Satellite dynamic magnetic compensation method and system

Abstract

The application provides a satellite dynamic magnetic compensation method and system, which comprises the following steps: performing magnetic test on the satellite to obtain the magnetic moment of the satellite under each working condition; determining the dynamic magnetic compensation magnetic moment required by the working condition of the load, so that the magnetic moment of the working condition of the load after compensation is within the interval formed by the magnetic moments under other working conditions; calculating the dynamic magnetic compensation loop area according to the dynamic magnetic compensation magnetic moment and the load power supply current under the working condition of the load, and determining the loop current direction; winding the current loop according to the loop area and the current direction requirement according to the positive line or the negative line of the load power supply cable to form the dynamic magnetic compensation loop; performing magnetic test on the satellite to confirm the dynamic magnetic compensation effect. The application solves the problem that the dynamic magnetic moment of the satellite during the intermittent work of the load cannot be effectively compensated when the satellite is statically compensated by using permanent magnetic material. The application does not need to additionally configure active magnetic compensation equipment on the satellite, and has the advantages of simplicity, economy and effective dynamic compensation of the magnetic moment during the work of the load.

Description

Technical Field

[0001] This invention relates to the field of satellite magnetic compensation technology, specifically to a satellite dynamic magnetic compensation method and system. Background Technology

[0002] When a low Earth orbit satellite is in orbit, its magnetic moment interacts with the Earth's magnetic field, generating a magnetic disturbance torque. When the satellite's magnetic moment exceeds the required specifications, this magnetic disturbance torque may cause the satellite to deviate from its orientation. Therefore, in order to verify and control the satellite's magnetic moment and ensure it meets the required specifications, magnetic testing and magnetic compensation must be performed on the satellite during ground development.

[0003] Magnetic compensation, a crucial method for satellite magnetic moment control, typically employs permanent magnets mounted on the satellite to compensate for (reduce or cancel) the magnetic moment in various directions, thereby ensuring the satellite's magnetic moment meets performance requirements. Since the magnetic moment of permanent magnets is a constant (ignoring decay), its magnetic compensation effect is the same across all satellite operating conditions. This is equivalent to adding or subtracting the same compensation magnetic moment value (a constant) under all operating conditions; therefore, this is a static magnetic compensation method. When the satellite's magnetic moment is relatively close across operating conditions, this method can effectively compensate for the satellite's magnetic moment, resulting in a smaller magnetic moment under each condition after compensation. This method is simple, mature, and currently, most satellites use this method for magnetic compensation.

[0004] Some satellites are equipped with intermittently operating payloads. When the payload is active, the satellite's magnetic moment under that condition may be larger and significantly different from that under other conditions. For example, the SAR antenna on a Synthetic Aperture Radar (SAR) satellite is briefly activated each orbit. When the SAR antenna is active, the current in the antenna generates a large stray magnetic moment (magnetic moment caused by current); when the SAR antenna is not active, no current flows through this part, and therefore no stray magnetic moment is generated. These intermittently occurring stray magnetic moments will result in the overall satellite's magnetic moment being much larger during SAR operation than under other conditions. In this case, if the static magnetic compensation method described above is used for magnetic compensation, since the compensated magnetic moment is a constant value, the following may occur: the satellite's magnetic moment may meet the requirements when the payload is active, but may fail to meet the requirements under other conditions due to overcompensation; or the satellite's magnetic moment may meet the requirements under other conditions, but may fail to meet the requirements when the payload is active due to undercompensation. In other words, static magnetic compensation using permanent magnet materials may not be able to compensate for the dynamic magnetic moment during payload operation to ensure that the satellite's magnetic moment meets the requirements under all conditions.

