Satellite magnetic stability control method for on-orbit operation mode switching

Abstract

This invention relates to a satellite magnetic stability control method for on-orbit operating mode switching, belonging to the field of satellite magnetic stability control; it includes the following steps: Step 1, magnetic design of individual equipment; Step 2, measurement of magnetic moment change of individual equipment using the method of measuring the magnetic moment after demagnetization under zero magnetic field; Step 3, magnetic testing and magnetic compensation calibration of each individual equipment under each satellite operating mode; by reducing the magnetic moment change of individual equipment during satellite operating mode switching, the magnetic stability of the entire satellite is ensured during operating mode switching, so that the magnetic moment change of the entire satellite is minimized, thereby reducing the impact of satellite operating mode switching on in-situ magnetic field measurement tasks; this invention has the advantages of good control effect and high control accuracy for satellite magnetic control.

Description

Technical Field

[0001] This invention belongs to the field of satellite magnetic stability control, and relates to a satellite magnetic stability control method for switching on-orbit operating modes. Background Technology

[0002] Magnetic field parameters, as fundamental physical quantities, are commonly selected as basic elements for detection in various fields such as deep space exploration and near-Earth space environment monitoring. Space magnetic field parameter detection typically employs in-situ measurement methods using magnetometers and other magnetic field detection equipment installed on satellites. To ensure the accuracy and precision of in-situ magnetic field measurements, it is crucial to minimize interference from the satellite's own magnetism, especially changing magnetism. Therefore, satellites with magnetic field measurement missions require strict magnetic control to ensure that magnetic interference from the satellite itself meets the requirements of the exploration mission.

[0003] Satellite missions typically involve switching operating modes during different phases, which often leads to changes in the operational status of onboard equipment, such as adjustments to operating parameters, switching of operating modules, and changes in the switching status of primary and backup equipment. The magnetism of onboard equipment is generally composed of the inherent magnetism of the materials and the magnetism induced by the operating current. The magnetism induced by the operating current manifests as a magnetic moment, determined by the magnitude of the operating current and the area of ​​the loop through which it flows. Changes in the operating status of the equipment inevitably lead to changes in the magnitude of the operating current and the area of ​​the loop through which it flows, thus causing changes in the magnetic moment. Therefore, the magnetism of onboard equipment is closely related to the satellite's operating mode, especially since switching between different operating modes can cause changes in the overall magnetism of the satellite, becoming one of the main sources of interference in in-situ magnetic field measurements. Generally speaking, for a 1000 kg satellite, without dedicated magnetic control design and control, switching operating modes can sometimes cause unidirectional magnetic moment changes as large as several hundred mA·m². Such large changes in the satellite's own magnetism will cause significant interference to in-situ magnetic field measurements, which is generally unacceptable.

[0004] To address the magnetic variations caused by satellite operating mode switching, current satellite magnetic control methods typically involve measuring the magnetism of the satellite in various operating modes, performing comprehensive magnetic compensation by attaching magnetic sheets to different satellite surfaces, and conducting magnetic calibration for all operating modes to obtain an on-orbit magnetic variation model. During the satellite's on-orbit operation, this model is used to correct magnetic field measurement data. However, due to the significant magnetic variations between operating modes and limitations imposed by ground calibration test conditions and equipment accuracy, the accuracy of the model obtained from actual calibration tests is limited. This results in low accuracy for on-orbit data correction using the calibration magnetic model of each operating mode, leading to a decrease in the accuracy of in-situ magnetic field detection, particularly impacting high-precision magnetic field measurement missions. Summary of the Invention

[0005] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a satellite magnetic stability control method for on-orbit working mode switching, which has the advantages of good control effect and high control accuracy in satellite magnetic control.

[0006] The solution of the present invention is:

[0007] A satellite magnetic stability control method for on-orbit operating mode switching includes:

[0008] Step 1: Perform magnetic design for standalone equipment:

[0009] When wiring a single-unit circuit board module, the positive and negative power return lines of the module should be wired in parallel and close together while ensuring a safe distance, so as to reduce the loop area occupied by the positive and negative power return lines.

[0010] The power leads from the chassis to the circuit board are made of twisted pair, with reduced twist pitch and twist length.

[0011] When a single machine is designed as a primary backup, a symmetrical layout is adopted.

