Spacecraft on-orbit magnetic simulation method, device and equipment

Abstract

The invention provides a spacecraft on-orbit magnetic simulation method, device and equipment, and the method comprises the steps: calibrating the parameters of a spacecraft in a ground zero magnetic field environment; determining an in-orbit sub-satellite point trajectory of the spacecraft by utilizing orbit dynamics according to the number of spacecraft orbits; inputting the sub-satellite point trajectory to the geomagnetic field reference model, and outputting three components of the geomagnetic field at the position of the spacecraft; converting the three components of the geomagnetic field into three components of the geomagnetic field under an earth-fixed coordinate system based on the sub-satellite point trajectory of the spacecraft; based on the yaw angle, the pitch angle and the rolling angle of the spacecraft, converting the geomagnetic field three-component under the earth-fixed coordinate system into the geomagnetic field three-component under the spacecraft coordinate system; according to the method, on-orbit magnetic field interference of the spacecraft is determined by using the geomagnetic field three components and the spacecraft parameters under the spacecraft coordinate system, interference magnetic field analysis at different orbits of the spacecraft is realized based on the sub-satellite point trajectory, the ground calibration data and the geomagnetic field model, and the accuracy of magnetic field analysis is improved while the analysis steps are simplified.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft magnetic simulation, and in particular to a method, device and equipment for on-orbit magnetic simulation of a spacecraft. Background Art

[0002] For space magnetic field detection, the interference magnetic field of a spacecraft itself can affect the accuracy of space magnetic field detection. The interference magnetic field of a spacecraft on the space magnetic field detection payload includes residual magnetic field, stray magnetic field, and sensed magnetic field. The residual magnetic field and stray magnetic field of a spacecraft are only related to the operating state of the spacecraft itself, while the sensed magnetic field varies with the magnetic field environment of the spacecraft's orbit and the spacecraft's attitude.

[0003] To reduce or eliminate the effects of interfering magnetic fields, traditional methods often use non-magnetic extension rods to place onboard magnetometers far away from the satellite platform. The interfering magnetic field decays as the cube of the distance, and at the magnetometer location, it decays to below the magnetometer's background noise or below the noise index required by the magnetic measurement indicators. This solution requires a longer non-magnetic extension rod, which places higher demands on the spacecraft structure. At the same time, the extension rod structure also increases the complexity of the structure, power supply and other systems. There are also methods that use multiple probes to measure and monitor on-orbit magnetic disturbances, but this solution requires the deployment of a large number of magnetic sensors, which places higher demands on the spacecraft's power supply, space, and computing power. At the same time, axial deviations between magnetic sensors will also introduce new errors.

[0004] Therefore, how to provide a method for detecting the on-orbit magnetic properties of a spacecraft has become a technical problem that needs to be solved urgently by those skilled in the art. Summary of the Invention

[0005] The present invention provides a method, device and equipment for on-orbit magnetic simulation of a spacecraft, which are used to solve the defects in the prior art that the interference magnetic field analysis of a spacecraft at different orbits is relatively complex and has poor accuracy.

[0006] In a first aspect, the present invention provides a method for on-orbit magnetic simulation of a spacecraft, comprising:

[0007] In a zero magnetic field environment on the ground, calibrate the spacecraft parameters, which include the three components of the residual magnetic field, the three components of the stray magnetic field, and the induced magnetic field matrix;

[0008] Based on the orbital elements of the spacecraft, the orbital dynamics is used to determine the sub-satellite point trajectory of the spacecraft in orbit;

[0009] Inputting the sub-satellite point trajectory into a geomagnetic field reference model, and outputting the three components of the geomagnetic field at the spacecraft's location;

[0010] Based on the sub-satellite point trajectory of the spacecraft, converting the three components of the geomagnetic field into the three components of the geomagnetic field in an earth-fixed coordinate system;

[0011] Based on the yaw angle, pitch angle and roll angle of the spacecraft, the three components of the geomagnetic field in the Earth-fixed coordinate system are converted to the three components of the geomagnetic field in the spacecraft coordinate system;

[0012] The magnetic field interference of the spacecraft on orbit is determined by using the three components of the geomagnetic field, the three components of the residual magnetic field, the three components of the stray magnetic field and the induced magnetic field matrix in the spacecraft coordinate system.