[0005] To address the aforementioned issues, active magnetic compensation devices are generally used to counteract the dynamic magnetic moment of the payload during operation. This method requires modifications or additions to onboard components, increasing the satellite's cost, power consumption, and weight. A literature review revealed that Yi Zhong, in his paper "Magnetic Compensation for Medium and Low Earth Orbit Satellites" ("Ring Model Technology," 1997, No. 4), summarized magnetic compensation methods for medium and low Earth orbit satellites, including ground-based use of permanent magnet materials and on-orbit use of magnetic torquers. The former is a static magnetic compensation method and cannot solve the aforementioned problems; the latter requires measuring and calculating the satellite's orbital parameters to determine the satellite's real-time magnetic moment interference, and then controlling the current of the magnetic torquer to provide the required compensating magnetic moment. Since the main function of the magnetic torquer is to unload torque from equipment such as reaction flywheels or to magnetically control the satellite, using it to compensate for the satellite's magnetic moment will inevitably reduce the efficiency of the magnetic torquer. Therefore, this method requires the magnetic torquer to have a large rated output magnetic moment. Ye Jiancheng et al., in their paper "Active Compensation Method for Internal Magnetic Field Environment of Spacecraft" (Journal of Space Science, 2020, No. 202001), proposed a method for measuring, inverting, and actively compensating the internal magnetic field of spacecraft. The measurement and inversion results serve as the input for compensation, which is achieved using a coil. Chu Zhongyi et al., in their papers "Active Magnetic Compensation of a Spin-Free Exchange Relaxation Atomic Magnetometer" (Optical Engineering, 2014, Vol. 22, No. 7) and "Experimental Study on Active Magnetic Compensation of a Space Detection Atomic Magnetometer" (Acta Aeronautica Sinica, 2014, Vol. 35, No. 9), proposed an active magnetic compensation method. This method measures magnetic field information in three directions and then uses this as feedback to adjust the current source to control the current in the coil, causing the coil to generate a compensating magnetic field that is the same magnitude but opposite in direction to the external disturbance magnetic field. Zhao Yu et al., in their paper "Aircraft Magnetic Interference Compensation Technology" (Electronic World, 2018, No. 3), summarized domestic and international magnetic interference compensation technologies, including two categories: interference measurement-based interference compensation and geomagnetic interference compensation. Both of these technologies require measuring the external interfering magnetic field and then generating a compensating magnetic field through equipment to cancel or reduce the interfering magnetic field. The above schemes can be summarized into four steps: measurement, calculation, control, and compensation. First, the environmental or interfering magnetic field is measured to obtain relevant data; then, using a magnetic field model and the obtained data, the environmental or interfering magnetic field and the required magnetic compensation value are calculated; third, based on the calculated magnetic compensation value, the power supply is controlled to adjust the current in the coil (a magnetic torquer is essentially also a coil), causing it to generate a compensating magnetic field of the same magnitude but opposite direction to the environmental or interfering magnetic field; fourth, the compensating magnetic field cancels out the environmental or interfering magnetic field, achieving the purpose of active magnetic compensation. These schemes require active magnetic compensation equipment such as measurement sensors, computing devices, current control devices, and magnetic compensation devices (coils).

[0006] Patent document CN113212811A (application number: CN202110705542.9) discloses a thermal control system compatible with dynamic magnetic compensation, including: a thermal control design module configured to obtain design parameters of a thermal control electric heater based on the functional requirements of magnetic compensation and thermal control requirements; and a thermal control electric heater configured to perform magnetic compensation and active thermal control based on the design parameters. However, this invention does not solve the problem that when using permanent magnet materials to perform static magnetic compensation on a satellite, it is impossible to effectively compensate for the dynamic magnetic moment of the satellite during intermittent payload operation. Summary of the Invention

[0007] To address the shortcomings of existing technologies, the purpose of this invention is to provide a satellite dynamic magnetic compensation method and system.

[0008] A satellite dynamic magnetic compensation method provided by the present invention includes:

[0009] Step S1: Conduct magnetic tests on the satellite to obtain the satellite's magnetic moment under various operating conditions;

[0010] Step S2: Determine the dynamic magnetic compensation moment required for the load operating condition, so that the magnetic moment under the compensated load operating condition is within the range formed by the magnetic moment under other operating conditions;

[0011] Step S3: Calculate the dynamic magnetic compensation loop area and determine the loop current direction based on the dynamic magnetic compensation magnetic moment and the load power supply current under the load operating conditions;

[0012] Step S4: Based on the positive or negative line of the load power supply cable, wind it into a current loop according to the requirements of loop area and current direction to form a dynamic magnetic compensation loop;

[0013] Step S5: Conduct a magnetic test on the satellite to confirm the effect of dynamic magnetic compensation.