[0012] Step 2: Measure the change in magnetic moment of a single machine using the method of measuring the demagnetized magnetic moment under zero magnetic field:

[0013] Given n operating modes for a single device, the magnetic moment changes during mode transitions are obtained by subtracting the magnetic moments of each operating mode, denoted as {Δm}. xikm , Δm yikm , Δm zikm}; where k and m are the working mode numbers; according to {Δm xikm , Δm yikm , Δm zikm Determine whether a single device meets the magnetic moment stability requirements; if not, compensate the magnetic moment until it meets the requirements.

[0014] Step 3: Perform magnetic testing and magnetic compensation calibration on each unit of the satellite in each operating mode:

[0015] After the development of the individual equipment is completed, the method in step two is used to carry out electromagnetic tests on the working state of each individual equipment under various working modes of the satellite, and obtain the three-component magnetic moment of the equipment under various working modes.

[0016] The reference magnetic moment of a single device is set to {m} x0i m y0i m z0i}, where i is the device serial number; calculate the change in magnetic moment of the device in other operating modes, using {Δm}. xik , Δm yik , Δmzik} represents the magnetic moment change of k groups relative to the reference operating mode;

[0017] The magnitude and direction of the current required for magnetic compensation in each direction for each individual device are calculated based on the change in magnetic moment and the parameters of the compensation coil, and a dynamic magnetic compensation parameter table for the entire satellite is generated; magnetic moment compensation is then performed based on the dynamic magnetic compensation parameter table for the entire satellite.

[0018] In the above-mentioned satellite magnetic stability control method for switching on-orbit working modes, in step one, for modules with a module current greater than 0.5A, the loop area occupied by the positive and negative power return lines is reduced by parallel close wiring.

[0019] In the aforementioned satellite magnetic stability control method for switching on-orbit operating modes, when twisted-pair cables are used for the power supply leads, the number of twisted-pair units is ensured to be an integer to avoid the situation of half a twisted-pair unit.

[0020] In the aforementioned satellite magnetic stability control method for switching on-orbit operating modes, when a primary and backup design is adopted, the primary and backup designs remain consistent to ensure minimal change in magnetic moment when switching between primary and backup.

[0021] In the aforementioned satellite magnetic stability control method for switching on-orbit operating modes, the specific method for the magnetic moment change measurement experiment in step two is as follows:

[0022] S21. Before measuring the magnetic moment of a single machine, demagnetize it. The demagnetization process is carried out with a maximum demagnetization field strength of 3mT and a demagnetization time of 1 to 10 minutes.

[0023] S22. Fabricate a test fixture; the test fixture includes a non-magnetic turntable, a non-magnetic support, and three magnetometers; the three magnetometers are placed on the non-magnetic support; the three magnetometers are arranged radially along the rotation axis of the non-magnetic turntable in a straight line, and the distances from the measurement center of the three magnetometers to the rotation axis of the non-magnetic turntable are r1, r2, and r3, respectively.

[0024] S23. In a zero magnetic field environment, place the single device under test in the center of the turntable and adjust the single device so that the center of the device is on the rotation axis of the turntable.

[0025] S24. Power on the stand-alone equipment and set the stand-alone working mode through the ground inspection equipment, so that the stand-alone equipment runs in the set working mode;

[0026] S25. Manually control the non-magnetic turntable to rotate counterclockwise, measure the magnetic field readings using three magnetometers, and calculate the magnetic moment {m} of the single-unit equipment in this operating mode using the equatorial plotting method. xik m yik m zik}, where i is the device serial number and k is the working mode serial number;

[0027] S26. Repeat S24-S25 to complete the magnetic moment measurement of the single-machine equipment in other working modes.

[0028] In the above-mentioned satellite magnetic stability control method for switching on-orbit working modes, in step S22, the distance r1 between the magnetometer closest to the single unit and the rotation axis of the non-magnetic turntable is 1.5 to 2 times the size of the single unit, the distance r3 between the magnetometer farthest from the single unit and the rotation axis of the turntable is 3.5 to 2 times the size of the single unit, and the distance r2 between the magnetometer in the middle position and the rotation axis of the turntable is (r1+r3) / 2.

