A method, system, device, and storage medium for rapid counterweighting of satellite center of mass.

Abstract

A method, system, device, and storage medium for rapid satellite center of mass adjustment are disclosed, belonging to the field of spacecraft technology. This invention solves the problem of low efficiency and high error rate in existing satellite center of mass adjustment methods, which require multiple adjustments of the counterweight. The method includes the following steps: Step S1, setting the counterweight installation position in the satellite coordinate system; Step S2, calculating the offset between the measured position of the satellite center of mass and the target position of the satellite center of mass in the satellite coordinate system along each coordinate axis; Step S3, calculating the distance between the counterweight installation position and the target position of the satellite center of mass in the satellite coordinate system along each coordinate axis; Step S4, calculating the equivalent counterweight mass on each coordinate axis; Step S5, distributing the counterweight mass on each coordinate axis based on the equivalent counterweight mass on each coordinate axis.

Description

Technical Field

[0001] This invention relates to the field of spacecraft technology, specifically to a method, system, device, and storage medium for rapid counterweighting of a satellite's center of mass. Background Technology

[0002] Commercial spaceflight is developing rapidly. Microsatellites, with their short R&D cycle, low R&D cost, and ability to launch multiple satellites on a single rocket, have become the main force in satellite launches. Satellite manufacturing is shifting from a research and development model to a production model.

[0003] In the prior art, Chinese patent CN218524363U discloses "a centroid adjustment device and a simulated satellite," which adjusts the centroid through the adjustment device. However, it is not applicable to prototype satellites and does not involve a centroid adjustment method. Chinese patent CN106503322A discloses "a spacecraft mass characteristic balancing method," which is based on discretized constraint boundary conditions and corresponding design processes, requiring multiple iterative optimizations. Similarly, it does not involve specific processing or calculation methods.

[0004] Therefore, no method for rapid adjustment of a satellite's center of mass has been disclosed in existing technologies. Furthermore, in actual operation, adjusting the satellite's center of mass requires on-site calculations and calibrations, often involving multiple adjustments of the counterweight mass, which increases the probability of error and reduces work efficiency.

[0005] In summary, existing methods for adjusting the satellite's center of mass require multiple adjustments to the counterweight, resulting in a high probability of error and low work efficiency. Summary of the Invention

[0006] This invention solves the problem that existing satellite centroid adjustment methods require multiple adjustments of the counterweight, resulting in a high probability of error and low work efficiency.

[0007] The present invention provides a method for rapid rebalancing of a satellite's center of mass, comprising the following steps:

[0008] Step S1: Establish the satellite centroid coordinate system in the satellite coordinate system and set the counterweight installation position;

[0009] Step S2: Measure the satellite mass and, based on the measured position of the satellite's center of mass, calculate the offset of the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis.

[0010] Step S3: Based on the installation position of the counterweight, calculate the distance between it and the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis;

[0011] Step S4: Based on the satellite mass, the measured position of the satellite's center of mass and the offset of the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis, and the distance between the counterweight installation position and the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis, calculate the equivalent counterweight mass on each coordinate axis.

[0012] Step S5: Based on the equivalent counterweight mass on each coordinate axis, distribute the counterweight mass on each coordinate axis.

[0013] Furthermore, in one embodiment of the present invention, step S1, specifically setting the counterweight installation position, involves:

[0014] There are multiple counterweight installation locations, with multiple counterweight installation locations set at the edge of the satellite.

[0015] Furthermore, in one embodiment of the present invention, the provision of multiple counterweight installation positions at the edge of the satellite specifically refers to:

[0016] The equivalent centroid of multiple counterweight installation positions is approximately the center of the installation position on the counterweight installation surface, and the distances from multiple counterweight installation positions to the origin of the centroid are equal in the satellite centroid coordinate system.

[0017] Furthermore, in one embodiment of the present invention, step S4, specifically calculating the equivalent counterweight mass on each coordinate axis, involves:

[0018]

[0019] When m0 > 0, the equivalent counterweight is in the positive direction of each coordinate axis L0; when m0 < 0, the equivalent counterweight is in the negative direction of each coordinate axis L0.

[0020] Where m0 is the equivalent counterweight mass on each coordinate axis, and M is the satellite mass. This represents the offset of the measured position of the satellite's center of mass from the target position of the satellite's center of mass in the satellite coordinate system along each coordinate axis. This refers to the distance between the counterweight installation location and the target location of the satellite's center of mass in the satellite coordinate system on each coordinate axis.