[0014] Preferably, in step S1:

[0015] Let the magnetic moment of the satellite under various operating conditions be {M}. xi M yi M zi |i=1,2,…,N};

[0016] Among them, M xi M yi M zi Let L represent the components of the satellite's magnetic moment along the three orthogonal axes (x, y, z) under operating condition i; N is the operating condition number, and let i = L represent the payload's operating condition. For other operating conditions;

[0017] The load operates intermittently; it is powered on during normal operating conditions and powered off during other conditions.

[0018] Preferably, in step S2:

[0019] Select a set of dynamic compensation magnetic moments This makes the magnetic moment under the compensated load working condition Magnetic moment under other operating conditions Within the formed interval, the following conditions are met:

[0020]

[0021]

[0022]

[0023] in, These are the components of the dynamic compensation magnetic moment on the three orthogonal axes: x, y, and z; M xL M yL M zL These are the components of the magnetic moment of the satellite on the three orthogonal axes (x, y, z) when i = L, under the payload operating conditions before compensation. These refer to all operating conditions other than the load-bearing operating condition, namely... The minimum value of the components of the magnetic moment on the three orthogonal axes x, y, and z; These refer to all operating conditions other than the load-bearing operating condition, namely... The maximum value of the components of the magnetic moment on the three orthogonal axes x, y, and z;

[0024] The dynamic compensation magnetic moment affects the magnetic moment under the load working condition, but has no effect on the magnetic moment under other working conditions.

[0025] Preferably, in step S3:

[0026] Based on dynamic compensation magnetic moment Given the current I flowing through its power supply cable under load operating conditions, calculate the areas of the dynamic magnetic compensation loops on the three orthogonal axes x, y, and z, respectively:

[0027]

[0028]

[0029]

[0030] Among them, S x S y S z , respectively, represent the areas of the dynamic magnetic compensation loops on the three orthogonal axes x, y, and z; I is the current flowing through its power supply cable under load operating conditions; |·| indicates taking the absolute value;

[0031] The direction of the current in the loop on each axis is determined based on the fact that the direction of the magnetic moment generated by the current is consistent with the direction of the component of the dynamic compensation magnetic moment on that axis.

[0032] Preferably, in step S4:

[0033] The positive and negative wires of the load power supply cable are partially separated. The positive or negative wires are wound into current loops on the three orthogonal axes x, y, and z according to the loop area and current direction determined in step S3. The current loops are dynamic magnetic compensation loops.

[0034] The dynamic magnetic compensation loop on a single axis can be single or multiple. For multiple loops, the sum of the areas of each loop is the loop area determined in step S3, and the current direction in each loop is consistent with the current direction determined in step S3.

[0035] The dynamic magnetic compensation loop is wound around the load power supply cable. When the load is working, the current in the loop generates a magnetic moment, and the magnitude of the magnetic moment increases with the increase of the current in the loop. When the load is not working, there is no current in the loop and no magnetic moment is generated. The dynamic magnetic compensation loop realizes dynamic magnetic compensation for the load's working conditions and has no effect on the magnetic moment under other working conditions.

[0036] A satellite dynamic magnetic compensation system provided by the present invention includes:

[0037] Module M1: Performs magnetic tests on the satellite to obtain the satellite's magnetic moment under various operating conditions;

[0038] Module M2: Determines the dynamic magnetic compensation moment required for the load operating condition, so that the magnetic moment under the compensated load operating condition is within the range formed by the magnetic moment under other operating conditions;

[0039] Module M3: Calculate the dynamic magnetic compensation loop area and determine the loop current direction based on the dynamic magnetic compensation magnetic moment and the load supply current under load operating conditions;

[0040] Module M4: Based on the positive or negative line of the load power supply cable, wind it into a current loop according to the requirements of loop area and current direction to form a dynamic magnetic compensation loop;

[0041] Module M5: Conducts magnetic tests on the satellite to confirm the effectiveness of dynamic magnetic compensation.