[0029] In the aforementioned satellite magnetic stability control method for switching on-orbit operating modes, the measurement process in step S25 specifically includes:

[0030] Record the readings of the three components of the magnetic field strength from three magnetometers at 20° intervals. 1x B 1y B 1z}、{B 2x B 2y B 2z} and {B 3x B 3y B 3z Rotate the non-magnetic turntable until it completes a 360° rotation, and record 18 sets of magnetic field strength readings. After completing one cycle of measurement, the single-machine equipment is powered off.

[0031] In the aforementioned satellite magnetic stability control method for switching on-orbit operating modes, the method for determining whether a single device meets the magnetic moment stability requirements is as follows:

[0032] When the intermode magnetic moment variation is between 1 and 2 mA·m 2 If the inter-mode magnetic moment variation is small and meets the magnetic moment stability requirements, no further measures are taken, and the equipment can be directly put into use on satellite; if the inter-mode magnetic moment variation is between 1 and 2 mA·m 2 When the magnetic moment is not in stable condition, compensation magnetic moment is required.

[0033] The specific method for compensating for the magnetic moment is as follows:

[0034] Based on the characteristics of magnetic moment changes between equipment modes, a pre-embedded magnetic compensation coil is designed on the structural plate in the corresponding direction of the single-machine equipment chassis. The single-turn area and number of turns of the magnetic compensation coil are determined by comprehensive design based on the required magnetic moment compensation and the compensation current, providing magnetic compensation current, so that the compensation magnetic moment can be controlled by setting the current magnitude in different working modes.

[0035] In the aforementioned satellite magnetic stability control method for switching on-orbit operating modes, step three stipulates that the compensation principle is that the unidirectional magnetic moment change is less than 1–2 mA·m. 2 Reduce the change in magnetic moment in all directions.

[0036] In the aforementioned satellite magnetic stability control method for switching on-orbit operating modes, the whole-satellite dynamic magnetic compensation parameter table represents the operating status of each individual device and the compensation current parameters under any operating mode of the whole satellite.

[0037] The advantages of this invention compared to the prior art are:

[0038] (1) Compared with the conventional satellite magnetic control method, the method adopted in this invention has the characteristics of good control effect and high control accuracy;

[0039] (2) Through magnetic stability design oriented to working mode switching and ground testing, this invention controls the magnetic moment variation of single-unit equipment (including single-unit equipment used directly and single-unit equipment with magnetic compensation) under various working mode changes within 1 to 2 mA·m. 2 Internally, the magnetic moment variation under various operating modes of the entire satellite can be controlled within 20–30 mA·m. 2 Within this range, the satellite's magnetic stability is greatly improved, and the interference of in-situ magnetic field measurement caused by the switching of satellite working modes is reduced, which can better ensure the completion of deep space exploration and space environment monitoring missions.

[0040] (3) The present invention reduces the magnetic change when the satellite working mode is switched, which also reduces the difficulty of implementing high-precision magnetic field measurement tasks, such as reducing the dependence on ground calibration test and reducing the length of the extension rod used for magnetic probe extension. Attached Figure Description

[0041] Figure 1 This is a schematic diagram of the layout of the single-machine magnetic moment measurement and testing device of the present invention;

[0042] Figure 2 This is a schematic diagram of the design of the pre-embedded compensation coil in the single-unit equipment of the present invention. Detailed Implementation

[0043] The present invention will be further described below with reference to the embodiments.

[0044] This invention provides a satellite magnetic stability control method for switching on-orbit operating modes. It addresses each stage from individual device magnetic control design and testing to overall satellite magnetic control design and testing verification, establishing a method to ensure the magnetic stability of the entire satellite during on-orbit operating mode switching. First, individual device magnetic compensation parameters are obtained through individual device magnetic testing and compensation. Then, a dynamic magnetic compensation parameter table for the entire satellite is established. Individual device magnetic compensation is performed according to the compensation parameters corresponding to each operating mode, ensuring the magnetic moment stability of the satellite under various on-orbit operating mode switching conditions.

[0045] The satellite magnetic stability control method for switching on-orbit operating modes includes the following steps:

[0046] Step 1: Magnetic Design of Single-Unit Equipment

[0047] When routing modules on a single circuit board, the positive and negative power return lines of the module should be routed in parallel and close together, while ensuring a safe distance, to reduce the loop area occupied by the positive and negative power return lines. For modules with a current greater than 0.5A, the loop area occupied by the positive and negative power return lines should be reduced by routing them in parallel and close together.