[0021] Furthermore, in one embodiment of the present invention, step S5, which involves distributing the counterweight mass on each coordinate axis based on the equivalent counterweight mass on each coordinate axis, specifically includes:

[0022] The counterweight mass is distributed on each coordinate axis based on the order of the equivalent counterweight mass from largest to smallest.

[0023] Furthermore, in one embodiment of the present invention, the distribution of counterweight mass on each coordinate axis based on the order of equivalent counterweight mass from largest to smallest specifically refers to:

[0024] When the equivalent counterweight mass on the coordinate axis is the first in order, the counterweight mass distributed on the coordinate axis is the equivalent counterweight mass with the first in order.

[0025] When the equivalent counterweight mass on the coordinate axis is the second in order, the counterweight mass distributed on the coordinate axis is 1 / 2 (equivalent counterweight mass of the first in order + equivalent counterweight mass of the second in order) and 1 / 2 (equivalent counterweight mass of the first in order - equivalent counterweight mass of the second in order).

[0026] When the equivalent counterweight mass on the coordinate axis is the third in order, the counterweight mass distributed on the coordinate axis is 1 / 4 (equivalent counterweight mass of the first in order + equivalent counterweight mass of the second in order) ± a / 2 equivalent counterweight mass of the third in order, and 1 / 4 (equivalent counterweight mass of the first in order + equivalent counterweight mass of the second in order) ± 1 - a / 2 equivalent counterweight mass of the third in order.

[0027] Where, a∈(1-(equivalent weight mass of the first order - equivalent weight mass of the second order) equivalent weight mass of the third order, 1)∩(0,∞).

[0028] The satellite centroid rapid counterweight system of the present invention includes the following modules:

[0029] Module S1, the satellite centroid coordinate system in the satellite coordinate system, and sets the counterweight installation position;

[0030] Module S2 measures the satellite's mass and, based on the measured position of the satellite's center of mass, calculates the offset of the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis.

[0031] Module S3 calculates the distance between the counterweight and the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis, based on the counterweight's installation position.

[0032] Module S4 calculates the equivalent counterweight mass on each coordinate axis based on the satellite mass, the measured position of the satellite's center of mass and the offset of the target position of the satellite's center of mass in the satellite coordinate system, and the distance between the counterweight installation position and the target position of the satellite's center of mass in the satellite coordinate system.

[0033] Module S5 distributes the counterweight mass on each coordinate axis based on the equivalent counterweight mass on each coordinate axis.

[0034] The electronic device of the present invention includes a processor, a communication interface, a memory, and a communication bus, wherein the processor, the communication interface, and the memory communicate with each other through the communication bus.

[0035] Memory, used to store computer programs;

[0036] When a processor executes a program stored in memory, it implements any of the steps described in the above methods.

[0037] The present invention provides a computer-readable storage medium storing a computer program, which, when executed by a processor, implements any of the steps described above.

[0038] This invention solves the problem of low efficiency and high error rate in existing satellite center-of-gravity adjustment methods, which require multiple adjustments of the counterweight. Specific beneficial effects include:

[0039] 1. The present invention provides a rapid counterweight method for satellite center of mass adjustment. Existing satellite center of mass adjustment methods require on-site calculation and calibration, resulting in multiple adjustments of the counterweight mass, leading to a high probability of error and low work efficiency. To solve the above technical problems, the present invention can quickly determine the counterweight installation position and calculate the counterweight mass at the corresponding installation position, improving the accuracy of the counterweight installation position and mass, while also improving work efficiency, thereby effectively solving the technical problems existing in the prior art.

[0040] 2. The rapid counterweight method for satellite center of mass described in this invention can achieve accurate calculation of the counterweight mass at each counterweight installation point, with the error controlled within 5%, or even within 1%.

[0041] 3. The present invention provides a method for rapid balancing of the satellite's center of mass. By clarifying the design method for rapid balancing of the satellite's center of mass, the present invention standardizes and unifies the design process, clearly analyzes the calculation process for balancing the center of mass, and accurately calculates the mass of each balancing point.

