions are executed by the processor, the steps of the above-mentioned spacecraft multi-layer near-field method magnetic moment calculation method are implemented.

[0035] According to a fourth aspect of the embodiments of this specification, a computer-readable storage medium is provided, which stores computer-executable instructions, which, when executed by a processor, implement the steps of the above-mentioned method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method.

[0036] According to a fifth aspect of the embodiments of this specification, a computer program is provided, wherein when the computer program is executed in a computer, the computer is caused to execute the steps of the above-mentioned method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method.

[0037] Embodiments of this specification provide a method and apparatus for calculating the magnetic moment of a spacecraft using the multi-layer near-field method. The method comprises: determining spacecraft characteristics and determining a magnetometer experimental arrangement based on the spacecraft characteristics; wherein the magnetometer experimental arrangement includes at least two layers; determining a magnetic moment conversion matrix based on the magnetometer experimental arrangement; determining a magnetic moment result using the multi-layer near-field method based on the magnetometer experimental arrangement; and determining a magnetic moment measurement result based on the magnetic moment conversion matrix and the magnetic moment result. By using the multi-layer near-field method and a magnetic dipole magnetic field model, the method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method can be optimized to evaluate the magnetic properties of a spacecraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Figure 1 This is a flow chart of a method for calculating magnetic moments of a spacecraft using a multi-layer near-field method provided in one embodiment of this specification;

[0039] Figure 2 This is a schematic diagram of the principle of a method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method provided in one embodiment of this specification;

[0040] Figure 3 This is a schematic structural diagram of a spacecraft multi-layer near-field magnetic moment calculation device provided by one embodiment of this specification;

[0041] Figure 4 This is a structural block diagram of a computing device provided by one embodiment of this specification. DETAILED DESCRIPTION

[0042] The following description sets forth many specific details to facilitate a thorough understanding of this specification. However, this specification can be implemented in many other ways than those described herein, and those skilled in the art can make similar generalizations without violating the scope of this specification. Therefore, this specification is not limited to the specific implementations disclosed below.

[0043] The terms used in one or more embodiments of this specification are for the purpose of describing specific embodiments only and are not intended to limit one or more embodiments of this specification. The singular forms "a," "an," and "the" used in one or more embodiments of this specification and the appended claims are also intended to include plural forms unless the context clearly indicates otherwise. It should also be understood that the term "and / or" used in one or more embodiments of this specification refers to and includes any or all possible combinations of one or more associated listed items.

[0044] It should be understood that although the terms first, second, etc. may be used to describe various information in one or more embodiments of this specification, such information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of one or more embodiments of this specification, the first may also be referred to as the second, and similarly, the second may also be referred to as the first. Depending on the context, the word "if" as used herein may be interpreted as "at the time of" or "when" or "in response to determining".

[0045] In this specification, a method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method is provided. This specification also involves a device for calculating the magnetic moment of a spacecraft using the multi-layer near-field method, a computing device, and a computer-readable storage medium, which are described in detail one by one in the following embodiments.

[0046] See also Figure 1 , Figure 1 A flow chart of a method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method according to an embodiment of the present specification is shown, which specifically includes the following steps.

[0047] Step 101: Determine spacecraft characteristics, and determine a magnetometer experiment layout based on the spacecraft characteristics; wherein the magnetometer experiment layout includes at least two layers.

[0048] In one possible implementation, a magnetometer experiment arrangement is determined based on spacecraft characteristics, including: determining at least two groups of magnetometer probes based on the spacecraft characteristics; determining the number of layers based on magnetometer heights of the magnetometer probes; and establishing a right-handed coordinate system based on the distance between the magnetometer probes and the spacecraft.

[0049] In practical applications, a multi-layer near-field method is used as an example to arrange three layers on the top, equatorial and bottom surfaces of a spacecraft. Three groups of magnetometer probes are arranged, and the magnetometers in the same group are recorded as one layer with the same height, namely the first layer, the second layer and the third layer, as shown in the following example: Figure 2 shown.

[0050] Step 102: Determine the magnetic moment conversion matrix based on the magnetometer experimental arrangement.