[0048] The power supply leads from the chassis to the circuit board should be twisted pairs, with reduced twist pitch and twist length. When using twisted pairs for power supply leads, ensure that the number of twisted pairs is an integer to avoid using half-twisted pairs.

[0049] When a single machine is designed as a primary backup, a symmetrical layout is adopted. When a primary backup design is adopted, the primary backup design remains consistent to minimize the change in magnetic moment when switching between primary and backup.

[0050] Step 2: Measure the change in magnetic moment of a single machine using the method of measuring the demagnetized magnetic moment under zero magnetic field.

[0051] Given n operating modes for a single device, the magnetic moment changes during mode transitions are obtained by subtracting the magnetic moments of each operating mode, denoted as {Δm}. xikm , Δm yikm , Δm zikm}; where k and m are the working mode numbers; according to {Δm xikm , Δm yikm , Δm zikm Determine whether a single device meets the magnetic moment stability requirements; if not, compensate the magnetic moment until it meets the magnetic moment stability requirements.

[0052] The specific method for measuring magnetic moment change is as follows:

[0053] S21. Before measuring the magnetic moment of a single machine, demagnetize it. The demagnetization process is carried out with a maximum demagnetization field strength of 3mT and a demagnetization time of 1 to 10 minutes.

[0054] S22. Fabricate the test fixture; the test fixture includes a non-magnetic turntable, a non-magnetic support, and three magnetometers; the three magnetometers are placed on the non-magnetic support; the three magnetometers are arranged radially along the rotation axis of the non-magnetic turntable in a straight line, and the distances from the measurement center of the three magnetometers to the rotation axis of the non-magnetic turntable are r1, r2, and r3, respectively. Figure 1 As shown.

[0055] The distance r1 between the magnetometer closest to the single unit and the rotation axis of the non-magnetic turntable is 1.5 to 2 times the size of the single unit. The distance r3 between the magnetometer farthest from the single unit and the rotation axis of the turntable is 3.5 to 2 times the size of the single unit. The distance r2 between the magnetometer in the middle position and the rotation axis of the turntable is (r1+r3) / 2.

[0056] S23. In a zero magnetic field environment, place the device under test in the center of the turntable and adjust the device so that the center of the device is on the rotation axis of the turntable.

[0057] S24. Power on the stand-alone equipment and set the stand-alone working mode through the ground inspection equipment, so that the stand-alone equipment runs in the set working mode.

[0058] S25. Manually control the non-magnetic turntable to rotate counterclockwise, measure the magnetic field readings using three magnetometers, and calculate the magnetic moment {m} of the single-unit equipment in this operating mode using the equatorial plotting method. xik m yik m zik}, where i is the device serial number and k is the working mode serial number.

[0059] The measurement process is as follows:

[0060] Record the readings of the three components of the magnetic field strength from three magnetometers at 20° intervals. 1x B 1y B 1z}、{B 2x B 2y B 2z} and {B 3x B 3y B 3z Rotate the non-magnetic turntable until it completes a 360° rotation, and record 18 sets of magnetic field strength readings. After completing one cycle of measurement, the single-machine equipment is powered off.

[0061] S26. Repeat S24-S25 to complete the magnetic moment measurement of the single-machine equipment in other working modes.

[0062] The method for determining whether a single device meets the requirements for magnetic moment stability is as follows:

[0063] When the intermode magnetic moment variation is between 1 and 2 mA·m 2If the inter-mode magnetic moment variation is small and meets the magnetic moment stability requirements, no further measures are taken, and the equipment can be directly put into use on satellite; if the inter-mode magnetic moment variation is between 1 and 2 mA·m 2 When the magnetic moment is not in stable condition, compensation magnetic moment is required.

[0064] The specific method for compensating for the magnetic moment is as follows:

[0065] Based on the characteristics of magnetic moment changes between equipment modes, pre-embedded magnetic compensation coils are designed on the structural plate of the corresponding direction of the single-machine equipment chassis, such as... Figure 2 As shown. The area and number of turns of the magnetic compensation coil are determined by a comprehensive design based on the required magnetic moment to be compensated and the compensation current. This provides the magnetic compensation current, allowing the compensation magnetic moment to be controlled by setting the current magnitude in different operating modes.