[0042] The rapid counterweight method for satellite center of mass described in this invention is applicable to all stages of the development of various types of satellites. It is suitable for measuring the position of the satellite center of mass during the design stage and for testing the position of the satellite center of mass during the experimental stage, and has versatility. Attached Figure Description

[0043] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the following description of the embodiments taken in conjunction with the accompanying drawings, wherein:

[0044] Figure 1 This is a flowchart of the centroid balancing design method described in Implementation Method 1;

[0045] Figure 2 This is a schematic diagram of the satellite body coordinate system as described in Implementation Method 1;

[0046] Figure 3 This is a schematic diagram of the centroid coordinate system under the satellite body coordinate system described in Implementation Method 1;

[0047] Figure 4 This is a schematic diagram of the satellite body coordinate system and counterweight position as described in Implementation Method 1;

[0048] Figure 5 This is a schematic diagram showing the distance between the counterweight position and the designed position of the center of mass as described in Embodiment 1;

[0049] Figure 6 This is a schematic diagram showing the distance between the counterweight position and the target position of the center of mass as described in Embodiment 1;

[0050] Figure 7 This is a schematic diagram of the target position and the measured position of the centroid as described in Implementation Method 1;

[0051] In the diagram, 1 represents a satellite, and P... X O0 is the design position of the center of mass, O1 is the target position of the center of mass, and O2 is the measured position of the center of mass. Detailed Implementation

[0052] Various embodiments of the present invention will now be clearly and completely described with reference to the accompanying drawings. The embodiments described with reference to the drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0053] Implementation Method 1: The rapid counterweight method for satellite center of mass described in this implementation method includes the following steps:

[0054] Step S1: Establish the satellite centroid coordinate system in the satellite coordinate system and set the counterweight installation position;

[0055] Step S2: Measure the satellite mass and, based on the measured position of the satellite's center of mass, calculate the offset of the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis.

[0056] Step S3: Based on the installation position of the counterweight, calculate the distance between it and the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis;

[0057] Step S4: Based on the satellite mass, the measured position of the satellite's center of mass and the offset of the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis, and the distance between the counterweight installation position and the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis, calculate the equivalent counterweight mass on each coordinate axis.

[0058] Step S5: Based on the equivalent counterweight mass on each coordinate axis, distribute the counterweight mass on each coordinate axis.

[0059] In this embodiment, step S1, specifically setting the counterweight installation position, involves:

[0060] There are multiple counterweight installation locations, with multiple counterweight installation locations set at the edge of the satellite.

[0061] In this embodiment, setting multiple counterweight installation locations at the edge of the satellite specifically means:

[0062] The equivalent centroid of multiple counterweight installation positions is approximately the center of the installation position on the counterweight installation surface, and the distances from multiple counterweight installation positions to the origin of the centroid are equal in the satellite centroid coordinate system.

[0063] In this embodiment, step S4, which involves calculating the equivalent counterweight mass on each coordinate axis, specifically includes:

[0064]

[0065] When m0 > 0, the equivalent counterweight is in the positive direction of each coordinate axis L0; when m0 < 0, the equivalent counterweight is in the negative direction of each coordinate axis L0.

[0066] Where m0 is the equivalent counterweight mass on each coordinate axis, and M is the satellite mass. This represents the offset of the measured position of the satellite's center of mass from the target position of the satellite's center of mass in the satellite coordinate system along each coordinate axis. This refers to the distance between the counterweight installation location and the target location of the satellite's center of mass in the satellite coordinate system on each coordinate axis.

[0067] In this embodiment, step S5, which involves distributing the counterweight mass on each coordinate axis based on the equivalent counterweight mass on each coordinate axis, specifically includes:

[0068] The counterweight mass is distributed on each coordinate axis based on the order of the equivalent counterweight mass from largest to smallest.

[0069] In this embodiment, the distribution of counterweight mass on each coordinate axis based on the order of equivalent counterweight mass from largest to smallest specifically refers to:

[0070] When the equivalent counterweight mass on the coordinate axis is the first in order, the counterweight mass distributed on the coordinate axis is the equivalent counterweight mass with the first in order.

[0071] When the equivalent counterweight mass on the coordinate axis is the second in order, the counterweight mass distributed on the coordinate axis is 1 / 2 (equivalent counterweight mass of the first in order + equivalent counterweight mass of the second in order) and 1 / 2 (equivalent counterweight mass of the first in order - equivalent counterweight mass of the second in order).

[0072] When the equivalent counterweight mass on the coordinate axis is the third in order, the counterweight mass distributed on the coordinate axis is 1 / 4 (equivalent counterweight mass of the first in order + equivalent counterweight mass of the second in order) ± a / 2 equivalent counterweight mass of the third in order, and 1 / 4 (equivalent counterweight mass of the first in order + equivalent counterweight mass of the second in order) ± 1 - a / 2 equivalent counterweight mass of the third in order.

