High-precision quality characteristic calculation method and system suitable for small satellites

Abstract

The invention provides a high-precision quality characteristic calculation method and system suitable for a small satellite. The high-precision quality characteristic calculation method comprises the steps that a whole-satellite three-dimensional model is constructed according to the overall layout of the satellite; calculating a whole satellite quality characteristic budget value; decomposing the quality characteristic index to each satellite component; according to the quality characteristic index of each subsystem, the manufacturing process of each part of the satellite is controlled; substituting the measured value or the accurate design value of the quality characteristic of each part of the satellite into the whole satellite three-dimensional model, and calculating the calculated value of the quality characteristic of the satellite; and iteratively modifying the whole-satellite layout by combining the whole-satellite quality characteristic measured value until the measured value meets the precision requirement. According to the invention, fine estimation is carried out on structure, thermal control, propulsion and cable network model sub-modules, and rotational inertia calculation values of satellite parts relative to a self centroid coordinate system are incorporated into whole-satellite quality characteristic calculation sub-modules, so that the calculation precision of the whole-satellite quality characteristics is improved, the control capability of satellite attitudes and orbits is ensured, and the calculation efficiency of the whole-satellite quality characteristics is improved. And the on-orbit working capability of the high-precision small satellite is ensured.

Description

Technical Field

[0001] The present invention relates to the field of aerospace satellite technology, and in particular to a high-precision mass characteristic calculation method and system suitable for small satellites. Background Art

[0002] In recent years, with the rapid development of aerospace technology, space launch vehicles have achieved increasingly faster flight speeds, resulting in greater aerodynamic forces. During satellite launches, accurate attitude and orbit control are crucial to minimizing fuel consumption and ensuring flight distance. High-precision satellite mass characteristics are crucial for ensuring precise attitude and orbit control. However, during satellite development, due to iterations in overall layout, optimization of payload equipment, and deviations between designed and measured values, the accuracy of mass characteristic calculations can be difficult to guarantee.

[0003] Satellite mass characteristics are one of the main parameters of the satellite as a whole. Mass characteristic parameters include: mass, center of mass position, moment of inertia, and product of inertia. Generally, the mass characteristics of a satellite are mainly determined by each subsystem, structure, thermal control, propulsion, cable network, etc. Among them, the mass characteristics of each subsystem, structure, and propulsion can be estimated through three-dimensional models, while the mass characteristics of thermal control and cable network need to be estimated based on experience. When the satellite size is small, even small changes caused by different directions of thermal control and cable network will have a significant impact on the satellite's mass characteristics. Therefore, the development of high-precision mass characteristic calculation methods is an important technical support for the production practices of small satellite assembly and commissioning, attitude and orbit control, final assembly and testing, and is also an urgent need to improve the accuracy of satellite insertion into orbit.

[0004] Patent document CN115342971A discloses a mass characteristic simulation system based on a satellite three-dimensional model, including: the parameter setting module is used to set the mass characteristic parameters of a stand-alone model or a distributed structural component model in a defined coordinate system; the collaborative calculation module uses the mass characteristic parameters set by the parameter setting module to calculate and integrate the mass characteristic parameters of each satellite model in a unified satellite layout coordinate system; the synthesis application module uses the mass characteristic parameters output by the collaborative calculation module to carry out synthetic calculations for scenario conditions with different forms of large movable parts, whether propellant is filled, and counterweight block configuration.

[0005] However, when calculating the mass characteristic values, patent document CN115342971A simplifies the mass characteristic parameters of the distributed structural parts. This simplification may introduce calculation errors, resulting in inaccurate mass characteristic calculation results.

[0006] Patent document CN107860513A discloses a method for determining the mass characteristics of a spacecraft, including the following steps: establishing a three-dimensional model of a spacecraft cabin and equipment; using the three-dimensional model to calculate the initial values ​​of the mass characteristics of the spacecraft cabin and the spacecraft after loading part of the cargo; using quality measurement equipment to measure the measured mass characteristics of the above-mentioned spacecraft cabin and the spacecraft after loading part of the cargo; comparing the measured mass characteristics with the initial values ​​of the mass characteristics, and when the comparison result exceeds a preset range, correcting the three-dimensional model and comparing again; when the comparison result is within the preset range, using the three-dimensional model to calculate the mass characteristics of the spacecraft in a fully loaded state.

