Spacecraft magnetic simulation method and device based on three-dimensional configuration

Abstract

The embodiment of this specification provides a spacecraft magnetic simulation method and device based on a three-dimensional configuration, wherein the spacecraft magnetic simulation method based on a three-dimensional configuration includes: determining an initial format file based on a spacecraft three-dimensional model; wherein the spacecraft three-dimensional model includes models of multiple stand-alone devices; converting the initial format file into a target file format, and establishing coordinate system information based on the target file format; determining a stand-alone equivalent residual magnetic model, and determining a spacecraft residual magnetic model based on the stand-alone equivalent residual magnetic model and coordinate system information; determining the magnetic field of the target stand-alone position based on the spacecraft residual magnetic model, and determining the mutual induction moment based on the magnetic field; determining the spacecraft mutual induction magnetic model based on the mutual induction moment and coordinate system information; determining magnetic field information based on the spacecraft residual magnetic model and the spacecraft mutual induction magnetic model, and displaying a magnetic field distribution diagram based on the magnetic field information. This method does not require meshing of the three-dimensional model, has a fast calculation speed, and does not have the situation of non-convergence of calculation.

Description

Technical Field

[0001] The embodiments of this specification relate to the field of aerospace technology, and in particular to a spacecraft magnetic simulation method based on three-dimensional configuration. Background Art

[0002] Spacecraft for magnetic field detection have strict control requirements on their magnetic cleanliness. In the design stage, in order to verify the magnetic cleanliness index of the spacecraft, it is necessary to simulate and analyze the magnetic properties of the spacecraft to verify and optimize the magnetic cleanliness control scheme of the whole device.

[0003] The commonly used three-dimensional magnetic field simulation methods are mainly finite element and finite difference methods. These methods first establish a three-dimensional model of the simulation object, then mesh and discretize the three-dimensional model, and finally solve the partial differential equations of Maxwell's equations to calculate the spatial magnetic field distribution.

[0004] However, for the magnetic field simulation of a complex system such as a spacecraft, this finite element or finite difference method based on meshing is difficult to perform simulation analysis. A spacecraft is a complex and large system with hundreds of stand-alone devices inside it, and the magnetism of the spacecraft mainly comes from the magnetic components and working current inside these stand-alone devices. If the finite element or finite difference method is used, it is necessary to establish a three-dimensional model of the magnetic components and working current inside each stand-alone device, set the corresponding magnetic parameters and perform meshing. First of all, due to the complexity of magnetic materials, their magnetism is related to the magnetization state, and there are many magnetic components inside, so it is impossible to accurately set the magnetic parameters of each magnetic component. In addition, due to the large difference in size between the magnetic devices inside the stand-alone device and the spacecraft, when meshing, the mesh sizes of different areas vary greatly, which is bound to affect the accuracy and convergence of the simulation results; if the entire calculation area is meshed, the number of meshes is huge, which is bound to cause the software to be unable to calculate or converge. Therefore, a better solution is urgently needed. Summary of the invention

[0005] In view of this, the embodiments of this specification provide a spacecraft magnetic simulation method based on a three-dimensional configuration. One or more embodiments of this specification also relate to a spacecraft magnetic simulation device based on a three-dimensional configuration, a computing device, a computer-readable storage medium, and a computer program to solve the technical defects existing in the prior art.

[0006] According to a first aspect of an embodiment of this specification, a spacecraft magnetic simulation method based on a three-dimensional configuration is provided, comprising:

[0007] Determine an initial format file based on a three-dimensional model of the spacecraft; wherein the three-dimensional model of the spacecraft includes models of multiple stand-alone devices;

[0008] Convert the initial format file into the target file format, and establish the coordinate system information based on the target file format;

[0009] Determine the single-machine equivalent residual magnetic model, and determine the spacecraft residual magnetic model based on the single-machine equivalent residual magnetic model and coordinate system information;

[0010] Determine the magnetic field at the target single machine location based on the spacecraft remanent magnetism model, and determine the mutual induction moment based on the magnetic field;

[0011] Determine the spacecraft mutual magnetic model based on the mutual magnetic moment and coordinate system information;

[0012] The magnetic field information is determined based on the spacecraft remanent magnetism model and the spacecraft mutual induction magnetic model, and the magnetic field distribution map is displayed based on the magnetic field information.