[0013] According to a spacecraft on-orbit magnetic simulation method provided by the present invention, the magnetic field interference of the spacecraft on-orbit is determined by using the three components of the geomagnetic field, the three components of the residual magnetic field, the three components of the stray magnetic field, and the induced magnetic field matrix in the spacecraft coordinate system, including:

[0014] Calculate the magnetic field interference of the spacecraft on the space magnetic field detection payload by using the three components of the geomagnetic field, the three components of the residual magnetic field, the three components of the stray magnetic field and the induced magnetic field matrix in the spacecraft coordinate system;

[0015] The magnetic field interference of the spacecraft on orbit is determined based on the magnetic field interference of the spacecraft on orbit on the space magnetic field detection payload and the three components of the geomagnetic field in the spacecraft coordinate system.

[0016] According to a method for on-orbit magnetic simulation of a spacecraft provided by the present invention, calibrating spacecraft parameters in a zero magnetic field environment on the ground includes:

[0017] In a zero magnetic field environment on the ground, the three components of the spacecraft's residual magnetic field are calibrated using the equatorial mapping method. The three components of the spacecraft's stray magnetic field are determined by switching between different operating conditions using the equatorial mapping method.

[0018] A standard magnetic field is applied to the spacecraft on the ground, and a corresponding induced magnetic field matrix of the spacecraft under the standard magnetic field is determined.

[0019] According to a method for on-orbit magnetic simulation of a spacecraft provided by the present invention, the sub-satellite point trajectory includes: longitude and latitude;

[0020] The converting of the three components of the geomagnetic field into the three components of the geomagnetic field in an earth-fixed coordinate system based on the sub-satellite point trajectory of the spacecraft includes:

[0021]

[0022] in, represents the three components of the geomagnetic field in the earth-fixed coordinate system, represents the three components of the geomagnetic field at the spacecraft's location, θ represents longitude, Indicates latitude.

[0023] According to a spacecraft on-orbit magnetic simulation method provided by the present invention, the three components of the geomagnetic field in the Earth-fixed coordinate system are converted to the three components of the geomagnetic field in the spacecraft coordinate system based on the yaw angle, pitch angle and roll angle of the spacecraft, including:

[0024]

[0025] in, represents the three components of the geomagnetic field in the spacecraft coordinate system, Represents the three components of the geomagnetic field in the earth-fixed coordinate system, α represents the yaw angle, β represents the pitch angle, and γ represents the roll angle.

[0026] According to a spacecraft on-orbit magnetic simulation method provided by the present invention, the magnetic field interference of the spacecraft on the space magnetic field detection payload is calculated by using the three components of the geomagnetic field, the three components of the residual magnetic field, the three components of the stray magnetic field, and the induced magnetic field matrix in the spacecraft coordinate system, including:

[0027]

[0028] in, It represents the magnetic field interference of the spacecraft on orbit to the space magnetic field detection payload. represents the induced magnetic field matrix, represents the three components of the geomagnetic field in the spacecraft coordinate system, represents the three components of the residual magnetic field, Represents the three components of the stray magnetic field.

[0029] According to a spacecraft on-orbit magnetic simulation method provided by the present invention, the magnetic field interference of the spacecraft on-orbit is determined based on the magnetic field interference of the spacecraft on-orbit on the space magnetic field detection payload and the three components of the geomagnetic field in the spacecraft coordinate system, including:

[0030]

[0031] in, represents the magnetic field disturbance of the spacecraft in orbit, It represents the magnetic field interference of the spacecraft on orbit to the space magnetic field detection payload. Represents the three components of the geomagnetic field in the spacecraft coordinate system.

[0032] According to a method for on-orbit magnetic simulation of a spacecraft provided by the present invention, the orbital elements include at least one of the semi-major axis, eccentricity, inclination, right ascension of the ascending node, and argument of perigee of the spacecraft orbit.