[0007] However, patent document CN115342971A only focuses on obtaining accurate quality characteristic data and is unable to adjust the quality characteristic values ​​as required to meet the index requirements.

[0008] Patent document CN107063567A discloses a method for calculating the mass characteristics of the transfer segment of a high-orbit parallel-lay tank satellite. The method includes simplifying fixed products and calculating the mass characteristics of fixed products on the satellite; calculating the mass characteristics of products with one-time state transitions on the satellite; calculating the remaining propellant in the tank and the corresponding liquid level based on the engine thrust, specific impulse and engine operating time, and then calculating the mass characteristics of the propellant in the parallel-lay tank based on the tank shape, installation position, etc.; calculating the mass characteristics of the satellite in the transfer orbit segment, obtaining the satellite center of mass position, satellite moment of inertia and product of inertia corresponding to each time point, and obtaining the satellite mass characteristics in the entire transfer segment through programming loop calculation.

[0009] However, when calculating in patent document CN107063567A, some products are simplified into mass points, and the moment of inertia and product of inertia of the products relative to their own center of mass coordinate system are ignored. This will introduce calculation errors and lead to increased errors in satellite mass characteristics. Summary of the Invention

[0010] In view of the defects in the prior art, the purpose of the present invention is to provide a high-precision mass characteristic calculation method and system suitable for small satellites.

[0011] According to the present invention, a high-precision mass characteristic calculation method applicable to small satellites is provided, comprising:

[0012] Step S1: construct a three-dimensional model of the entire satellite according to the overall layout of the satellite;

[0013] Step S2: Calculating the mass characteristics of each satellite component in the entire satellite layout coordinate system based on the three-dimensional model to obtain a mass characteristic budget value for the entire satellite;

[0014] Step S3: Decomposing the quality characteristic index into each satellite component according to the whole satellite quality characteristic budget value;

[0015] Step S4: Control the manufacturing process of each satellite component based on the quality characteristic indicators of each subsystem;

[0016] Step S5: Substituting the measured values ​​or accurate design values ​​of the mass characteristics of each satellite component into the three-dimensional model of the entire satellite to calculate the calculated values ​​of the satellite mass characteristics;

[0017] Step S6: Based on the measured values ​​of the mass characteristics of the entire satellite, the calculation model is modified and the entire satellite layout is iteratively modified until the measured values ​​meet the accuracy requirements.

[0018] Preferably, while ensuring that there is sufficient space margin for final assembly operations, each unit is placed at the lateral center of mass trim position of the entire satellite, and a design margin is reserved based on the difference between the actual measured weight and the design weight of each unit.

[0019] Preferably, when calculating the budget value of the mass characteristics of the entire satellite, the mass characteristics of the three-dimensional model of each satellite component are substituted into the calculation, and the calculation module includes the stand-alone model of each subsystem, the propulsion module, the cable network module, the whole satellite counterweight module, the structure module and the thermal control module.

[0020] Preferably, the step S6 includes: judging whether the measured value of the quality characteristic meets the index requirements, if so, the quality characteristic calculation is completed; if not, it means that the current measured value is inconsistent with the calculated value, and the center of mass deviation exceeds the design requirements. At this time, by correcting the quality characteristic calculation model, adjusting the layout position of the satellite components, and returning to step S5 until the measured value meets the accuracy requirements.

[0021] Preferably, the layout positions of the satellite components include:

[0022] When the deviation between the measured mass characteristic value and the index requirement is within 5 mm, i.e. the deviation is small, the center of mass balance accuracy of the entire satellite is corrected by adjusting the layout of thermal control and propulsion or the direction of the cable network;

[0023] When the deviation between the measured mass characteristic value and the index requirement is within 5 to 15 mm, that is, the deviation is large, the balance accuracy of the center of mass of the entire satellite is corrected by adjusting the layout position of the heavier single unit;

[0024] When the deviation between the measured value of the quality characteristic and the index requirement exceeds 15mm, that is, the deviation is very large, the calculated value shall be corrected by adding counterweight blocks at appropriate positions until it meets the accuracy requirements.