[0042] Preferably, in module M1:

[0043] Let the magnetic moment of the satellite under various operating conditions be {M}. xi M yi M zi |i=1,2,…,N};

[0044] Among them, M xi M yi Mzi Let L represent the components of the satellite's magnetic moment along the three orthogonal axes (x, y, z) under operating condition i; N is the operating condition number, and let i = L represent the payload's operating condition. For other operating conditions;

[0045] The load operates intermittently; it is powered on during normal operating conditions and powered off during other conditions.

[0046] Preferably, in module M2:

[0047] Select a set of dynamic compensation magnetic moments This makes the magnetic moment under the compensated load working condition Magnetic moment under other operating conditions Within the formed interval, the following conditions are met:

[0048]

[0049]

[0050]

[0051] in, These are the components of the dynamic compensation magnetic moment on the three orthogonal axes: x, y, and z; M xL M yL M zL These are the components of the magnetic moment of the satellite on the three orthogonal axes (x, y, z) when i = L, under the payload operating conditions before compensation. These refer to all operating conditions other than the load-bearing operating condition, namely... The minimum value of the components of the magnetic moment on the three orthogonal axes x, y, and z; These refer to all operating conditions other than the load-bearing operating condition, namely... The maximum value of the components of the magnetic moment on the three orthogonal axes x, y, and z;

[0052] The dynamic compensation magnetic moment affects the magnetic moment under the load working condition, but has no effect on the magnetic moment under other working conditions.

[0053] Preferably, in module M3:

[0054] Based on dynamic compensation magnetic moment Given the current I flowing through its power supply cable under load operating conditions, calculate the areas of the dynamic magnetic compensation loops on the three orthogonal axes x, y, and z, respectively:

[0055]

[0056]

[0057]

[0058] Among them, S x S y S z , respectively, represent the areas of the dynamic magnetic compensation loops on the three orthogonal axes x, y, and z; I is the current flowing through its power supply cable under load operating conditions; |·| indicates taking the absolute value;

[0059] The direction of the current in the loop on each axis is determined based on the fact that the direction of the magnetic moment generated by the current is consistent with the direction of the component of the dynamic compensation magnetic moment on that axis.

[0060] Preferably, in module M4:

[0061] The positive and negative wires of the load power supply cable are partially separated, and the positive or negative wires are wound into current loops on the three orthogonal axes of x, y, and z according to the loop area and current direction determined by module M3. The current loops are dynamic magnetic compensation loops.

[0062] The dynamic magnetic compensation loop on a single axis can be single or multiple. For multiple loops, the sum of the areas of each loop is the loop area determined in module M3, and the current direction in each loop is consistent with the current direction determined in module M3.

[0063] The dynamic magnetic compensation loop is wound around the load power supply cable. When the load is working, the current in the loop generates a magnetic moment, and the magnitude of the magnetic moment increases with the increase of the current in the loop. When the load is not working, there is no current in the loop and no magnetic moment is generated. The dynamic magnetic compensation loop realizes dynamic magnetic compensation for the load's working conditions and has no effect on the magnetic moment under other working conditions.

[0064] Compared with the prior art, the present invention has the following beneficial effects:

[0065] 1. This invention solves the problem that when using permanent magnet materials to perform static magnetic compensation on satellites, it is impossible to effectively compensate for the dynamic magnetic moment of the satellite when the payload operates intermittently;

[0066] 2. This invention does not require additional magnetic compensation active control equipment on the satellite, and has the advantages of being simple, economical, and able to effectively and dynamically compensate for the magnetic moment of the payload during operation. Attached Figure Description

[0067] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0068] Figure 1 This is a flowchart of the steps of the present invention. Detailed Implementation

[0069] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0070] Example 1:

[0071] This invention provides a simple, economical and effective method for dynamic magnetic compensation of satellites. This method directly utilizes the existing cables on the satellite to dynamically compensate the magnetic moment of the satellite with intermittent payload operation. It does not require additional active magnetic compensation equipment, nor does it require any changes or additions to the satellite's product accessories. It has the advantages of being simple, economical and able to effectively compensate the magnetic moment of the payload during operation.