[0033] In a second aspect, the present invention provides an on-orbit magnetic simulation device for a spacecraft, comprising:

[0034] The calibration module is used to calibrate the spacecraft parameters in a zero-magnetic field environment on the ground. The spacecraft parameters include the three components of the residual magnetic field, the three components of the stray magnetic field, and the induced magnetic field matrix;

[0035] A calculation module is used to determine the sub-satellite point trajectory of the spacecraft on orbit using orbital dynamics based on the number of spacecraft orbit elements;

[0036] a conversion module, configured to input the sub-satellite point trajectory into a geomagnetic field reference model and output the three components of the geomagnetic field at the spacecraft's location; based on the sub-satellite point trajectory of the spacecraft, convert the three components of the geomagnetic field into the three components of the geomagnetic field in an Earth-fixed coordinate system; and based on the yaw, pitch, and roll angles of the spacecraft, convert the three components of the geomagnetic field in the Earth-fixed coordinate system into the three components of the geomagnetic field in the spacecraft coordinate system;

[0037] The determination module is used to determine the magnetic field interference of the spacecraft on orbit by using the three components of the geomagnetic field, the three components of the residual magnetic field, the three components of the stray magnetic field and the induced magnetic field matrix in the spacecraft coordinate system.

[0038] In a third aspect, the present invention also provides an electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, the method for in-orbit magnetic simulation of a spacecraft as described above is implemented.

[0039] In a fourth aspect, the present invention further provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements any of the above-described methods for in-orbit magnetic simulation of a spacecraft.

[0040] In a fifth aspect, the present invention further provides a computer program product, comprising a computer program, which, when executed by a processor, implements any of the above-mentioned methods for on-orbit magnetic simulation of a spacecraft.

[0041] The present invention provides a method, device and equipment for on-orbit magnetic simulation of a spacecraft. The method comprises the following steps: calibrating spacecraft parameters in a zero magnetic field environment on the ground, the spacecraft parameters including three components of the remanent magnetic field, three components of the stray magnetic field and a sensed magnetic field matrix; determining the sub-satellite point trajectory of the spacecraft on orbit using orbital dynamics according to the number of spacecraft orbit elements; inputting the sub-satellite point trajectory into a geomagnetic field reference model, and outputting the three components of the geomagnetic field at the spacecraft's location; converting the three components of the geomagnetic field into three components of the geomagnetic field in an earth-fixed coordinate system based on the sub-satellite point trajectory of the spacecraft; converting the three components of the geomagnetic field in the earth-fixed coordinate system into three components of the geomagnetic field in the spacecraft coordinate system based on the yaw angle, pitch angle and roll angle of the spacecraft; and determining the magnetic field interference of the spacecraft on orbit using the three components of the geomagnetic field, three components of the remanent magnetic field, three components of the stray magnetic field and the sensed magnetic field matrix in the spacecraft coordinate system. By adopting a coordinate conversion method, interference magnetic field analysis at different orbits of the spacecraft is ultimately achieved based on the sub-satellite point trajectory, ground calibration data and the geomagnetic field model, thereby simplifying the analysis steps and improving the accuracy of the magnetic field analysis. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] In order to more clearly illustrate the technical solutions in the present invention or the prior art, a brief introduction is given below to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0043] Figure 1 1 is a flow chart of the on-orbit magnetic simulation method for a spacecraft provided in this embodiment;

[0044] Figure 2 Schematic diagram of the relationship between the three components of the geomagnetic field and the Earth-fixed coordinate system at the position of the spacecraft provided in this embodiment;

[0045] Figure 3 Schematic diagram of the structure of the on-orbit magnetic simulation device for spacecraft provided in this embodiment;

[0046] Figure 4 It is a structural diagram of the electronic device provided in this embodiment. DETAILED DESCRIPTION

[0047] To make the objectives, technical solutions, and advantages of the present invention more clear, the technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0048] Figure 1 4 is a flow chart of the on-orbit magnetic simulation method for spacecraft provided in this embodiment.

[0049] like Figure 1 As shown, the on-orbit magnetic simulation method for a spacecraft provided by an embodiment of the present invention mainly includes the following steps:

[0050] 101. In a zero magnetic field environment on the ground, calibrate the spacecraft parameters, which include the three components of the residual magnetic field, the three components of the stray magnetic field, and the induced magnetic field matrix.

[0051] In a specific implementation process, the spacecraft remanent magnetic field B is first calibrated using the equatorial mapping method in a zero magnetic field environment on the ground. re The three components of

[0052] Use the equatorial mapping method to switch between different working conditions to obtain the spacecraft stray magnetic field B stray The three components of

[0053] A standard magnetic field is applied to the spacecraft on the ground to obtain the corresponding magnetic field matrix A of the spacecraft under the standard magnetic field.