[0025] Preferably, the layout principles for adding counterweights include:

[0026] The counterweight block does not change the existing shape and number of interfaces of the structural plate. The counterweight block makes use of the existing single-machine mounting holes of the satellite as much as possible and is installed under the single machine or bracket. The counterweight block does not affect the implementation of thermal control and the overall circuit routing. The counterweight block occupies as little space as possible within the satellite. The counterweight block should not exceed the envelope of the entire satellite, nor affect the external interface of the satellite. The change in the moment of inertia of the satellite when it is retracted and deployed should not exceed the control margin.

[0027] According to the present invention, a high-precision mass characteristic calculation system suitable for small satellites is provided, comprising:

[0028] Module M1: Construct a 3D model of the entire satellite based on its overall layout;

[0029] Module M2: Calculate the mass characteristics of each satellite component in the entire satellite layout coordinate system based on the three-dimensional model to obtain a mass characteristic budget value of the entire satellite;

[0030] Module M3: Decomposing the quality characteristic indicators into each satellite component according to the quality characteristic budget value of the whole satellite;

[0031] Module M4: Controls the manufacturing process of satellite components based on the quality characteristics of each subsystem;

[0032] Module M5: Substitute the measured values ​​or precise design values ​​of the mass characteristics of each satellite component into the three-dimensional model of the entire satellite to calculate the calculated values ​​of the satellite mass characteristics;

[0033] Module M6: Based on the measured values ​​of the mass characteristics of the entire satellite, the calculation model is modified and the entire satellite layout is iteratively modified until the measured values ​​meet the accuracy requirements.

[0034] Preferably, while ensuring that there is sufficient space margin for final assembly operations, each unit is placed at the lateral center of mass trim position of the entire satellite, and a design margin is reserved based on the difference between the actual measured weight and the design weight of each unit.

[0035] Preferably, when calculating the budget value of the mass characteristics of the entire satellite, the mass characteristics of the three-dimensional model of each satellite component are substituted into the calculation, and the calculation module includes the stand-alone model of each subsystem, the propulsion module, the cable network module, the whole satellite counterweight module, the structure module and the thermal control module.

[0036] Preferably, the module M6 includes: judging whether the measured value of the quality characteristic meets the index requirements. If so, the quality characteristic calculation is completed; if not, it means that the current measured value is inconsistent with the calculated value, and the center of mass deviation exceeds the design requirements. At this time, by correcting the quality characteristic calculation model, adjusting the layout position of the satellite components, and returning to module M5 until the measured value meets the accuracy requirements.

[0037] Compared with the prior art, the present invention has the following beneficial effects:

[0038] 1. The present invention refines the estimation of the structure, thermal control, propulsion, and cable network models by sub-modules, and incorporates the calculated value of the moment of inertia of satellite components relative to their own center of mass coordinate system into the calculation of the mass characteristics of the entire satellite. This improves the calculation accuracy of the mass characteristics of the entire satellite, ensures the control capability of the satellite attitude and orbit, and guarantees the on-orbit operation capability of high-precision small satellites.

[0039] 2. Based on the difference analysis between the calculated and measured values ​​of mass characteristics, the present invention adjusts the spacecraft layout and corrects the simulation calculation model to achieve high-precision index requirements for mass characteristics. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0041] Figure 1 It is a schematic flow chart of the working method of the present invention. DETAILED DESCRIPTION

[0042] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0043] This method first breaks down the overall satellite quality performance indicators into individual satellite components. By controlling the component manufacturing process to ensure the accuracy of quality performance calculations, the calculated values ​​are then compared and analyzed with the measured values. The quality performance requirements are met by adjusting the layout of individual components, the distribution of the cable network, and adding counterweights. This method is suitable for small satellites that require high-precision control of the satellite's flight attitude and precise control of satellite quality characteristics.