[0013] In a possible implementation, establishing coordinate system information based on the target file format includes:

[0014] Determine the 3D view based on the target file format;

[0015] Determine first transformation information for transformation between a test coordinate system and a product coordinate system, and second transformation information for transformation between a product coordinate system and a spacecraft coordinate system based on the three-dimensional view;

[0016] Coordinate system information is established based on the first conversion information and the second conversion information.

[0017] In a possible implementation, determining the equivalent residual magnetism model of a single machine includes:

[0018] Obtain magnetic field measurement data of a single device;

[0019] The equivalent residual magnetism model of a single machine is determined based on the magnetic field measurement data.

[0020] In a possible implementation, determining a single machine equivalent residual magnetism model based on magnetic field measurement data includes:

[0021] Determine the magnetic field value vector of a single device;

[0022] Determine an initial magnetic model, and determine a magnetic field calculation value vector based on the initial magnetic model and a least squares optimization objective function;

[0023] Determine a least square optimization objective function based on the magnetic field value vector and the magnetic field calculation value vector;

[0024] The least squares optimal solution is solved based on the magnetic field measurement data and the least squares optimization objective function to determine the equivalent residual magnetism model of a single machine.

[0025] In a possible implementation, determining the mutual induction moment based on the magnetic field includes:

[0026] Determine the target magnetic field strength of the stand-alone device, and determine the magnetic moment based on the target magnetic field strength;

[0027] Based on the magnetic induction moment and the magnetic field, the mutual induction moment is determined.

[0028] In a possible implementation, determining a spacecraft mutual magnetic induction model based on the mutual magnetic induction moment and coordinate system information includes:

[0029] The mutual magnetic induction model of the spacecraft is obtained by transformation based on the mutual magnetic moment and coordinate system information.

[0030] In a possible implementation, determining magnetic field information based on a spacecraft remanent magnetism model and a spacecraft mutual induction magnetic model includes:

[0031] Determine the magnetic field calculation rules;

[0032] Determining a first magnetic field distribution based on a spacecraft remanent magnetism model and a magnetic field calculation rule;

[0033] Determine the second magnetic field distribution based on the spacecraft mutual induction magnetic model and magnetic field calculation rules;

[0034] Magnetic field information is determined based on vector superposition of the first magnetic field distribution and the second magnetic field distribution.

[0035] According to a second aspect of the embodiments of this specification, a spacecraft magnetic simulation device based on a three-dimensional configuration is provided, comprising:

[0036] A file conversion module is configured to determine an initial format file based on a three-dimensional model of a spacecraft; wherein the three-dimensional model of the spacecraft includes models of multiple stand-alone devices;

[0037] A coordinate conversion module is configured to convert the initial format file into a target file format and establish coordinate system information based on the target file format;

[0038] The residual magnetism model module is configured to determine a single machine equivalent residual magnetism model, and determine a spacecraft residual magnetism model based on the single machine equivalent residual magnetism model and coordinate system information;

[0039] A mutual induction moment module is configured to determine a magnetic field at a target single machine position based on a spacecraft residual magnetism model, and determine a mutual induction moment based on the magnetic field;

[0040] A mutual induction magnetic model module is configured to determine a mutual induction magnetic model of a spacecraft based on the mutual induction magnetic moment and the coordinate system information;

[0041] The magnetic field information module is configured to determine the magnetic field information based on the spacecraft remanent magnetism model and the spacecraft mutual inductance magnetic model, and to display the magnetic field distribution map based on the magnetic field information.

[0042] According to a third aspect of an embodiment of this specification, a computing device is provided, including:

[0043] Memory and processor;

[0044] 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 magnetic simulation method based on three-dimensional configuration are implemented.

[0045] According to a fourth aspect of the embodiments of this specification, a computer-readable storage medium is provided, which stores computer-executable instructions, and when the instructions are executed by a processor, the steps of the above-mentioned spacecraft magnetic simulation method based on three-dimensional configuration are implemented.

[0046] According to a fifth aspect of the embodiments of the present 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 spacecraft magnetic simulation method based on three-dimensional configuration.