[0051] In a possible implementation, determining a magnetic moment conversion matrix based on a magnetometer experimental arrangement includes: constructing a mathematical model based on the magnetometer experimental arrangement; and determining the magnetic moment conversion matrix based on the mathematical model.

[0052] Specifically, the mathematical model is constructed based on the magnetometer experimental arrangement, including: determining a virtual magnetic source based on the magnetometer experimental arrangement; and determining magnetic field data based on the virtual magnetic source and a corresponding magnetic field formula.

[0053] Furthermore, a magnetic moment conversion matrix is ​​determined based on the mathematical model, including: determining a magnetic moment value corresponding to each layer based on the magnetic field data and the distance parameter; and determining the magnetic moment conversion matrix based on the magnetic moment value.

[0054] Furthermore, the magnetic moment value corresponding to each layer is determined based on the magnetic field data and the distance parameter, including: determining the magnetic moment values ​​from the nth layer to the last layer based on the magnetic field data and the distance parameter; wherein the value range of n is 1 to the last layer; and determining the vector value based on the magnetic moment value.

[0055] In practical applications, taking the z-axis as an example, a virtual magnetic source is placed at the intersection of the spacecraft's z-axis and the first-layer plane, and the dipole is the standard unit magnetic dipole in the x-direction, designated M1. Based on the magnetic field formula for a magnetic dipole at any point in electromagnetics, the magnetic field data B at all magnetometer positions required for magnetic moment calculation in the multi-layer near-field method are calculated.

[0056] Furthermore, the multi-layer near-field method is used to calculate the x-direction magnetic moment values ​​of the first, second, and third layers, which are respectively recorded as M1,1, M1,2, and M1,3 and written as column vector A1(M1,1; M1,2; M1,3).

[0057] A virtual magnetic source is placed at the intersection of the spacecraft z-axis and the second-layer plane. The dipole is a standard unit magnetic dipole in the x-direction and is designated M2. According to the magnetic field formula of a magnetic dipole at any point in electromagnetics, the magnetic field data B of all magnetometer positions required for the magnetic moment calculation in the multi-layer near-field method are calculated.

[0058] Furthermore, the multi-layer near-field method is used to calculate the x-direction magnetic moment values ​​of the first, second, and third layers, which are respectively recorded as M2,1, M2,2, and M2,3, and written as column vector A2(M2,1; M2,2; M2,3);

[0059] A virtual magnetic source is placed at the intersection of the spacecraft z-axis and the third-layer plane. The dipole is a standard unit magnetic dipole in the x-direction, and M3 is used. Based on the magnetic field formula of a magnetic dipole at any point in electromagnetics, the magnetic field data B at all magnetometer positions required for the magnetic moment calculation in the multi-layer near-field method are calculated.

[0060] The multi-layer near-field method is used to calculate the x-direction magnetic moment values ​​of the first, second, and third layers respectively, which are recorded as M3,1, M3,2, and M3,3, and written as column vector A3(M3,1; M3,2; M3,3).

[0061] The coefficient matrix A = (A1, A2, A3), the coefficient matrix B is the inverse matrix of matrix A, B = A -1 .

[0062] Step 103: Based on the magnetometer experimental arrangement, the magnetic moment result is determined by a multi-layer near-field method.

[0063] In practical applications, the x-direction magnetic moment Mx of the spacecraft is measured experimentally. According to the experimental arrangement, the experiment is carried out according to the multi-layer near-field method to measure the magnetic moment of the spacecraft. The x-direction magnetic moment of each layer is denoted as M1, M2, and M3 respectively. The magnetic moment results of all layers can be written as a column vector C = (M1; M2; M3).

[0064] Step 104: Determine a magnetic moment measurement result based on the magnetic moment conversion matrix and the magnetic moment result.

[0065] In a possible implementation, determining the magnetic moment measurement result based on the magnetic moment conversion matrix and the magnetic moment result includes: determining the magnetic moment measurement results of the x, y, and z axes respectively based on the magnetic moment conversion matrix and the magnetic moment result.