[0044] Example 1

[0045] According to the present invention, a high-precision mass characteristic calculation method suitable for small satellites is provided. Figure 1 Shown, including:

[0046] Step S1: Construct a 3D model of the entire satellite based on the overall satellite layout. Based on the overall satellite layout plan, 3D models of satellite components such as each subsystem unit, structure, thermal control, propulsion, and cable network are constructed using 3D modeling software. During the initial stages of satellite layout, the weight of each subsystem unit and structure, the layout of thermal control and propulsion, and the routing of the cable network are difficult to estimate. Therefore, when constructing the initial 3D model, special attention should be paid to the layout position of the units, especially those with a large weight contribution. While ensuring sufficient space for final assembly operations, each unit should be placed at the trim position of the satellite's lateral center of mass. The difference between the measured weight and the designed weight of each unit should be considered, and a design margin should be reserved.

[0047] Step S2: Calculate the mass characteristics of each satellite component in the entire satellite layout coordinate system based on the three-dimensional model to obtain a mass characteristic budget value for the entire satellite. The mass characteristic budget value includes the mass characteristics of the entire satellite in the layout coordinate system, including mass, center of mass, moment of inertia, and product of inertia, as follows:

[0048] The mass calculation formula of the entire satellite is as follows:

[0049]

[0050] Where: M i (i=1,2,3....,n) is the mass of each component in the satellite; M is the mass of the satellite.

[0051] The calculation formula of the center of mass coordinates of the entire satellite is as follows:

[0052]

[0053] Where: X c 、Y c , Z c is the satellite relative to the satellite mechanical coordinate system O l X l Y l Z l The center of mass of X i 、Y i , Z i is the coordinate system of the satellite component i relative to the satellite mechanical coordinate system O l X l Y l Z l The center of mass.

[0054] The calculation formula of the satellite's moment of inertia is as follows:

[0055]

[0056] Where: For the satellite center of mass coordinate system O hb X hb Y hb Z hb :I xxb , I yyb , I zzb is the satellite relative to the satellite mass center coordinate system O hb X hb Y hb Z hb The moment of inertia. xIi , I yIi , I zIi is the moment of inertia of the i-th satellite component around its own axis. ib 、Y ib , Z ib is the coordinate system O of the i-th satellite component relative to the satellite center of mass hb X hb Y hb Z hb The center of mass.

[0057] The calculation formula of the satellite's inertia product is as follows:

[0058]

[0059] Where: For the satellite center of mass coordinate system O hb X hb Y hb Z hb :I xyb , I yzb , I xzb : Satellite relative to satellite mass center coordinate system O hb X hb Y hb Z hb The product of inertia. xyIi , I yzIi , I xzIi : The inertia product of the i-th satellite component around its own axis. X ib 、Y ib , Z ib : The i-th satellite component relative to the satellite center of mass coordinate system O hb X hb Y hb Z hb The center of mass.

[0060] When calculating the mass characteristic values ​​of the entire satellite, the mass characteristics of the three-dimensional models of satellite components, including each subsystem, structure, thermal control, propulsion, and cable network, are substituted into the calculation. Based on their calculation characteristics, these components can be specifically divided into the following five calculation modules: each subsystem's individual model, the propulsion module, the cable network module, the satellite's overall counterweight module, and the structure and thermal control module. The individual subsystem models first use three-dimensional modeling software to read out the relevant mass, center of mass position, and moment of inertia and product of inertia relative to their own center of mass coordinate system for each individual subsystem. This data is then converted to the satellite's center of mass coordinate system for unified calculation. The structure and thermal control modules evenly distribute the structural and thermal control weights on the relevant structural plates and adjust the density of each structural plate to match the corresponding mass values. The structural plate's mass characteristic data is then read out using three-dimensional modeling software and converted to the satellite's center of mass coordinate system for unified calculation. The propulsion module estimates the mass characteristic data of the entire propulsion model based on the tank's shape, installation location, and propulsion pipeline routing in the three-dimensional propulsion model, then converts this data into the satellite's center-of-mass coordinate system for unified calculation. The cable network module estimates the mass characteristic data of the cable network based on the cable routing in the three-dimensional cable network model, then converts this data into the satellite's center-of-mass coordinate system for unified calculation. The satellite counterweight module estimates the layout position of the counterweight blocks based on the estimated mass characteristic values, estimates the counterweight block's mass characteristic data, and assists in balancing the lateral center of mass in the satellite's center-of-mass coordinate system.