[0073] Where, a∈(1-(equivalent weight mass of the first order - equivalent weight mass of the second order) equivalent weight mass of the third order, 1)∩(0,∞).

[0074] In existing technologies, satellite center of mass adjustment requires on-site calculation and calibration, which involves multiple adjustments to the counterweight mass, resulting in a high probability of error and low work efficiency.

[0075] To solve the above technical problems, such as Figure 1 As shown, this embodiment designs a method for rapid counterweighting of a satellite's center of mass, including the following steps:

[0076] Step S1: Based on the satellite design, determine the coordinates of the counterweight installation position in the satellite coordinate system OL1L2L3. Where X∈{1,2,3,4,5,6,7,8}, and the theoretical coordinates of the satellite's centroid are O0(0,0,L3);

[0077] Step S2: Measure the satellite's mass to determine its designed or measured mass M, and calculate the offset of the measured position of the satellite's center of mass relative to the target position of the satellite's center of mass in the satellite coordinate system along each coordinate axis. and

[0078] Step S3: Based on the target position of the satellite's center of mass and the coordinates of the counterweight installation position, calculate the distance between the counterweight installation position and the target position of the satellite's center of mass in the satellite coordinate system. and

[0079] Step S4: Based on the satellite mass, the offset of the actual position of the satellite's center of mass relative to the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis, and the distance between the counterweight installation position and the target position of the satellite's center of mass in the satellite coordinate system, calculate the equivalent counterweight mass m1, m2 and m3 on each coordinate axis respectively.

[0080] Step S5: Based on the equivalent counterweight mass on each coordinate axis, determine the counterweight installation position using the designed calculation method, and calculate the counterweight mass at the corresponding position.

[0081] The method described in this embodiment has the advantages of versatility, accurate installation location, high accuracy in calculating counterweight mass, and high work efficiency.

[0082] To better illustrate the rapid satellite centroid counterweight method described in this embodiment, the following examples provide a detailed description:

[0083] The rapid rebalancing method for satellite centroid described in this embodiment includes the following steps:

[0084] Step S1, as follows Figure 2 As shown, the satellite coordinate system is OL1L2L3. The designed position of the satellite's center of mass in the satellite body coordinate system is O0(0,0,L3). Using the designed position of the satellite's center of mass as the origin, and with all coordinate axes aligned with the coordinate axes of the satellite coordinate system, the satellite center of mass coordinate system OL1L2L3 is established. Its relationship with the satellite coordinate system is as follows: Figure 3 As shown;

[0085] Counterweight mounting points are set at the edge of the satellite, and the equivalent center of mass of each counterweight mounting point is approximately the center of the mounting point on the counterweight mounting surface, such as... Figure 4 As shown, the distances from each counterweight installation point to the origin O0 of the center of mass are equal on the same coordinate axis in the satellite's center-of-mass coordinate system. Figure 5 As shown, the coordinates of the equivalent center of mass of the counterweight are... Where X∈{1,2,3,4,5,6,7,8}.

[0086] Step S2: Obtain the satellite mass M by measurement or testing, and determine the coordinates of the target position of the satellite's center of mass adjustment in the satellite's body coordinate system. like Figure 6 As shown, in the optimal state Right now

[0087] The satellite target position and the measured position of the centroid in the satellite body coordinate system are as follows: Figure 7 As shown, the coordinates of the satellite's measured position.

[0088] The vector between the measured position of the centroid and the target position is:

[0089] Step S3, the distance between the counterweight position and the target centroid position along coordinate axis L1 is... The distance between the counterweight position and the target center of mass along the L2 axis is... The distance between the counterweight position and the target center of mass along the L3 axis is:

[0090] Step S4: Under normal circumstances, there is a certain deviation between the measured position of the satellite's center of mass and the target position. In order to adjust the satellite's center of mass from the measured position to the target position, counterweights need to be installed on the satellite body. The equivalent counterweight masses to be installed on each coordinate axis are as follows:

[0091] The equivalent counterweight mass distributed on coordinate axis L1 is:

[0092]

[0093] When m1 > 0, that is When the counterweight is in the positive direction of coordinate axis L1, and m1 < 0, that is... At that time, the counterweight is in the negative direction of coordinate axis L1.