[0066] In practical applications, according to the formula D=B*C, the column vector D=(DM1; DM2; DM3) is calculated; the sum of all elements of D is the spacecraft x-direction magnetic moment measurement result Mx=DM1+DM2+DM3; the x-direction is replaced by the y-direction and the z-direction respectively, and steps 2 to 4 are repeated to obtain the spacecraft y-direction magnetic moment measurement result My and the spacecraft z-direction magnetic moment measurement result Mz respectively.

[0067] Embodiments of this specification provide a method and apparatus for calculating the magnetic moment of a spacecraft using the multi-layer near-field method. The method comprises: determining spacecraft characteristics and determining a magnetometer experimental arrangement based on the spacecraft characteristics; wherein the magnetometer experimental arrangement includes at least two layers; determining a magnetic moment conversion matrix based on the magnetometer experimental arrangement; determining a magnetic moment result using the multi-layer near-field method based on the magnetometer experimental arrangement; and determining a magnetic moment measurement result based on the magnetic moment conversion matrix and the magnetic moment result. By using the multi-layer near-field method and a magnetic dipole magnetic field model, the method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method can be optimized to evaluate the magnetic properties of a spacecraft.

[0068] Corresponding to the above method embodiment, this specification also provides an embodiment of a spacecraft multi-layer near-field magnetic moment calculation device. Figure 3 A schematic structural diagram of a spacecraft multi-layer near-field magnetic moment calculation device provided by an embodiment of this specification is shown.

[0069] like Figure 3 As shown, the device includes:

[0070] The magnetometer arrangement module 301 is configured to determine spacecraft characteristics and determine a magnetometer experiment arrangement based on the spacecraft characteristics;

[0071] a matrix determination module 302 configured to determine a magnetic moment conversion matrix based on a magnetometer experimental arrangement;

[0072] A magnetic moment result determination module 303 is configured to determine a magnetic moment result by a multi-layer near-field method based on a magnetometer experimental arrangement;

[0073] The measurement result determination module 304 is configured to determine the magnetic moment measurement result based on the magnetic moment conversion matrix and the magnetic moment result.

[0074] In one possible implementation, determining a magnetometer experiment arrangement based on spacecraft characteristics includes:

[0075] determining at least two sets of magnetometer probes based on spacecraft characteristics;

[0076] Determine the number of layers based on the magnetometer height of the magnetometer probe;

[0077] A right-handed coordinate system is established based on the distance between the magnetometer probe and the spacecraft.

[0078] In one possible implementation, based on a magnetometer experimental arrangement, determining a magnetic moment conversion matrix includes:

[0079] Constructing a mathematical model based on the magnetometer experimental arrangement;

[0080] The magnetic moment conversion matrix is ​​determined based on the mathematical model.

[0081] In one possible implementation, a mathematical model is constructed based on the magnetometer experimental arrangement, including:

[0082] Determine virtual magnetic sources based on the magnetometer experimental arrangement;

[0083] The magnetic field data is determined based on the virtual magnetic source and the corresponding magnetic field formula.

[0084] In one possible implementation, determining a magnetic moment conversion matrix based on a mathematical model includes:

[0085] Determine the magnetic moment value corresponding to each layer based on magnetic field data and distance parameters;

[0086] A magnetic moment conversion matrix is ​​determined based on the magnetic moment values.

[0087] In one possible implementation, determining the magnetic moment value corresponding to each layer based on the magnetic field data and the distance parameter includes:

[0088] Determine the magnetic moment values ​​from the nth layer to the last layer based on the magnetic field data and the distance parameter; wherein the value of n ranges from 1 to the last layer;

[0089] A vector value is determined based on the magnetic moment value.

[0090] In one possible implementation, determining the magnetic moment measurement result based on the magnetic moment conversion matrix and the magnetic moment result includes:

[0091] The magnetic moment measurement results of the x, y and z axes are determined based on the magnetic moment conversion matrix and the magnetic moment results.

[0092] The above is a schematic diagram of a device for calculating the magnetic moment of a spacecraft using the multi-layer near-field method according to this embodiment. It should be noted that the technical solution of the device for calculating the magnetic moment of a spacecraft using the multi-layer near-field method is based on the same concept as the technical solution of the method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method. For details not described in detail in the technical solution of the device for calculating the magnetic moment of a spacecraft using the multi-layer near-field method, please refer to the description of the technical solution of the method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method.