[0054] 102. Based on the orbital elements of the spacecraft, orbital dynamics is used to determine the sub-satellite trajectory of the spacecraft in orbit.

[0055] The subsatellite point trajectory includes longitude θ, latitude and height h. The orbital elements include parameters such as the semi-major axis, eccentricity, inclination, right ascension of the ascending node, and argument of perigee. Based on the orbital elements, the sub-satellite trajectory of the spacecraft in orbit is determined using methods such as orbital dynamics or double elements. It should be noted that the specific method for obtaining the sub-satellite trajectory will not be described in detail. Any method can be used as long as the longitude θ and latitude in the sub-satellite trajectory can be obtained. That's it.

[0056] 103. Input the sub-satellite point trajectory to the geomagnetic field reference model and output the three components of the geomagnetic field at the spacecraft location.

[0057] Using geomagnetic field reference models such as IGRF or WMM, the three components of the geomagnetic field at the location of the spacecraft can be calculated. The specific calculation process is to input the longitude and latitude of the sub-satellite point trajectory into the geomagnetic field reference model. The geomagnetic field reference model, after its own calculation, outputs the three components of the geomagnetic field at the location of the corresponding spacecraft. Among them, the three components of the geomagnetic field include the vertical component, the east component and the north component, which are recorded as

[0058] 104. Based on the sub-satellite point trajectory of the spacecraft, convert the three components of the geomagnetic field into the three components of the geomagnetic field in the earth-fixed coordinate system.

[0059] The three components of the geomagnetic field at the spacecraft's location are converted to the Earth-fixed coordinate system using formula (1);

[0060]

[0061] in, represents the three components of the geomagnetic field in the earth-fixed coordinate system, represents the three components of the geomagnetic field at the spacecraft's location, θ represents longitude, Indicates latitude.

[0062] like Figure 2 As shown in Figure 1, it is a schematic diagram of the relationship between the three components of the geomagnetic field at the spacecraft's location and the Earth-fixed coordinate system.

[0063] 105. Based on the yaw angle, pitch angle and roll angle of the spacecraft, the three components of the geomagnetic field in the earth-fixed coordinate system are converted to the three components of the geomagnetic field in the spacecraft coordinate system.

[0064] Determine the yaw, pitch, and roll angles of the spacecraft, and then convert the three components of the geomagnetic field in the Earth-fixed coordinate system to the three components of the geomagnetic field in the spacecraft coordinate system using formula (2);

[0065]

[0066] in, represents the three components of the geomagnetic field in the spacecraft coordinate system, Represents the three components of the geomagnetic field in the earth-fixed coordinate system, α represents the yaw angle, β represents the pitch angle, and γ represents the roll angle.

[0067] 106. The magnetic field interference of the spacecraft on orbit is determined by using the three components of the geomagnetic field, the three components of the residual magnetic field, the three components of the stray magnetic field and the induced magnetic field matrix in the spacecraft coordinate system.

[0068] After obtaining the three components of the geomagnetic field in the spacecraft coordinate system, the three components of the geomagnetic field, the three components of the remanent magnetic field, the three components of the stray magnetic field, and the induced magnetic field matrix in the spacecraft coordinate system are used to calculate the magnetic field interference of the spacecraft on the space magnetic field detection payload, as shown in formula (3):

[0069]

[0070] in, It represents the magnetic field interference of the spacecraft on orbit to the space magnetic field detection payload. represents the magnetic field matrix, represents the three components of the geomagnetic field in the spacecraft coordinate system, represents the three components of the residual magnetic field, Represents the three components of the stray magnetic field.

[0071] Then, based on the magnetic field interference of the spacecraft on orbit to the space magnetic field detection payload and the three components of the geomagnetic field in the spacecraft coordinate system, the magnetic field interference of the spacecraft on orbit is determined, as shown in formula (4):

[0072]

[0073] in, represents the magnetic field disturbance of the spacecraft in orbit, It represents the magnetic field interference of the spacecraft on orbit to the space magnetic field detection payload. Represents the three components of the geomagnetic field in the spacecraft coordinate system.

[0074] This embodiment is based on spacecraft ground test calibration data and the geomagnetic field model, which can realize the interference magnetic field analysis at different orbits of the spacecraft and efficiently, accurately and quickly evaluate the magnetic characteristics of the spacecraft on orbit.