[0047] The embodiment of this specification provides a spacecraft magnetic simulation method and device based on a three-dimensional configuration, wherein the spacecraft magnetic simulation method based on a three-dimensional configuration includes: determining an initial format file based on a spacecraft three-dimensional model; wherein the spacecraft three-dimensional model includes models of multiple stand-alone devices; converting the initial format file into a target file format, and establishing coordinate system information based on the target file format; determining a stand-alone equivalent residual magnetic model, and determining a spacecraft residual magnetic model based on the stand-alone equivalent residual magnetic model and coordinate system information; determining the magnetic field of the target stand-alone position based on the spacecraft residual magnetic model, and determining the mutual induction moment based on the magnetic field; determining the spacecraft mutual induction magnetic model based on the mutual induction moment and coordinate system information; determining magnetic field information based on the spacecraft residual magnetic model and the spacecraft mutual induction magnetic model, and displaying a magnetic field distribution diagram based on the magnetic field information. This method does not require meshing of the three-dimensional model, has a fast calculation speed, and does not have the situation of non-convergence of calculation. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] Figure 1 is a flow chart of a spacecraft magnetic simulation method based on a three-dimensional configuration provided by an embodiment of this specification;

[0049] Figure 2 It is a schematic diagram of an equivalent magnetic model of a single-machine device of a spacecraft magnetic simulation method based on a three-dimensional configuration provided by an embodiment of this specification;

[0050] Figure 3 It is a schematic diagram of coordinate system conversion relationship of a spacecraft magnetic simulation method based on a three-dimensional configuration provided by an embodiment of this specification;

[0051] Figure 4 It is a structural schematic diagram of a spacecraft magnetic simulation device based on a three-dimensional configuration provided by an embodiment of this specification;

[0052] Figure 5 It is a structural block diagram of a computing device provided by an embodiment of this specification. DETAILED DESCRIPTION

[0053] Many specific details are described in the following description to facilitate a full 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 connotation of this specification, so this specification is not limited to the specific implementation disclosed below.

[0054] The terms used in one or more embodiments of this specification are only for the purpose of describing specific embodiments, and are not intended to limit one or more embodiments of this specification. The singular forms of "a" 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 other meanings. 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.

[0055] 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, this 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".

[0056] In this specification, a spacecraft magnetic simulation method based on a three-dimensional configuration is provided. This specification also relates to a spacecraft magnetic simulation device based on a three-dimensional configuration, a computing device, and a computer-readable storage medium, which are described in detail one by one in the following embodiments.

[0057] See also Figure 1 , Figure 1 A flow chart of a spacecraft magnetic simulation method based on a three-dimensional configuration provided according to an embodiment of the present specification is shown, which specifically includes the following steps.

[0058] Step 101: Determine an initial format file based on a three-dimensional model of a spacecraft; wherein the three-dimensional model of the spacecraft includes models of multiple stand-alone devices.

[0059] In practical applications, the spacecraft 3D design model is exported as a STEP file in 3D CAD design software such as Pro / E and Catia.

[0060] Step 102: Convert the initial format file into a target file format, and establish coordinate system information based on the target file format.

[0061] The coordinate system information may include the transformation relationship from the test coordinate system to the product coordinate system, and the transformation relationship from the product coordinate system to the spacecraft coordinate system.

[0062] In one possible implementation, coordinate system information is established based on the target file format, including: determining a three-dimensional view based on the target file format; determining first conversion information for converting a test coordinate system to a product coordinate system based on the three-dimensional view, and second conversion information for converting a product coordinate system to a spacecraft coordinate system; and establishing coordinate system information based on the first conversion information and the second conversion information.

[0063] In practical applications, the model conversion module of the simulation system is used to read the STEP file, parse the assembly relationship of the model in the file, and export the model of each stand-alone device to the STL file format. The pre-processing module of the simulation system reads the analyzed spacecraft assembly relationship and the stand-alone device STL file and displays them in a three-dimensional view. The test coordinate system and product coordinate system of each stand-alone device are established in the simulation system, and the Euler angle ( α 1, β 1, γ 1) and translation vector ( x 1, y 1, z 1), Euler angles for transforming product coordinate system to spacecraft coordinate system ( α 2, β 2, γ 2) and translation vector ( x 1, y 2, z 2).