[0094] The equivalent counterweight mass distributed on coordinate axis L2 is:

[0095] When m2 > 0, that is When the counterweight is in the positive direction of coordinate axis L2, and m2 < 0, that is... At that time, the counterweight is in the negative direction of coordinate axis L2.

[0096] The equivalent counterweight mass distributed on coordinate axis L3 is:

[0097] When m3 > 0, that is When the counterweight is in the positive direction of coordinate axis L3, and m3 < 0, that is... At that time, the counterweight is in the negative direction of coordinate axis L3.

[0098] Step S5: The magnitudes of the equivalent counterweight masses m1, m2, and m3 determine the installation position P of the counterweight. X The equivalent counterweights are distributed in descending order of size.

[0099] Assume m1≥m2≥m3;

[0100] 1) First step, distribute the counterweight mass on coordinate axis L1:

[0101]

[0102] Using the subscripts ± to indicate the position of the counterweight mass on the corresponding coordinate axis, the equivalent counterweight mass m1 is equivalent to:

[0103] 2) The second step is to continue distributing the counterweight mass on coordinate axis L2 based on the first step:

[0104]

[0105]

[0106] 3) The third step is to continue distributing the counterweight mass on coordinate axis L3 based on the second step:

[0107]

[0108] and This refers to the final location of the counterweight and the required mass for that location.

[0109] In summary, this implementation method designs a universal satellite center of mass rapid balancing method applicable to all stages of satellite development, making the design process standardized and unified. It also uses corresponding calculation methods to quickly determine the installation position of the counterweight, accurately calculate the required counterweight mass at the installation point, and achieve high calculation accuracy, thereby improving the accuracy of the counterweight installation position and its mass, and increasing the efficiency of satellite center of mass adjustment.

[0110] Implementation Method 2: The satellite centroid rapid counterweight system described in this implementation method includes the following modules:

[0111] Module S1, the satellite centroid coordinate system in the satellite coordinate system, and sets the counterweight installation position;

[0112] Module S2 measures the satellite's mass and, based on the measured position of the satellite's center of mass, calculates the offset of the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis.

[0113] Module S3 calculates the distance between the counterweight and the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis, based on the counterweight's installation position.

[0114] Module S4 calculates the equivalent counterweight mass on each coordinate axis based on the satellite mass, the measured position of the satellite's center of mass and the offset of the target position of the satellite's center of mass in the satellite coordinate system, and the distance between the counterweight installation position and the target position of the satellite's center of mass in the satellite coordinate system.

[0115] Module S5 distributes the counterweight mass on each coordinate axis based on the equivalent counterweight mass on each coordinate axis.

[0116] Implementation Method 3: An electronic device according to this implementation method includes a processor, a communication interface, a memory, and a communication bus, wherein the processor, the communication interface, and the memory communicate with each other through the communication bus.

[0117] Memory, used to store computer programs;

[0118] When a processor executes a program stored in memory, it implements the steps of the method described in Embodiment 1.

[0119] Implementation Method 4: A computer-readable storage medium according to this implementation method, wherein the computer-readable storage medium stores a computer program, and when the computer program is executed by a processor, it implements the steps of the method described in Implementation Method 1.

[0120] The above provides a detailed description of a rapid satellite center-of-mass counterweight method, system, device, and storage medium proposed in this invention. Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of this invention. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A method for rapid counterweighting of a satellite's center of mass, characterized in that, Includes the following steps: Step S1: Based on the coordinates of the satellite's designed center of mass in the satellite coordinate system, take the designed center of mass as the origin of the coordinate system, and align each coordinate axis with the coordinate axes of the satellite coordinate system to establish the satellite's center of mass coordinate system, and set the counterweight installation position. Step S2: Measure the satellite mass and, based on the measured position of the satellite's center of mass, calculate the offset of the target position of the satellite's center of mass relative to the satellite coordinate system on each coordinate axis. Step S3: Based on the installation position of the counterweight, calculate the distance between it and the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis; Step S4: Based on the satellite mass, the offset of the actual position of the satellite's center of mass relative to the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis, and the distance between the counterweight installation position and the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis, calculate the equivalent counterweight mass on each coordinate axis. Step S5, based on the order of equivalent counterweight mass on each coordinate axis from largest to smallest, distribute the counterweight mass on each coordinate axis, specifically as follows: When the equivalent counterweight mass on the coordinate axis is the first in order, the counterweight mass distributed on the coordinate axis is the equivalent counterweight mass with the first in order. When the equivalent counterweight mass on the coordinate axis is the second in order, the counterweight mass distributed on the coordinate axis is 1 / 2 (equivalent counterweight mass of the first in order + equivalent counterweight mass of the second in order) and 1 / 2 (equivalent counterweight mass of the first in order - equivalent counterweight mass of the second in order). When the equivalent counterweight mass on the coordinate axis is the third in order, the counterweight mass distributed on the coordinate axis is 1 / 4 (equivalent counterweight mass of the first in order + equivalent counterweight mass of the second in order) ± a / 2 equivalent counterweight mass of the third in order, and 1 / 4 (equivalent counterweight mass of the first in order - equivalent counterweight mass of the second in order) ± (1-a) / 2 equivalent counterweight mass of the third in order; Where a∈(1-(equivalent weight mass of the first order - equivalent weight mass of the second order) / equivalent weight mass of the third order,1)∩(0,∞).