[0066] Step 3: Magnetic testing and magnetic compensation calibration of each unit's equipment under various satellite operating modes.

[0067] After the individual equipment is developed, the method in step two is used to conduct electromagnetic tests on the working state of each individual unit under various working modes of the satellite, and obtain the three-component magnetic moment of the equipment under various working modes.

[0068] The reference magnetic moment of a single device is set to {m} x0i m y0i m z0i}, where i is the device serial number; calculate the change in magnetic moment of the device in other operating modes, using {Δm}. xik , Δm yik , Δm zik} represents the change in magnetic moment of group k relative to the reference operating mode, where k is the operating mode number;

[0069] The magnitude and direction of the current required for magnetic compensation in each direction for each individual device are calculated based on the change in magnetic moment and the parameters of the compensation coil, and a dynamic magnetic compensation parameter table for the entire satellite is generated; magnetic moment compensation is then performed based on the dynamic magnetic compensation parameter table for the entire satellite.

[0070] The compensation principle is that the change in magnetic moment in one direction is less than 1 to 2 mA·m. 2 Reduce the change in magnetic moment in all directions.

[0071] The whole satellite dynamic magnetic compensation parameter table shows the working status of each individual device and the compensation current parameters under any working mode of the whole satellite.

[0072] Example

[0073] Taking a certain space environment monitoring satellite as an example, this invention describes the specific implementation steps and methods of the present invention regarding the design and implementation process of satellite magnetic stability control during on-orbit operation mode switching:

[0074] 1) Single-unit equipment design stage:

[0075] First, classify the individual devices according to the magnitude of magnetic changes in various satellite operating modes to determine which individual devices meet the requirements and can be used directly, and which require magnetic compensation.

[0076] For stand-alone equipment requiring magnetic compensation, the design of the embedded magnetic compensation coil in the stand-alone chassis structure should be completed according to the magnetic compensation requirements.

[0077] 2) Magnetic testing and magnetic compensation calibration of stand-alone equipment

[0078] According to the magnetic test specifications for single-unit equipment, power-on tests were conducted on the equipment under various working modes in a zero-magnetic test chamber to obtain the three-component magnetic moments of the equipment under various working modes.

[0079] Determine the baseline state of the commonly used modes of the single-unit equipment, and subtract the magnetic moment of the equipment in other operating modes from the magnetic moment in the baseline mode to obtain the change in the magnetic moment of the equipment in various satellite modes.

[0080] Based on the change in magnetic moment between equipment modes, and combined with the design parameters of the magnetic compensation coil (including single-turn area, number of turns, etc.), the magnetic compensation parameters are calculated, including the magnitude and direction of the magnetic compensation current, to ensure that the magnetic moment generated by the magnetic compensation coil offsets the change in magnetic moment between equipment modes as much as possible, so as to achieve the purpose of magnetic stability of the single equipment in various working modes.

[0081] Taking the parameter calculation of a single device i in the X direction as an example, let S be the area of ​​a single turn of the magnetic compensation coil winding in the X direction. xi The number of coil turns is n xi The compensation current I under operating mode k xi for:

[0082] I xi =Δm xik / (S xi ·n xi )

[0083] The direction of the compensation current is determined by the left-handed relationship between the current flow direction and the direction of magnetic moment change.

[0084] This step can be performed in one, two, or three directions, depending on the magnetic compensation direction required by the standalone device.

[0085] Based on the calculated magnetic compensation parameters, a single-machine magnetic compensation calibration test is carried out. The specific procedure is as follows: under the condition of applying the corresponding magnetic compensation current to the equipment, magnetic compensation tests are carried out on various working modes according to the implementation method in step a). Based on the test results, the magnetic compensation parameters in each direction of the single machine are adjusted to ensure that the change of magnetic moment between modes in each direction is controlled within the required range.

[0086] For all individual devices on the satellite that require magnetic compensation, repeat steps a), b), c), and d) to obtain the magnetic compensation parameters for all individual devices on the satellite that require magnetic compensation.