[0064] Step 103: Determine a single-machine equivalent residual magnetic model, and determine a spacecraft residual magnetic model based on the single-machine equivalent residual magnetic model and coordinate system information.

[0065] In a possible implementation, determining a single-machine equivalent residual magnetism model includes: acquiring magnetic field measurement data of a single-machine device; and determining the single-machine equivalent residual magnetism model based on the magnetic field measurement data.

[0066] In practical applications, the magnetic field measurement data of a single device is imported and the equivalent residual magnetic model of the single device is calculated. Figure 2 The basic principle of the equivalent residual magnetism modeling method for a single device is to measure the n t The magnetic field value of the measurement point is assumed to be n d A magnetic dipole,n d If there is a combination of the position and magnetic moment of each magnetic dipole, so that the magnetic field generated at each measurement point is equal to the known magnetic field at the measurement point, then the magnetic model of the device is considered to be consistent with this n d The combination of magnetic dipoles is equivalent.

[0067] Specifically, the equivalent residual magnetism model of a single machine is determined based on magnetic field measurement data, including: determining the magnetic field value vector of the single machine equipment; determining the initial magnetic model, and determining the magnetic field calculation value vector based on the initial magnetic model and the least squares optimization objective function; determining the least squares optimization objective function based on the magnetic field value vector and the magnetic field calculation value vector; solving the least squares optimal solution based on the magnetic field measurement data and the least squares optimization objective function to determine the equivalent residual magnetism model of the single machine.

[0068] In practical applications, it is assumed that the magnetic field value vector and position vector of nt measurement points (nt≥108) on the circumference of a single device are Bt and Rt respectively:

[0069]

[0070] Define the equivalent magnetic model of a single device as including n d ( n d ≤5 ) The magnetic model of a magnetic dipole, whose magnetic moment vector and position vector are M d , R d :

[0071]

[0072] The least squares optimization objective function of the magnetic field measurement value and the magnetic field calculation value at the measurement point of the single-machine equipment is established, and the magnetic field calculation value vector based on the equivalent magnetic dipole model at the measurement point of the single-machine equipment is defined as B c :

[0073]

[0074] Then we have:

[0075] (1)

[0076] G for G ik of n t ×n d dimensional matrix, G ikis a 3×3 matrix, which can be obtained by the following formula

[0077] (2)

[0078] in, r t i For the i The position vector of each measurement point;

[0079] r d j For the j The magnetic dipole position vector;

[0080] I is a 3×3 identity matrix.

[0081] Define the least squares optimization objective function of the magnetic field measurement value and magnetic field calculation value at the measurement point of a single device e for:

[0082] (3)

[0083] The Gauss-Newton algorithm or the Levenberg-Marquardt algorithm is used to solve the least squares optimal solution of formula (3) to obtain the magnetic dipole magnetic moment vector of the equivalent magnetic dipole model of the optimized single-machine equipment. M d and the position vector R d .

[0084] For further information, see Figure 3 According to the relationship between the single-machine product test coordinate system, the product coordinate system and the spacecraft coordinate system, the single-machine equivalent residual magnetism model is transformed into the spacecraft coordinate system to obtain the equivalent residual magnetism model of the spacecraft.

[0085] Step 104: Determine the magnetic field at the target single machine position based on the spacecraft remanent magnetism model, and determine the mutual induction moment based on the magnetic field.

[0086] In a possible implementation, determining the mutual induction moment based on the magnetic field includes: determining a target magnetic field strength of a single device, and determining the magnetic induction moment based on the target magnetic field strength; and determining the mutual induction moment based on the magnetic induction moment and the magnetic field.

[0087] Among them, the target magnetic field strength can be 50000nT.

[0088] In practical applications, the residual magnetic model of the spacecraft is used to calculate the magnetic field at each unit location according to formula (4) and the installation location of each unit:

[0089] (4)

[0090] The mutual induction moment of each unit is calculated using the magnetic induction moment of the unit under an external magnetic field of 50000nT and the magnetic field at the position of each unit:

[0091] (5)

[0092] Step 105: Determine the spacecraft mutual magnetic model based on the mutual magnetic moment and the coordinate system information.