[0075] Based on the same general inventive concept, the present invention also protects an on-orbit magnetic simulation device for spacecraft. The on-orbit magnetic simulation device for spacecraft provided by the present invention is described below. The on-orbit magnetic simulation device for spacecraft described below and the on-orbit magnetic simulation method for spacecraft described above can be referenced to each other.

[0076] Figure 3 Schematic diagram of the structure of the on-orbit magnetic simulation device for spacecraft provided in this embodiment.

[0077] like Figure 3 As shown, this embodiment provides a spacecraft on-orbit magnetic simulation device, including:

[0078] The calibration module 301 is used to calibrate the spacecraft parameters in a zero magnetic field environment on the ground. The spacecraft parameters include the three components of the residual magnetic field, the three components of the stray magnetic field, and the induced magnetic field matrix.

[0079] A calculation module 302 is configured to determine the sub-satellite point trajectory of the spacecraft on orbit using orbital dynamics based on the orbital elements of the spacecraft;

[0080] The conversion module 303 is configured to input the sub-satellite point trajectory into the geomagnetic field reference model and output the three components of the geomagnetic field at the spacecraft's location; based on the sub-satellite point trajectory of the spacecraft, convert the three components of the geomagnetic field to the three components of the geomagnetic field in the Earth-fixed coordinate system; based on the yaw, pitch, and roll angles of the spacecraft, convert the three components of the geomagnetic field in the Earth-fixed coordinate system to the three components of the geomagnetic field in the spacecraft coordinate system;

[0081] The determination module 304 is used to determine the magnetic field interference of the spacecraft on orbit using the three components of the geomagnetic field, the three components of the remanent magnetic field, the three components of the stray magnetic field and the induced magnetic field matrix in the spacecraft coordinate system.

[0082] Figure 4Schematic diagram of the structure of the electronic device provided in this embodiment.

[0083] like Figure 4 As shown, the electronic device may include: a processor (processor) 410, a communication interface (Communications Interface) 420, a memory (memory) 430 and a communication bus 440, wherein the processor 410, the communication interface 420, and the memory 430 communicate with each other through the communication bus 440. The processor 410 can call the logic instructions in the memory 430 to execute the spacecraft on-orbit magnetic simulation method, which includes: calibrating the spacecraft parameters in a zero magnetic field environment on the ground, the spacecraft parameters including the three components of the residual magnetic field, the three components of the stray magnetic field and the sensed magnetic field matrix; determining the sub-satellite point trajectory of the spacecraft on orbit using orbital dynamics according to the number of spacecraft orbit elements; inputting the sub-satellite point trajectory into the geomagnetic field reference model, and outputting the three components of the geomagnetic field at the spacecraft's location; based on the sub-satellite point trajectory of the spacecraft, converting the three components of the geomagnetic field into the three components of the geomagnetic field in the earth-fixed coordinate system; based on the yaw angle, pitch angle and roll angle of the spacecraft, converting the three components of the geomagnetic field in the earth-fixed coordinate system into the three components of the geomagnetic field in the spacecraft coordinate system; and determining the magnetic field interference of the spacecraft on orbit using the three components of the geomagnetic field in the spacecraft coordinate system, the three components of the residual magnetic field, the three components of the stray magnetic field and the sensed magnetic field matrix.

[0084] In addition, the logic instructions in the above-mentioned memory 430 can be implemented in the form of a software functional unit and can be stored in a computer-readable storage medium when sold or used as an independent product. Based on this understanding, the technical solution of the present invention is essentially or the part that contributes to the prior art or the part of the technical solution can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions for enabling a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: various media that can store program codes, such as a USB flash drive, a mobile hard disk, a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk.