[0087] 3) Establishment of the whole satellite dynamic magnetic compensation parameter table

[0088] A table of dynamic magnetic compensation parameters for each individual device corresponding to various satellite operating modes was established. Table 1 provides an example of the magnetic compensation parameters for the entire satellite.

[0089] Table 1. Dynamic Magnetic Compensation Parameters for the Entire Satellite (Example)

[0090]

[0091] 4) Verification of magnetic stability during satellite operating mode switching

[0092] In accordance with the overall satellite magnetic test specifications, magnetic moment compensation verification was conducted under zero-magnetic laboratory conditions in various operating modes of the entire satellite. The satellite set the magnetic compensation parameters for each individual component according to the established operating mode, and the overall magnetic stability of the satellite under various operating modes was observed through a ground-based magnetic testing system to determine whether it met the requirements.

[0093] 5) In-orbit application.

[0094] During the satellite's operation in orbit, based on the dynamic magnetic compensation parameter table of the entire satellite verified by the ground magnetic test, the corresponding magnetic compensation parameters of each individual device are automatically set for each working mode to ensure that the satellite's magnetic stability meets the requirements under various working modes.

[0095] Compared with conventional satellite magnetic control methods, the method employed in this invention has the advantages of better control effect and higher control accuracy. Through magnetic stability design oriented towards operating mode switching and ground testing, the magnetic moment variation of individual equipment (including single-unit operation and single-unit operation with magnetic compensation) under various operating mode changes is controlled within 1-2 mA·m. 2 Internally, the magnetic moment variation under various operating modes of the entire satellite can be controlled within 20–30 mA·m. 2 Within this range, the satellite's magnetic stability is greatly improved, and interference with in-situ magnetic field measurements caused by switching satellite operating modes is reduced, thus better ensuring the completion of deep space exploration and space environment monitoring missions. At the same time, because the magnetic changes decrease when the satellite switches operating modes, the difficulty of implementing high-precision magnetic field measurement missions is also reduced, such as reducing reliance on ground calibration tests and decreasing the length of the extension rod used for magnetic probe extension.

[0096] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A satellite magnetic stability control method for on-orbit operating mode switching, characterized in that: include: Step 1: Perform magnetic design for standalone equipment: When wiring a single-unit circuit board module, the positive and negative power return lines of the module should be wired in parallel and close together while ensuring a safe distance, so as to reduce the loop area occupied by the positive and negative power return lines. The power leads from the chassis to the circuit board are made of twisted pair, with reduced twist pitch and twist length. When a single machine is designed as a primary backup, a symmetrical layout is adopted. Step 2: Measure the change in magnetic moment of a single machine using the method of measuring the demagnetized magnetic moment under zero magnetic field: Given n operating modes for a single device, the magnetic moment changes during mode transitions are obtained by subtracting the magnetic moments of each operating mode, denoted as {Δm}. xikm , Δm yikm , Δm zikm }; where k and m are the working mode numbers; according to {Δm xikm , Δm yikm , Δm zikm Determine whether a single device meets the magnetic moment stability requirements; if not, compensate the magnetic moment until it meets the requirements. Step 3: Perform magnetic testing and magnetic compensation calibration on each unit of the satellite in each operating mode: After the development of the individual equipment is completed, the method in step two is used to carry out electromagnetic tests on the working state of each individual equipment under various working modes of the satellite, and obtain the three-component magnetic moment of the equipment under various working modes. The reference magnetic moment of a single device is set to {m} x0i m y0i m z0i }, where i is the device serial number; calculate the change in magnetic moment of the device in other operating modes, using {Δm}. xik , Δm yik , Δm zik } represents the magnetic moment change of k groups relative to the reference operating mode; The magnitude and direction of the current required for magnetic compensation in each direction for each individual device are calculated based on the change in magnetic moment and the parameters of the compensation coil, and a dynamic magnetic compensation parameter table for the entire satellite is generated; magnetic moment compensation is then performed based on the dynamic magnetic compensation parameter table for the entire satellite.

2. The satellite magnetic stability control method for on-orbit operating mode switching according to claim 1, characterized in that: In step one, for modules with a current greater than 0.5A, the loop area occupied by the positive and negative power return lines is reduced by parallel and close wiring.

3. The satellite magnetic stability control method for on-orbit operating mode switching according to claim 1, characterized in that: When using twisted-pair cables for power leads, ensure that there are an integer number of twisted-pair units to avoid using only half a twisted-pair unit.