[0093] In a possible implementation, determining a spacecraft mutual magnetic model based on the mutual magnetic moment and coordinate system information includes: performing conversion based on the mutual magnetic moment and coordinate system information to obtain the spacecraft mutual magnetic model.

[0094] In practical applications, the mutual magnetic moment of each single machine is converted into the spacecraft coordinate system in the manner shown in FIG3 to form a spacecraft mutual magnetic model.

[0095] Step 106: Determine magnetic field information based on the spacecraft remanent magnetism model and the spacecraft mutual inductance magnetic model, and display a magnetic field distribution map based on the magnetic field information.

[0096] In one possible implementation, magnetic field information is determined based on a spacecraft residual magnetism model and a spacecraft mutual induction magnetic model, including: determining a magnetic field calculation rule; determining a first magnetic field distribution based on the spacecraft residual magnetism model and the magnetic field calculation rule; determining a second magnetic field distribution based on the spacecraft mutual induction magnetic model and the magnetic field calculation rule; and determining magnetic field information by performing vector superposition on the first magnetic field distribution and the second magnetic field distribution.

[0097] In practical applications, the magnetic field calculation area and the position distribution of the spatial magnetic field discrete points are set, and the spatial magnetic field distribution at each discrete point of the spacecraft is calculated using the spacecraft remanent magnetism model and the mutual induction magnetic model using formula (4), and the magnetic field vectors of the magnetic field simulation results calculated by the two magnetic models are superimposed:

[0098]

[0099] Furthermore, the simulation system post-processing module is used to display the distribution diagrams of the spacecraft's magnetic field vector, scalar, etc.

[0100] The embodiment of the present specification provides a spacecraft magnetic simulation method and device based on a three-dimensional configuration, wherein the spacecraft magnetic simulation method based on a three-dimensional configuration includes: determining an initial format file based on a spacecraft three-dimensional model; wherein the spacecraft three-dimensional model includes models of multiple stand-alone devices; converting the initial format file into a target file format, and establishing coordinate system information based on the target file format; determining a stand-alone equivalent residual magnetic model, and determining a spacecraft residual magnetic model based on the stand-alone equivalent residual magnetic model and coordinate system information; determining the magnetic field of the target stand-alone position based on the spacecraft residual magnetic model, and determining the mutual induction magnetic moment based on the magnetic field; determining the spacecraft mutual induction magnetic model based on the mutual induction magnetic moment and coordinate system information; determining the magnetic field information based on the spacecraft residual magnetic model and the spacecraft mutual induction magnetic model, and displaying a magnetic field distribution map based on the magnetic field information. The method does not require meshing of the three-dimensional model, has a fast calculation speed, and does not have the situation of non-convergence of the calculation. Further, the method does not require the establishment of a complex model of material parameters and current trends of magnetic devices inside a single spacecraft, and constructs a stand-alone equivalent model based on measured data, which is simple and more accurate in modeling, and has high simulation accuracy.

[0101] Corresponding to the above method embodiment, this specification also provides an embodiment of a spacecraft magnetic simulation device based on a three-dimensional configuration, Figure 4 FIG. 1 shows a schematic diagram of a structure of a spacecraft magnetic simulation device based on a three-dimensional configuration provided by an embodiment of the present specification. Figure 4 As shown, the device comprises:

[0102] The file conversion module 401 is configured to determine an initial format file based on a three-dimensional model of a spacecraft; wherein the three-dimensional model of the spacecraft includes models of multiple stand-alone devices;

[0103] A coordinate conversion module 402 is configured to convert the initial format file into a target file format and establish coordinate system information based on the target file format;

[0104] The residual magnetism model module 403 is configured to determine a single machine equivalent residual magnetism model, and determine a spacecraft residual magnetism model based on the single machine equivalent residual magnetism model and coordinate system information;

[0105] The mutual induction moment module 404 is configured to determine the magnetic field at the target stand-alone position based on the spacecraft residual magnetism model, and determine the mutual induction moment based on the magnetic field;

[0106] The mutual induction magnetic model module 405 is configured to determine the mutual induction magnetic model of the spacecraft based on the mutual induction magnetic moment and the coordinate system information;

[0107] The magnetic field information module 406 is configured to determine the magnetic field information based on the spacecraft remanent magnetism model and the spacecraft mutual induction magnetic model, and display the magnetic field distribution map based on the magnetic field information.