[0061] Step S3: Decompose the quality characteristics into individual satellite components based on the estimated satellite quality characteristics. Combining the theoretical estimated satellite quality characteristics and accuracy requirements, decompose the quality characteristics into individual subsystems, including individual components, structure, thermal control, propulsion, and cable network. Specifically, the total satellite quality is decomposed into individual components based on design experience, and the layout position is decomposed into individual components based on the required accuracy for satellite attitude and orbit control. During this decomposition process, sufficient space is reserved for individual component installation, cable clamps, and cable routing.

[0062] Step S4: Control the manufacturing process of each satellite component based on the quality performance indicators of each subsystem. During the satellite payload preparation process, regular inspection and control of the component preparation process is carried out according to the quality performance indicators of each satellite component. Specifically, regular inspections are conducted on the quality and appearance changes of each subsystem, including the unit, structure, thermal control, and propulsion, before and after manufacturing. The overall satellite layout is regularly updated based on manufacturing changes of each subsystem. Changes in the satellite thermal control layout and cable network routing are monitored to prevent such changes from causing deviations in the overall satellite quality performance.

[0063] Step S5: Substitute the measured or precisely designed mass characteristics of each satellite component into the full satellite 3D model to calculate the satellite's calculated mass characteristics. The satellite components' layout is adjusted to ensure the calculated lateral center of mass meets the design requirements. After the satellite components are prepared, the calculated mass characteristics of the entire satellite are calculated based on their installation positions and measured or precisely calculated mass characteristics. Once the calculated values ​​meet the required specifications, the full satellite mass characteristics are measured.

[0064] Step S6: Based on the measured values ​​of the satellite's mass characteristics, the calculation model is modified, and the satellite layout is iteratively modified until the measured values ​​meet the accuracy requirements. Step S6 includes determining whether the measured values ​​of the mass characteristics meet the index requirements. If so, the mass characteristic calculation is completed. If not, it indicates that the current measured values ​​are inconsistent with the calculated values ​​and the center of mass deviation exceeds the design requirements. In this case, the mass characteristic calculation model is modified, the layout of the satellite components is adjusted, and the process returns to step S5 until the measured values ​​meet the accuracy requirements.

[0065] The layout positions of the satellite components include: when the deviation between the measured value of the mass characteristic and the index requirement is within 5 mm, that is, the deviation is small, the balancing accuracy of the center of mass of the entire satellite can be corrected by adjusting the layout of thermal control, propulsion or the direction of the cable network; when the deviation between the measured value of the mass characteristic and the index requirement is within 5 to 15 mm, that is, the deviation is large, the balancing accuracy of the center of mass of the entire satellite can be corrected by adjusting the layout position of the heavier single machine; when the deviation between the measured value of the mass characteristic and the index requirement exceeds 15 mm, that is, the deviation is large, the calculated value can be corrected by adding counterweight blocks at appropriate positions, etc. until it meets the accuracy requirements.

[0066] The layout principles for adding counterweights include: the counterweights do not change the existing shape and number of interfaces of the structural plate; the counterweights make full use of the existing single-unit mounting holes of the satellite as much as possible, and are installed under the single unit or bracket; the counterweights do not affect the implementation of thermal control and overall circuit routing; the counterweights occupy as little space as possible within the satellite; the counterweights should not exceed the envelope of the entire satellite and should not affect the satellite's external interfaces; the change in the satellite's moment of inertia caused by the counterweights when retracting and deploying should not exceed the control margin.

[0067] This invention aims to precisely control the calculation accuracy of satellite mass characteristics and improve the accuracy of satellite attitude and orbit control. Addressing the challenges of achieving high-precision mass characteristics for small satellites, this method uses satellite mass characteristic estimates as input and decomposes these indicators into individual satellite subsystems. By monitoring and controlling the manufacturing processes of each subsystem, including its individual components, structure, thermal control, and propulsion, the calculated mass characteristics are calculated. Combined with the measured mass characteristics, the calculation model is iteratively modified and the satellite component layout is adjusted to achieve the required high-precision mass characteristic indicators. This provides a basis for pre-launch dynamic analysis of satellites and safeguards the satellite's on-orbit attitude and orbit control.