4. The satellite magnetic stability control method for on-orbit operating mode switching according to claim 1, characterized in that: When using a primary backup design, the primary backup design remains consistent to ensure minimal change in magnetic moment when switching between primary and backup.

5. A satellite magnetic stability control method for on-orbit operating mode switching according to claim 1, characterized in that: In step two, the specific method for measuring the change in magnetic moment is as follows: S21. Before measuring the magnetic moment of a single machine, demagnetize it. The demagnetization process is carried out with a maximum demagnetization field strength of 3mT and a demagnetization time of 1 to 10 minutes. S22. Fabricate a test fixture; the test fixture includes a non-magnetic turntable, a non-magnetic support, and three magnetometers; the three magnetometers are placed on the non-magnetic support; the three magnetometers are arranged radially along the rotation axis of the non-magnetic turntable in a straight line, and the distances from the measurement center of the three magnetometers to the rotation axis of the non-magnetic turntable are r1, r2, and r3, respectively. S23. In a zero magnetic field environment, place the single device under test in the center of the turntable and adjust the single device so that the center of the device is on the rotation axis of the turntable. S24. Power on the stand-alone equipment and set the stand-alone working mode through the ground inspection equipment, so that the stand-alone equipment runs in the set working mode; S25. Manually control the non-magnetic turntable to rotate counterclockwise, measure the magnetic field readings using three magnetometers, and calculate the magnetic moment {m} of the single-unit equipment in this operating mode using the equatorial plotting method. xik m yik m zik }, where i is the device serial number and k is the working mode serial number; S26. Repeat S24-S25 to complete the magnetic moment measurement of the single-machine equipment in other working modes.

6. A satellite magnetic stability control method for on-orbit operating mode switching according to claim 5, characterized in that: In S22, the distance r1 between the magnetometer closest to the single unit and the rotation axis of the non-magnetic turntable is 1.5 to 2 times the size of the single unit, the distance r3 between the magnetometer farthest from the single unit and the rotation axis of the turntable is 3.5 to 2 times the size of the single unit, and the distance r2 between the magnetometer in the middle position and the rotation axis of the turntable is (r1+r3) / 2.

7. A satellite magnetic stability control method for on-orbit operating mode switching according to claim 5, characterized in that: In S25, the measurement process is specifically as follows: Record the three-component magnetic field strength readings from three magnetometers at 20° intervals. 1x B 1y B 1z }、{B 2x B 2y B 2z } and {B 3x B 3y B 3z Rotate the non-magnetic turntable until it completes a 360° rotation, and record 18 sets of magnetic field strength readings. After completing one cycle of measurement, the single-machine equipment is powered off.

8. A satellite magnetic stability control method for on-orbit operating mode switching according to claim 1, characterized in that: The method for determining whether a single device meets the requirements for magnetic moment stability is as follows: When the intermode magnetic moment variation is between 1 and 2 mA·m 2 If the inter-mode magnetic moment variation is small and meets the magnetic moment stability requirements, no further measures are taken, and the equipment can be directly put into use on satellite; if the inter-mode magnetic moment variation is between 1 and 2 mA·m 2 When the magnetic moment is not in stable condition, compensation magnetic moment is required. The specific method for compensating for the magnetic moment is as follows: Based on the characteristics of magnetic moment changes between equipment modes, a pre-embedded magnetic compensation coil is designed on the structural plate in the corresponding direction of the single-machine equipment chassis. The single-turn area and number of turns of the magnetic compensation coil are determined by comprehensive design based on the required magnetic moment compensation and the compensation current, providing magnetic compensation current, so that the compensation magnetic moment can be controlled by setting the current magnitude in different working modes.

9. A satellite magnetic stability control method for on-orbit operating mode switching according to claim 1, characterized in that: In step three, the compensation principle is that the change in magnetic moment in one direction is less than 1 to 2 mA·m. 2 Reduce the change in magnetic moment in all directions.

10. A satellite magnetic stability control method for on-orbit operating mode switching according to claim 1, characterized in that: The whole satellite dynamic magnetic compensation parameter table shows the working status of each individual device and the compensation current parameters under any working mode of the whole satellite.

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