[0108] In a possible implementation, the coordinate conversion module 402 is further configured to:

[0109] Determine the 3D view based on the target file format;

[0110] Determine first transformation information for transformation between a test coordinate system and a product coordinate system, and second transformation information for transformation between a product coordinate system and a spacecraft coordinate system based on the three-dimensional view;

[0111] Coordinate system information is established based on the first conversion information and the second conversion information.

[0112] In a possible implementation, the residual magnetism model module 403 is further configured as follows:

[0113] Obtain magnetic field measurement data of a single device;

[0114] The equivalent residual magnetism model of a single machine is determined based on the magnetic field measurement data.

[0115] In a possible implementation, the residual magnetism model module 403 is further configured as follows:

[0116] Determine the magnetic field value vector of a single device;

[0117] Determine an initial magnetic model, and determine a magnetic field calculation value vector based on the initial magnetic model and a least squares optimization objective function;

[0118] Determine a least square optimization objective function based on the magnetic field value vector and the magnetic field calculation value vector;

[0119] The least squares optimal solution is solved based on the magnetic field measurement data and the least squares optimization objective function to determine the equivalent residual magnetism model of a single machine.

[0120] In a possible implementation, the mutual inductance module 404 is further configured as follows:

[0121] Determine the target magnetic field strength of the stand-alone device, and determine the magnetic moment based on the target magnetic field strength;

[0122] Based on the magnetic induction moment and the magnetic field, the mutual induction moment is determined.

[0123] In a possible implementation, the mutual inductance magnetic model module 405 is further configured as follows:

[0124] The mutual magnetic induction model of the spacecraft is obtained by transformation based on the mutual magnetic moment and coordinate system information.

[0125] In a possible implementation, the magnetic field information module 406 is further configured to:

[0126] Determine the magnetic field calculation rules;

[0127] Determining a first magnetic field distribution based on a spacecraft remanent magnetism model and a magnetic field calculation rule;

[0128] Determine the second magnetic field distribution based on the spacecraft mutual induction magnetic model and magnetic field calculation rules;

[0129] Magnetic field information is determined based on vector superposition of the first magnetic field distribution and the second magnetic field distribution.

[0130] The embodiment of this specification provides a spacecraft magnetic simulation method and device based on a three-dimensional configuration, wherein the spacecraft magnetic simulation device based on the three-dimensional configuration includes: determining an initial format file based on a spacecraft three-dimensional model; wherein the spacecraft three-dimensional model includes models of multiple stand-alone devices; converting the initial format file into a target file format, and establishing coordinate system information based on the target file format; determining a stand-alone equivalent residual magnetic model, and determining a spacecraft residual magnetic model based on the stand-alone equivalent residual magnetic model and coordinate system information; determining the magnetic field of the target stand-alone position based on the spacecraft residual magnetic model, and determining the mutual induction moment based on the magnetic field; determining the spacecraft mutual induction magnetic model based on the mutual induction moment and coordinate system information; determining magnetic field information based on the spacecraft residual magnetic model and the spacecraft mutual induction magnetic model, and displaying a magnetic field distribution diagram based on the magnetic field information. This method does not require meshing of the three-dimensional model, has a fast calculation speed, and does not have the situation of non-convergence of calculation.

[0131] The above is a schematic scheme of a spacecraft magnetic simulation device based on a three-dimensional configuration of this embodiment. It should be noted that the technical scheme of the spacecraft magnetic simulation device based on a three-dimensional configuration and the technical scheme of the spacecraft magnetic simulation method based on a three-dimensional configuration belong to the same concept, and the details of the technical scheme of the spacecraft magnetic simulation device based on a three-dimensional configuration that are not described in detail can be found in the description of the technical scheme of the spacecraft magnetic simulation method based on a three-dimensional configuration.

[0132] Figure 5 The structure block diagram of a computing device 500 provided according to an embodiment of the present specification is shown. The components of the computing device 500 include but are not limited to a memory 510 and a processor 520. The processor 520 is connected to the memory 510 via a bus 530, and the database 550 is used to store data.