[0072] This invention provides a satellite dynamic magnetic compensation method, such as... Figure 1 As shown, it includes the following steps:

[0073] Step 1: Conduct magnetic tests on the satellite to obtain its magnetic moment under various operating conditions;

[0074] Step 2: Determine the dynamic magnetic compensation moment required for the load operating condition, so that the compensated magnetic moment under this condition is within the range formed by the magnetic moments under other operating conditions;

[0075] Step 3: Calculate the dynamic magnetic compensation loop area and determine the current direction in the loop based on the dynamic magnetic compensation magnetic moment and the load supply current under the load operating conditions;

[0076] Step 4: Using the positive or negative wire of the load power supply cable, wind it into a current loop according to the requirements of loop area and current direction, thus forming a dynamic magnetic compensation loop.

[0077] Step 5: Conduct another magnetic test on the satellite to confirm the effect of dynamic magnetic compensation.

[0078] In step 1, specifically: the magnetic moment of the satellite under various operating conditions is denoted as {M}. xi M yi M zi |i=1,2,…,N}. Where M xi M yi M zi Let L represent the components of the satellite's magnetic moment along the three orthogonal axes (x, y, z) under operating condition i; N is the operating condition number. Let i = L represent the load's operating condition. For other operating conditions.

[0079] The load operates intermittently, meaning that the load is powered on during normal operating conditions and powered off during other operating conditions.

[0080] In step 2, specifically: a set of dynamic compensation magnetic moments is selected. This makes the magnetic moment under the compensated load working condition Magnetic moment under other operating conditions Within the formed interval, that is, satisfying

[0081]

[0082]

[0083]

[0084] in, These are the components of the dynamic compensation magnetic moment on the three orthogonal axes: x, y, and z; M xL M yL M zL These are the components of the magnetic moment of the satellite on the three orthogonal axes (x, y, z) when i = L, under the payload operating conditions before compensation. These refer to all operating conditions other than the load-bearing operating condition, namely... The minimum value of the components of the magnetic moment on the three orthogonal axes x, y, and z; These refer to all operating conditions other than the load-bearing operating condition, namely... The maximum value of the components of the magnetic moment on the three orthogonal axes x, y, and z;

[0085] The dynamic compensation magnetic moment only affects the magnetic moment under the load operating condition, and has no effect on the magnetic moment under other operating conditions.

[0086] In step 3, specifically: based on the dynamic compensation magnetic moment Given the current I flowing through its power supply cable under load conditions, calculate the areas of the dynamic magnetic compensation loop (i.e., the plane whose normal lies on the three orthogonal axes x, y, and z) on the x, y, and z axes respectively:

[0087]

[0088]

[0089]

[0090] Among them, S x S y S z , respectively, represent the areas of the dynamic magnetic compensation loops on the three orthogonal axes x, y, and z; I is the current flowing through its power supply cable under load operating conditions; |·| indicates taking the absolute value;

[0091] The direction of the current in the loop on each axis is determined by the direction of the magnetic moment generated by the current (following the right-hand rule) and the direction of the component of the dynamic compensation magnetic moment on that axis.

[0092] In step 4, specifically: the positive and negative wires of the load power supply cable are partially separated, and the positive or negative wires are wound into current loops on the three orthogonal axes of x, y, and z according to the loop area and current direction required in step 3. This current loop is the dynamic magnetic compensation loop.

[0093] The dynamic magnetic compensation loop on a single axis can be single or multiple. For multiple loops, the sum of the areas of each loop is the loop area required in step 3, and the current direction in each loop is consistent with the current direction required in step 3.