[0085] On the other hand, the present invention also provides a computer program product, which includes a computer program, which can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the spacecraft on-orbit magnetic simulation method provided by the above-mentioned methods, the method including: calibrating spacecraft parameters in a zero magnetic field environment on the ground, the spacecraft parameters including the three components of the residual magnetic field, the three components of the stray magnetic field and the sensed magnetic field matrix; determining the sub-satellite point trajectory of the spacecraft on orbit using orbital dynamics according to the number of spacecraft orbit elements; inputting the sub-satellite point trajectory into a geomagnetic field reference model, and outputting the three components of the geomagnetic field at the position of the spacecraft; based on the sub-satellite point trajectory of the spacecraft, converting the three components of the geomagnetic field into the three components of the geomagnetic field in the earth-fixed coordinate system; based on the yaw angle, pitch angle and roll angle of the spacecraft, converting the three components of the geomagnetic field in the earth-fixed coordinate system into the three components of the geomagnetic field in the spacecraft coordinate system; using the three components of the geomagnetic field in the spacecraft coordinate system, the three components of the residual magnetic field, the three components of the stray magnetic field and the sensed magnetic field matrix, to determine the magnetic field interference of the spacecraft on orbit.

[0086] On the other hand, the present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, is implemented to execute the spacecraft on-orbit magnetic simulation method provided by the above-mentioned methods, the method comprising: calibrating spacecraft parameters in a zero magnetic field environment on the ground, the spacecraft parameters including the three components of the residual magnetic field, the three components of the stray magnetic field and the sensed magnetic field matrix; determining the sub-satellite point trajectory of the spacecraft on orbit using orbital dynamics according to the number of spacecraft orbit elements; inputting the sub-satellite point trajectory into a geomagnetic field reference model, and outputting the three components of the geomagnetic field at the position of the spacecraft; based on the sub-satellite point trajectory of the spacecraft, converting the three components of the geomagnetic field into the three components of the geomagnetic field in an earth-fixed coordinate system; based on the yaw angle, pitch angle and roll angle of the spacecraft, converting the three components of the geomagnetic field in the earth-fixed coordinate system into the three components of the geomagnetic field in the spacecraft coordinate system; and determining the magnetic field interference of the spacecraft on orbit using the three components of the geomagnetic field in the spacecraft coordinate system, the three components of the residual magnetic field, the three components of the stray magnetic field and the sensed magnetic field matrix.

[0087] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separate, and the components shown as units may or may not be physical units, i.e., they may be located in one location or distributed across multiple network units. Some or all of the modules may be selected based on actual needs to achieve the objectives of the present embodiment. Persons of ordinary skill in the art will be able to understand and implement the present invention without inventive effort.

[0088] Through the description of the above embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus a necessary general hardware platform, or of course, by hardware. Based on this understanding, the essence of the above technical solution or the part that contributes to the existing technology can be embodied in the form of a software product. The computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a magnetic disk, an optical disk, etc., and includes a number of instructions for enabling a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or certain parts of the embodiments.

[0089] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. A method for on-orbit magnetic simulation of a spacecraft, characterized in that: include: In a zero magnetic field environment on the ground, calibrate the spacecraft parameters, which include the three components of the residual magnetic field, the three components of the stray magnetic field and the induced magnetic field matrix; Based on the orbital elements of the spacecraft, orbital dynamics is used to determine the sub-satellite point trajectory of the spacecraft in orbit; Inputting the sub-satellite point trajectory into the geomagnetic field reference model, and outputting the three components of the geomagnetic field at the position of the spacecraft; Based on the sub-satellite point trajectory of the spacecraft, converting the three components of the geomagnetic field into the three components of the geomagnetic field in an earth-fixed coordinate system; Based on the yaw angle, pitch angle and roll angle of the spacecraft, the three components of the geomagnetic field in the earth-fixed coordinate system are converted into the three components of the geomagnetic field in the spacecraft coordinate system; The magnetic field interference of the spacecraft on orbit is determined by using the three components of the geomagnetic field, the three components of the residual magnetic field, the three components of the stray magnetic field and the induced magnetic field matrix in the spacecraft coordinate system.

2. The on-orbit magnetic simulation method for spacecraft according to claim 1, characterized in that: The method of determining the magnetic field interference of the spacecraft on orbit by using the three components of the geomagnetic field, the three components of the residual magnetic field, the three components of the stray magnetic field and the induced magnetic field matrix in the spacecraft coordinate system includes: The magnetic field interference of the spacecraft on the space magnetic field detection payload is calculated by using the three components of the geomagnetic field, the three components of the residual magnetic field, the three components of the stray magnetic field and the sensed magnetic field matrix in the spacecraft coordinate system; Based on the magnetic field interference of the spacecraft on the space magnetic field detection payload and the three components of the geomagnetic field in the spacecraft coordinate system, the magnetic field interference of the spacecraft on orbit is determined.