[0093] Figure 4 The block diagram of a computing device 400 according to one embodiment of the present disclosure is shown. Components of the computing device 400 include, but are not limited to, a memory 410 and a processor 420. The processor 420 is connected to the memory 410 via a bus 430, and a database 450 is used to store data.

[0094] The computing device 400 also includes an access device 440 that enables the computing device 400 to communicate via one or more networks 460. Examples of such networks include a public switched telephone network (PSTN), a local area network (LAN), a wide area network (WAN), a personal area network (PAN), or a combination of communication networks such as the Internet. The access device 440 may include one or more of any type of network interface (e.g., a network interface card (NIC)) whether wired or wireless, such as an IEEE 802.11 wireless local area network (WLAN) wireless interface, a Worldwide Interoperability for Microwave Access (Wi-MAX) interface, an Ethernet interface, a universal serial bus (USB) interface, a cellular network interface, a Bluetooth interface, or a near field communication (NFC) interface.

[0095] In one embodiment of the present specification, the above components of the computing device 400 and Figure 4 Other components not shown in the figure may also be connected to each other, for example, via a bus. Figure 4 The computing device structure block diagram shown is for illustrative purposes only and is not intended to limit the scope of this specification. Those skilled in the art may add or replace other components as needed.

[0096] Computing device 400 may be any type of stationary or mobile computing device, including a mobile computer or mobile computing device (e.g., a tablet computer, a personal digital assistant, a laptop computer, a notebook computer, a netbook computer, etc.), a mobile phone (e.g., a smartphone), a wearable computing device (e.g., a smartwatch, smart glasses, etc.), or other types of mobile devices, or a stationary computing device such as a desktop computer or a personal computer (PC). Computing device 400 may also be a mobile or stationary server.

[0097] The processor 420 is configured to execute the following computer-executable instructions, which, when executed by the processor, implement the steps of the above-mentioned method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method. The above is a schematic diagram of a computing device of this embodiment. It should be noted that the technical solution of the computing device and the technical solution of the above-mentioned method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method are based on the same concept. For details not described in detail in the technical solution of the computing device, please refer to the description of the technical solution of the above-mentioned method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method.

[0098] An embodiment of the present specification further provides a computer-readable storage medium storing computer-executable instructions, which, when executed by a processor, implement the steps of the above-mentioned method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method.

[0099] The above is a schematic diagram of a computer-readable storage medium according to this embodiment. It should be noted that the technical solution of this storage medium is based on the same concept as the technical solution of the aforementioned method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method. For details not described in detail in the technical solution of the storage medium, please refer to the description of the technical solution of the aforementioned method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method.

[0100] An embodiment of the present specification further provides a computer program, wherein when the computer program is executed in a computer, the computer is caused to execute the steps of the above-mentioned method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method.

[0101] The above is an illustrative embodiment of a computer program. It should be noted that the technical solution of this computer program is based on the same concept as the technical solution of the aforementioned method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method. For details not described in detail in the technical solution of the computer program, please refer to the description of the technical solution of the aforementioned method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method.

[0102] The foregoing description of this specification describes specific embodiments. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recited in the claims can be performed in an order different from that described in the embodiments and still achieve the desired results. Furthermore, the processes depicted in the accompanying drawings do not necessarily require the specific order shown or the sequential order to achieve the desired results. In certain embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0103] The computer instructions include computer program code, which may be in source code form, object code form, executable file, or some intermediate form. The computer-readable medium may include: any entity or device capable of carrying the computer program code, recording medium, USB flash drive, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electric carrier signal, telecommunication signal, and software distribution medium, etc. It should be noted that the content contained in the computer-readable medium may be appropriately increased or decreased according to the requirements of legislation and patent practice in the jurisdiction. For example, in some jurisdictions, according to legislation and patent practice, computer-readable media do not include electric carrier signals and telecommunication signals.