[0133] The computing device 500 also includes an access device 540 that enables the computing device 500 to communicate via one or more networks 560. Examples of these 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 540 may include one or more of any type of network interface (e.g., a network interface card (NIC)) that is wired or wireless, such as an IEEE 802.11 wireless local area network (WLAN) wireless interface, a world-wide interoperability for microwave access (Wi-MAX) interface, an Ethernet interface, a universal serial bus (USB) interface, a cellular network interface, a Bluetooth interface, and a near field communication (NFC).

[0134] In one embodiment of the present specification, the above components of the computing device 500 and Figure 5 Other components not shown in the figure may also be connected to each other, for example, via a bus. It should be understood that Figure 5 The computing device structure block diagram shown is only for the purpose of illustration, and is not intended to limit the scope of this specification. Those skilled in the art can add or replace other components as needed.

[0135] The computing device 500 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, etc.), a mobile phone (e.g., a smart phone), a wearable computing device (e.g., a smart watch, smart glasses, etc.), or other types of mobile devices, or a stationary computing device such as a desktop computer or a personal computer (PC). The computing device 500 may also be a mobile or stationary server.

[0136] The processor 520 is used to execute the following computer executable instructions, which, when executed by the processor, implement the steps of the above-mentioned spacecraft magnetic simulation method based on three-dimensional configuration. The above is a schematic scheme of a computing device of this embodiment. It should be noted that the technical scheme of the computing device and the technical scheme of the above-mentioned spacecraft magnetic simulation method based on three-dimensional configuration belong to the same concept. The details of the technical scheme of the computing device that are not described in detail can be found in the description of the technical scheme of the above-mentioned spacecraft magnetic simulation method based on three-dimensional configuration.

[0137] An embodiment of the present specification also provides a computer-readable storage medium storing computer-executable instructions, which, when executed by a processor, implement the steps of the above-mentioned three-dimensional configuration-based spacecraft magnetic simulation method.

[0138] The above is a schematic scheme of a computer-readable storage medium of this embodiment. It should be noted that the technical scheme of the storage medium and the technical scheme of the above-mentioned spacecraft magnetic simulation method based on three-dimensional configuration belong to the same concept, and the details not described in detail in the technical scheme of the storage medium can be referred to the description of the technical scheme of the above-mentioned spacecraft magnetic simulation method based on three-dimensional configuration.

[0139] An embodiment of the present specification also 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 spacecraft magnetic simulation method based on three-dimensional configuration.

[0140] The above is a schematic scheme of a computer program of this embodiment. It should be noted that the technical scheme of the computer program and the technical scheme of the above-mentioned spacecraft magnetic simulation method based on three-dimensional configuration belong to the same concept, and the details not described in detail in the technical scheme of the computer program can be referred to the description of the technical scheme of the above-mentioned spacecraft magnetic simulation method based on three-dimensional configuration.

[0141] The above is a description of a specific embodiment of the specification. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recorded in the claims can be performed in an order different from that in the embodiments and still achieve the desired results. In addition, the processes depicted in the drawings do not necessarily require the specific order or continuous order shown to achieve the desired results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0142] The computer instructions include computer program codes, which may be in source code form, object code form, executable files or some intermediate forms, etc. 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.

[0143] It should be noted that, for the above-mentioned 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, some steps can be performed in other orders or simultaneously. Secondly, those skilled in the art should also be aware that the embodiments described in the specification are all preferred embodiments, and the actions and modules involved are not necessarily required by the embodiments of this specification.

[0144] In the above embodiments, the description of each embodiment has its own emphasis. For parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0145] The preferred embodiments of this specification disclosed above are only used to help explain this specification. The optional embodiments do not describe all the details in detail, nor do they limit the invention to only the specific implementation methods described. Obviously, many modifications and changes can be made according to 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 technicians in the relevant technical field can well understand and use this specification. This specification is only limited by the claims and their full scope and equivalents.