[0094] The dynamic magnetic compensation loop is wound around the load power supply cable. When the load is working, the current in the loop will generate a magnetic moment, and the magnitude of the magnetic moment will increase with the increase of the current in the loop. When the load is not working, there is no current in the loop, so no magnetic moment is generated. Therefore, the dynamic magnetic compensation loop can achieve the dynamic magnetic compensation for the load's working conditions as required in step 2, while having no effect on the magnetic moment under other working conditions.

[0095] Example 2:

[0096] Example 2 is a preferred embodiment of Example 1, and is used to illustrate the present invention in more detail.

[0097] In this embodiment, the satellite dynamic magnetic compensation method provided by the present invention includes the following steps:

[0098] Step 1: Conduct magnetic tests on the satellite to obtain its magnetic moment under various operating conditions.

[0099] The satellite's magnetic moment under various operating conditions is shown in Table 1. Operating condition 2 represents the payload's operational condition, in which the payload is powered on, while in other operating conditions the payload is powered off. The required magnetic moment for this satellite is no greater than 6 A·m². As can be seen from Table 1, permanent magnet materials cannot compensate the satellite's magnetic moment to below 6 A·m² under all operating conditions (i.e., for M...). x M y M z Adding or subtracting a constant cannot guarantee M under all operating conditions. 总 (None greater than 6 A·m2).

[0100] Table 1. Satellite magnetic moment before dynamic magnetic compensation

[0101]

[0102] Step 2: Determine the dynamic magnetic compensation moment required for the load operating condition, so that the compensated magnetic moment under this condition is within the range formed by the magnetic moments under other operating conditions.

[0103] Dynamic compensation magnetic moment The following conditions must be met:

[0104]

[0105]

[0106]

[0107] Based on the above conditions, select a set of dynamic compensation magnetic moment values.

[0108] Step 3: Calculate the dynamic magnetic compensation loop area and determine the current direction in the loop based on the dynamic magnetic compensation magnetic moment and the load power supply current under the load operating conditions.

[0109] Under load operating conditions, the current flowing through its power supply cable is I = 100A. Therefore, in order to generate the dynamic compensation magnetic moment required in step 2, the areas of the dynamic magnetic compensation loop on the three orthogonal axes of x, y, and z (i.e., the normals of its plane lie on the three orthogonal axes of x, y, and z) are respectively:

[0110]

[0111]

[0112]

[0113] Therefore, the area of ​​the dynamic magnetic compensation loop on the x-axis is 0.142 m², and the direction of the magnetic moment generated by the current in the loop should be oriented in the same direction as the x-axis. The direction of the current in the loop is consistent, i.e., oriented towards the satellite's X-axis, and can be determined using the right-hand rule. No dynamic magnetic compensation is needed on the Y and Z axes.

[0114] Step 4: Using the positive or negative wire of the load power supply cable, wind it into a current loop according to the requirements of loop area and current direction, thus forming a dynamic magnetic compensation loop.

[0115] Separate the positive and negative wires of the load power supply cable locally, and use the positive or negative wire to form a current loop with a normal on the x-axis and an area of ​​0.142m2 (here, it is wound into a circle with a radius of about 0.21m) according to the current direction required in step 3. This current loop is the dynamic magnetic compensation loop.

[0116] Step 5: Conduct another magnetic test on the satellite to confirm the effect of dynamic magnetic compensation.

[0117] The magnetic moment of the satellite after dynamic magnetic compensation is shown in Table 2. Since the dynamic magnetic compensation loop is wound around the load power supply cable, current only flows through the loop when the load is operating, thus generating the compensating magnetic moment. Therefore, the dynamic magnetic compensation loop only performs magnetic compensation under the load's operating conditions and has no effect on the magnetic moment under other conditions. Table 2 shows that after dynamic magnetic compensation, the maximum magnetic moment of the satellite is 4.3 A·m², which meets the requirement of not exceeding 6 A·m².