3. The on-orbit magnetic simulation method for spacecraft according to claim 1, characterized in that: The calibrating of spacecraft parameters in a zero magnetic field environment on the ground includes: In the zero magnetic field environment on the ground, the three components of the spacecraft's residual magnetic field are calibrated using the equatorial mapping method; the three components of the spacecraft's stray magnetic field are determined by switching between different working conditions using the equatorial mapping method; A standard magnetic field is applied to the spacecraft on the ground, and a corresponding induced magnetic field matrix of the spacecraft under the standard magnetic field is determined.

4. The on-orbit magnetic simulation method for spacecraft according to claim 1, characterized in that: The sub-satellite point trajectory includes: longitude and latitude; The converting of the three components of the geomagnetic field into the three components of the geomagnetic field in the earth-fixed coordinate system based on the sub-satellite point trajectory of the spacecraft includes: in, represents the three components of the geomagnetic field in the earth-fixed coordinate system, represents the three components of the geomagnetic field at the location of the spacecraft, θ represents the longitude, Indicates latitude.

5. The on-orbit magnetic simulation method for spacecraft according to claim 1, characterized in that: The converting the three components of the geomagnetic field in the earth-fixed coordinate system into the three components of the geomagnetic field in the spacecraft coordinate system based on the yaw angle, pitch angle and roll angle of the spacecraft includes: in, represents the three components of the geomagnetic field in the spacecraft coordinate system, Represents the three components of the geomagnetic field in the earth-fixed coordinate system, α represents the yaw angle, β represents the pitch angle, and γ represents the roll angle.

6. The on-orbit magnetic simulation method for spacecraft according to claim 2, characterized in that: The method uses the three components of the geomagnetic field, the three components of the residual magnetic field, the three components of the stray magnetic field and the induced magnetic field matrix in the spacecraft coordinate system to calculate the magnetic field interference of the spacecraft on the space magnetic field detection payload in orbit, including: in, It represents the magnetic field interference of the spacecraft on the space magnetic field detection payload in orbit. represents the magnetic field matrix, represents the three components of the geomagnetic field in the spacecraft coordinate system, represents the three components of the residual magnetic field, Represents the three components of the stray magnetic field.

7. The on-orbit magnetic simulation method for spacecraft according to claim 6, characterized in that: The determining of the magnetic field interference of the spacecraft on orbit based on the magnetic field interference of the spacecraft on orbit to the space magnetic field detection payload and the three components of the geomagnetic field in the spacecraft coordinate system includes: in, represents the magnetic field disturbance of the spacecraft in orbit, It represents the magnetic field interference of the spacecraft on the space magnetic field detection payload in orbit. Represents the three components of the geomagnetic field in the spacecraft coordinate system.

8. The on-orbit magnetic simulation method for spacecraft according to claim 1, characterized in that: The orbital elements include at least one of the semi-major axis, eccentricity, inclination, right ascension of ascending node, and argument of perigee of the spacecraft orbit.

9. A spacecraft on-orbit magnetic simulation device, characterized in that: include: The calibration module is used to calibrate the spacecraft parameters in a zero magnetic field environment on the ground. The spacecraft parameters include the three components of the residual magnetic field, the three components of the stray magnetic field and the induced magnetic field matrix; A calculation module is used to determine the sub-satellite point trajectory of the spacecraft on orbit using orbital dynamics based on the orbital elements of the spacecraft; A conversion module, used for inputting the sub-satellite point trajectory into a geomagnetic field reference model, and outputting the three components of the geomagnetic field at the position of the spacecraft; based on the sub-satellite point trajectory of the spacecraft, converting the three components of the geomagnetic field into the three components of the geomagnetic field in an earth-fixed coordinate system; based on the yaw angle, pitch angle and roll angle of the spacecraft, converting the three components of the geomagnetic field in the earth-fixed coordinate system into the three components of the geomagnetic field in the spacecraft coordinate system; The determination module is used to determine the magnetic field interference of the spacecraft on orbit by using the three components of the geomagnetic field, the three components of the residual magnetic field, the three components of the stray magnetic field and the induced magnetic field matrix in the spacecraft coordinate system.

10. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the program, the on-orbit magnetic simulation method for a spacecraft as described in any one of claims 1 to 8 is implemented.

Images