Claims

1. A spacecraft magnetic simulation method based on three-dimensional configuration, characterized in that: include: Determining an initial format file based on a three-dimensional model of a spacecraft; wherein the three-dimensional model of the spacecraft includes models of multiple stand-alone devices; Converting the initial format file into a target file format, and establishing coordinate system information based on the target file format; Determine a single machine equivalent residual magnetic model, and determine a spacecraft residual magnetic model based on the single machine equivalent residual magnetic model and the coordinate system information; Determine the magnetic field at the target single machine position based on the spacecraft residual magnetism model, and determine the mutual induction moment based on the magnetic field; Determine a spacecraft mutual magnetic model based on the mutual magnetic moment and the coordinate system information; Determining magnetic field information based on the spacecraft residual magnetism model and the spacecraft mutual induction magnetic model, and displaying a magnetic field distribution map based on the magnetic field information; The step of determining the single machine equivalent residual magnetism model comprises: Acquiring magnetic field measurement data of the stand-alone device; Determine the equivalent residual magnetism model of a single machine based on magnetic field measurement data; The method of determining a single machine equivalent residual magnetism model based on magnetic field measurement data comprises: Determining a magnetic field value vector of the stand-alone device; Determining an initial magnetic model, and determining a magnetic field calculation value vector based on the initial magnetic model and a least squares optimization objective function; Determine a least squares optimization objective function based on the magnetic field value vector and the magnetic field calculation value vector; A least squares optimal solution is obtained based on the magnetic field measurement data and the least squares optimization objective function to determine a single machine equivalent residual magnetism model.

2. The method according to claim 1, characterized in that The establishing of coordinate system information based on the target file format includes: determining a three-dimensional view based on the target file format; Determine first conversion information for converting between a test coordinate system and a product coordinate system based on the three-dimensional view, and second conversion information for converting between the product coordinate system and a spacecraft coordinate system; Coordinate system information is established based on the first conversion information and the second conversion information.

3. The method according to claim 1, characterized in that The determining the mutual induction moment based on the magnetic field comprises: Determining a target magnetic field strength of the stand-alone device, and determining a magnetic sensitivity moment based on the target magnetic field strength; Based on the magnetic induction moment and the magnetic field, a mutual magnetic induction moment is determined.

4. The method according to claim 1, characterized in that: The determining of the spacecraft mutual magnetic model based on the mutual magnetic moment and the coordinate system information includes: The mutual magnetic induction model of the spacecraft is obtained by performing transformation based on the mutual magnetic induction moment and the coordinate system information.

5. The method according to claim 1, characterized in that The determining of magnetic field information based on the spacecraft remanent magnetism model and the spacecraft mutual induction magnetic model includes: Determine the magnetic field calculation rules; Determining a first magnetic field distribution based on the spacecraft residual magnetism model and the magnetic field calculation rule; Determining a second magnetic field distribution based on the spacecraft mutual induction magnetic model and the magnetic field calculation rule; Magnetic field information is determined based on vector superposition of the first magnetic field distribution and the second magnetic field distribution.

6. A three-dimensional configuration-based spacecraft magnetic simulation device, used to implement the steps of the three-dimensional configuration-based spacecraft magnetic simulation method according to any one of claims 1 to 5, characterized in that: include: A file conversion module is configured to determine an initial format file based on a three-dimensional model of a spacecraft; wherein the three-dimensional model of the spacecraft includes models of multiple stand-alone devices; A coordinate conversion module, configured to convert the initial format file into a target file format, and establish coordinate system information based on the target file format; A residual magnetism model module is configured to determine a single-machine equivalent residual magnetism model, and determine a spacecraft residual magnetism model based on the single-machine equivalent residual magnetism model and the coordinate system information; A mutual induction moment module is configured to determine a magnetic field at a target stand-alone position based on the spacecraft residual magnetism model, and determine a mutual induction moment based on the magnetic field; A mutual induction magnetic model module, configured to determine a spacecraft mutual induction magnetic model based on the mutual induction magnetic moment and the coordinate system information; The magnetic field information module is configured to determine the magnetic field information based on the spacecraft residual magnetism model and the spacecraft mutual induction magnetic model, and to display a magnetic field distribution diagram based on the magnetic field information.

7. 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 spacecraft magnetic simulation method based on three-dimensional configuration described in any one of claims 1 to 5 are implemented.

8. A computer-readable storage medium storing computer-executable instructions, which, when executed by a processor, implement the steps of the three-dimensional configuration-based spacecraft magnetic simulation method as described in any one of claims 1 to 5.

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