[0118] Table 2 Satellite magnetic moment after dynamic magnetic compensation

[0119]

[0120] Those skilled in the art will understand that, in addition to implementing the system, apparatus, and their modules provided by this invention in purely computer-readable program code, the same program can be implemented in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system, apparatus, and their modules provided by this invention can be considered a hardware component, and the modules included therein for implementing various programs can also be considered structures within the hardware component; alternatively, modules for implementing various functions can be considered both software programs implementing the method and structures within the hardware component.

[0121] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A satellite dynamic magnetic compensation method, characterized in that, include: Step S1: Conduct magnetic tests on the satellite to obtain the satellite's magnetic moment under various operating conditions; Step S2: Determine the dynamic magnetic compensation moment required for the load operating condition, so that the magnetic moment under the compensated load operating condition is within the range formed by the magnetic moment under other operating conditions; Step S3: Calculate the dynamic magnetic compensation loop area and determine the loop current direction based on the dynamic magnetic compensation magnetic moment and the load power supply current under the load operating conditions; Step S4: Based on the positive or negative line of the load power supply cable, wind it into a current loop according to the requirements of loop area and current direction to form a dynamic magnetic compensation loop; Step S5: Conduct a magnetic test on the satellite to confirm the effect of dynamic magnetic compensation; In step S4: The positive and negative wires of the load power supply cable are partially separated. The positive or negative wires are wound into current loops on the three orthogonal axes x, y, and z according to the loop area and current direction determined in step S3. The current loops are dynamic magnetic compensation loops. The dynamic magnetic compensation loop on a single axis can be single or multiple. For multiple loops, the sum of the areas of each loop is the loop area determined in step S3, and the current direction in each loop is consistent with the current direction determined in step S3. The dynamic magnetic compensation loop is wound around the load power supply cable. When the load is working, the current in the loop generates a magnetic moment, and the magnitude of the magnetic moment increases with the increase of the current in the loop. When the load is not working, there is no current in the loop and no magnetic moment is generated. The dynamic magnetic compensation loop realizes dynamic magnetic compensation for the load's working conditions and has no effect on the magnetic moment under other working conditions.

2. The satellite dynamic magnetic compensation method according to claim 1, characterized in that, In step S1: Let the magnetic moment of the satellite under various operating conditions be {M}. xi M yi M zi |i=1,2,…,N}; Among them, M xi M yi M zi Let L represent the components of the satellite's magnetic moment along the three orthogonal axes (x, y, z) under operating condition i; N is the operating condition number, and let i = L represent the payload's operating condition. For other operating conditions; The load operates intermittently; it is powered on during normal operating conditions and powered off during other conditions.

3. The satellite dynamic magnetic compensation method according to claim 1, characterized in that, In step S2: Select a set of dynamic compensation magnetic moments This makes the magnetic moment under the compensated load working condition Magnetic moment under other operating conditions Within the formed interval, the following conditions are met: in, These are the components of the dynamic compensation magnetic moment on the three orthogonal axes: x, y, and z; M xL M yL M zL These are the components of the magnetic moment of the satellite on the three orthogonal axes (x, y, z) when i = L, under the payload operating conditions before compensation. These refer to all operating conditions other than the load-bearing operating condition, namely... The minimum value of the components of the magnetic moment on the three orthogonal axes x, y, and z; These refer to all operating conditions other than the load-bearing operating condition, namely... The maximum value of the components of the magnetic moment on the three orthogonal axes x, y, and z; The dynamic compensation magnetic moment affects the magnetic moment under the load working condition, but has no effect on the magnetic moment under other working conditions.

4. The satellite dynamic magnetic compensation method according to claim 1, characterized in that, In step S3: Based on dynamic compensation magnetic moment Given the current I flowing through its power supply cable under load operating conditions, calculate the areas of the dynamic magnetic compensation loops on the three orthogonal axes x, y, and z, respectively: Among them, S x S y S z These represent the areas of the dynamic magnetic compensation loops on the three orthogonal axes x, y, and z, respectively; I is the current flowing through its power supply cable under load operating conditions; / · / indicates taking the absolute value; The direction of the current in the loop on each axis is determined based on the fact that the direction of the magnetic moment generated by the current is consistent with the direction of the component of the dynamic compensation magnetic moment on that axis.