2. The method for rapid counterweighting of a satellite's center of mass according to claim 1, characterized in that, In step S1, setting the counterweight installation position specifically involves: There are multiple counterweight installation locations, with multiple counterweight installation locations set at the edge of the satellite.

3. The method for rapid counterweighting of a satellite's center of mass according to claim 2, characterized in that, The aforementioned setting of multiple counterweight installation locations at the edge of the satellite specifically refers to: The equivalent centroid of multiple counterweight installation positions is approximately the center of the installation position on the counterweight installation surface, and the distances from multiple counterweight installation positions to the origin of the centroid are equal in the satellite centroid coordinate system.

4. The method for rapid counterweighting of a satellite's center of mass according to claim 1, characterized in that, In step S4, the calculation of the equivalent counterweight mass on each coordinate axis specifically involves:

5. A rapid counterweight system for satellite center of mass, characterized in that, Includes the following modules: Module S1 establishes the satellite center of mass coordinate system based on the coordinates of the satellite center of mass design position in the satellite coordinate system, with the satellite center of mass design position as the coordinate origin and each coordinate axis in the same direction as the coordinate axis of the satellite coordinate system, and sets the counterweight installation position. Module S2 measures the satellite's mass and, based on the measured position of the satellite's center of mass, calculates the offset of the target position of the satellite's center of mass relative to the satellite's center of mass in the satellite coordinate system on each coordinate axis. Module S3 calculates the distance between the counterweight and the target position of the satellite's center of mass in the satellite coordinate system on each coordinate axis, based on the counterweight's installation position. Module S4 calculates the equivalent counterweight mass on each coordinate axis based on the satellite mass, the offset of the actual position of the satellite's center of mass relative to the target position of the satellite's center of mass in the satellite coordinate system, and the distance between the counterweight installation position and the target position of the satellite's center of mass in the satellite coordinate system. Module S5 distributes the counterweight mass on each coordinate axis based on the order of equivalent counterweight mass from largest to smallest, specifically as follows: When the equivalent counterweight mass on the coordinate axis is the first in order, the counterweight mass distributed on the coordinate axis is the equivalent counterweight mass with the first in order. When the equivalent counterweight mass on the coordinate axis is the second in order, the counterweight mass distributed on the coordinate axis is 1 / 2 (equivalent counterweight mass of the first in order + equivalent counterweight mass of the second in order) and 1 / 2 (equivalent counterweight mass of the first in order - equivalent counterweight mass of the second in order). When the equivalent counterweight mass on the coordinate axis is the third in order, the counterweight mass distributed on the coordinate axis is 1 / 4 (equivalent counterweight mass of the first in order + equivalent counterweight mass of the second in order) ± a / 2 equivalent counterweight mass of the third in order, and 1 / 4 (equivalent counterweight mass of the first in order - equivalent counterweight mass of the second in order) ± (1-a) / 2 equivalent counterweight mass of the third in order; Where a∈(1-(equivalent weight mass of the first order - equivalent weight mass of the second order) / equivalent weight mass of the third order,1)∩(0,∞).

6. An electronic device, characterized in that, It includes a processor, a communication interface, a memory, and a communication bus, wherein the processor, the communication interface, and the memory communicate with each other through the communication bus; Memory, used to store computer programs; A processor, when executing a program stored in memory, implements the method described in any one of claims 1-4.

7. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program that, when executed by a processor, implements the method described in any one of claims 1-4.

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