[0104] It should be noted that for the aforementioned method embodiments, for the sake of simplicity of description, they are all expressed as a series of action combinations, but those skilled in the art should be aware that the embodiments of this specification are not limited by the order of the actions described, because according to the embodiments of this specification, certain steps can be performed in other orders or simultaneously. Secondly, those skilled in the art should also be aware that the embodiments described in this specification are all preferred embodiments, and the actions and modules involved are not necessarily required by the embodiments of this specification.

[0105] In the above embodiments, the description of each embodiment has its own focus. For parts that are not described in detail in a certain embodiment, reference can be made to the relevant description of other embodiments.

[0106] The preferred embodiments disclosed above are intended only to help illustrate this specification. The optional embodiments do not exhaustively describe all details, nor do they limit the invention to the specific embodiments described. Obviously, many modifications and variations can be made based on the content of the embodiments of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the embodiments of this specification, so that those skilled in the art can better understand and utilize this specification. This specification is limited only by the claims and their full scope and equivalents.

Claims

1. A method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method, characterized in that: include: determining a spacecraft characteristic, and determining a magnetometer experimental arrangement based on the spacecraft characteristic; wherein the magnetometer experimental arrangement comprises at least two layers; Based on the magnetometer experimental arrangement, determining a magnetic moment conversion matrix; Based on the magnetometer experimental arrangement, the magnetic moment results are determined by the multi-layer near-field method; A magnetic moment measurement result is determined based on the magnetic moment conversion matrix and the magnetic moment result.

2. The method according to claim 1, characterized in that Determine the magnetometer experiment layout based on the spacecraft characteristics, including: determining at least two sets of magnetometer probes based on the spacecraft characteristics; determining the number of layers based on a magnetometer height of the magnetometer probe; A right-handed coordinate system is established based on the distance between the magnetometer probe and the spacecraft.

3. The method according to claim 1, characterized in that The determining of the magnetic moment conversion matrix based on the magnetometer experimental arrangement includes: constructing a mathematical model based on the magnetometer experimental arrangement; A magnetic moment conversion matrix is ​​determined based on the mathematical model.

4. The method according to claim 3, characterized in that The mathematical model is constructed based on the magnetometer experimental arrangement, comprising: determining a virtual magnetic source based on the magnetometer experimental arrangement; Magnetic field data is determined based on the virtual magnetic source and a corresponding magnetic field formula.

5. The method according to claim 4, characterized in that Determining the magnetic moment conversion matrix based on the mathematical model includes: Determine the magnetic moment value corresponding to each layer based on the magnetic field data and the distance parameter; A magnetic moment conversion matrix is ​​determined based on the magnetic moment values.

6. The method according to claim 5, characterized in that The determining of the magnetic moment value corresponding to each layer based on the magnetic field data and the distance parameter includes: Determining magnetic moment values ​​from n layers to the last layer based on the magnetic field data and the distance parameter; wherein the value range of n is 1 to the last layer; A vector value is determined based on the magnetic moment value.

7. The method according to claim 1, characterized in that The determining of the magnetic moment measurement result based on the magnetic moment conversion matrix and the magnetic moment result includes: Magnetic moment measurement results of the x-axis, y-axis, and z-axis are determined based on the magnetic moment conversion matrix and the magnetic moment result.

8. A spacecraft multi-layer near-field magnetic moment calculation device, characterized in that: include: a magnetometer arrangement module configured to determine spacecraft characteristics and determine a magnetometer experiment arrangement based on the spacecraft characteristics; a matrix determination module configured to determine a magnetic moment conversion matrix based on the magnetometer experimental arrangement; a magnetic moment result determination module, configured to determine a magnetic moment result by a multi-layer near-field method based on the magnetometer experimental arrangement; The measurement result determination module is configured to determine a magnetic moment measurement result based on the magnetic moment conversion matrix and the magnetic moment result.

9. A computing device, characterized in that include: memory and processor; The memory is used to store computer-executable instructions, and the processor is used to execute the computer-executable instructions. When the computer-executable instructions are executed by the processor, the steps of the method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method as described in any one of claims 1 to 7 are implemented.

10. A computer-readable storage medium storing computer-executable instructions, which, when executed by a processor, implement the steps of the method for calculating the magnetic moment of a spacecraft using the multi-layer near-field method as described in any one of claims 1 to 7.

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