5. A satellite dynamic magnetic compensation system, characterized in that, include: Module M1: Performs magnetic tests on the satellite to obtain the satellite's magnetic moment under various operating conditions; Module M2: Determines the dynamic magnetic compensation moment required for the load operating condition, so that the magnetic moment under the compensated load operating condition is within the range formed by the magnetic moment under other operating conditions; Module M3: Calculate the dynamic magnetic compensation loop area and determine the loop current direction based on the dynamic magnetic compensation magnetic moment and the load supply current under load operating conditions; Module M4: Based on the positive or negative line of the load power supply cable, wind it into a current loop according to the requirements of loop area and current direction to form a dynamic magnetic compensation loop; Module M5: Conduct magnetic tests on the satellite to confirm the effectiveness of dynamic magnetic compensation; In module M4: The positive and negative wires of the load power supply cable are partially separated, and the positive or negative wires are wound into current loops on the three orthogonal axes of x, y, and z according to the loop area and current direction determined by module M3. The current loops are dynamic magnetic compensation loops. The dynamic magnetic compensation loop on a single axis can be single or multiple. For multiple loops, the sum of the areas of each loop is the loop area determined in module M3, and the current direction in each loop is consistent with the current direction determined in module M3. The dynamic magnetic compensation loop is wound around the load power supply cable. When the load is working, the current in the loop generates a magnetic moment, and the magnitude of the magnetic moment increases with the increase of the current in the loop. When the load is not working, there is no current in the loop and no magnetic moment is generated. The dynamic magnetic compensation loop realizes dynamic magnetic compensation for the load's working conditions and has no effect on the magnetic moment under other working conditions.

6. The satellite dynamic magnetic compensation system according to claim 5, characterized in that, In module M1: Let the magnetic moment of the satellite under various operating conditions be {M}. xi M yi M zi |i=1,2,…,N}; Among them, M xi M yi M zi Let L represent the components of the satellite's magnetic moment along the three orthogonal axes (x, y, z) under operating condition i; N is the operating condition number, and let i = L represent the payload's operating condition. For other operating conditions; The load operates intermittently; it is powered on during normal operating conditions and powered off during other conditions.

7. The satellite dynamic magnetic compensation system according to claim 5, characterized in that, In module M2: Select a set of dynamic compensation magnetic moments This makes the magnetic moment under the compensated load working condition Magnetic moment under other operating conditions Within the formed interval, the following conditions are met: in, These are the components of the dynamic compensation magnetic moment on the three orthogonal axes: x, y, and z; M xL M yL M zL These are the components of the magnetic moment of the satellite on the three orthogonal axes (x, y, z) when i = L, under the payload operating conditions before compensation. These refer to all operating conditions other than the load-bearing operating condition, namely... The minimum value of the components of the magnetic moment on the three orthogonal axes x, y, and z; These refer to all operating conditions other than the load-bearing operating condition, namely... The maximum value of the components of the magnetic moment on the three orthogonal axes x, y, and z; The dynamic compensation magnetic moment affects the magnetic moment under the load working condition, but has no effect on the magnetic moment under other working conditions.

8. The satellite dynamic magnetic compensation system according to claim 5, characterized in that, In module M3: Based on dynamic compensation magnetic moment Given the current I flowing through its power supply cable under load operating conditions, calculate the areas of the dynamic magnetic compensation loops on the three orthogonal axes x, y, and z, respectively: Among them, S x S y S z These represent the areas of the dynamic magnetic compensation loops on the three orthogonal axes x, y, and z, respectively; I is the current flowing through its power supply cable under load operating conditions; / · / indicates taking the absolute value; The direction of the current in the loop on each axis is determined based on the fact that the direction of the magnetic moment generated by the current is consistent with the direction of the component of the dynamic compensation magnetic moment on that axis.

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