[0068] Example 2

[0069] The present invention also provides a high-precision mass characteristic calculation system suitable for small satellites. The high-precision mass characteristic calculation system suitable for small satellites can be implemented by executing the process steps of the high-precision mass characteristic calculation method suitable for small satellites, that is, those skilled in the art can understand the high-precision mass characteristic calculation method suitable for small satellites as a preferred implementation of the high-precision mass characteristic calculation system suitable for small satellites.

[0070] According to the present invention, a high-precision mass characteristic calculation system suitable for small satellites is provided, comprising:

[0071] Module M1: Construct a 3D model of the entire satellite based on its overall layout. While ensuring sufficient space for final assembly operations, each unit is placed at the satellite's horizontal center of mass trim position, and a design margin is reserved based on the difference between the measured weight and the designed weight of each unit.

[0072] Module M2: Calculates the mass characteristics of each satellite component in the satellite's layout coordinate system based on the 3D model to obtain a satellite mass characteristic estimate. This estimate is based on the mass characteristics of each satellite component's 3D model. The calculation module includes individual subsystem models, a propulsion module, a cable network module, a satellite counterweight module, a structure module, and a thermal control module.

[0073] Module M3: Decompose the quality characteristic indicators into each satellite component according to the quality characteristic budget value of the entire satellite.

[0074] Module M4: Control the manufacturing process of each satellite component based on the quality characteristic indicators of each subsystem.

[0075] Module M5: Substitute the measured values ​​or precise design values ​​of the mass characteristics of each satellite component into the three-dimensional model of the entire satellite to calculate the calculated values ​​of the satellite mass characteristics.

[0076] Module M6: Based on the measured values ​​of the satellite's mass characteristics, the calculation model is modified, and the satellite layout is iteratively revised until the measured values ​​meet the accuracy requirements. Module M6 includes determining whether the measured mass characteristics meet the requirements. If so, the mass characteristic calculation is completed. If not, it indicates that the current measured values ​​are inconsistent with the calculated values, and the center of mass deviation exceeds the design requirements. The mass characteristic calculation model is modified, the layout of the satellite components is adjusted, and the process returns to Module M5 until the measured values ​​meet the accuracy requirements. The satellite component layout includes: When the measured mass characteristics deviate from the required values ​​within 5 mm, the trim accuracy of the satellite's center of mass is corrected by adjusting the thermal control and propulsion layouts, or the cable network routing. When the measured mass characteristics deviate from the required values ​​within 5 to 15 mm, the trim accuracy of the satellite's center of mass is corrected by adjusting the layout of heavier components. When the measured mass characteristics deviate from the required values ​​by more than 15 mm, the calculated values ​​are corrected by adding counterweights at appropriate locations until the accuracy requirements are met. The layout principles for adding counterweights include: The counterweights should not alter the existing structural plate shape or number of interfaces; they should maximize the use of existing satellite mounting holes for individual units, and should be installed under the units or brackets. The counterweights should not affect thermal control implementation or overall circuit routing. The counterweights should occupy as little space as possible within the satellite. The counterweights should not exceed the overall satellite envelope or affect external interfaces. The change in the satellite's moment of inertia caused by the counterweights during retraction and deployment should not exceed the control margin.

[0077] Those skilled in the art will appreciate that, in addition to implementing the system and its various devices, modules, and units provided by the present invention in purely computer-readable program code, it is entirely possible to implement the same functions of the system and its various devices, modules, and units provided by the present invention 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 and its various devices, modules, and units provided by the present invention can be considered a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; the devices, modules, and units for implementing various functions can also be considered as both software modules implementing the method and structures within the hardware component.

[0078] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A high-precision mass characteristic calculation method suitable for small satellites, characterized in that: include: Step S1: construct a three-dimensional model of the entire satellite according to the overall layout of the satellite; Step S2: Calculating the mass characteristics of each satellite component in the entire satellite layout coordinate system based on the three-dimensional model to obtain a mass characteristic budget value for the entire satellite; Step S3: Decomposing the quality characteristic index into each satellite component according to the whole satellite quality characteristic budget value; Step S4: Control the manufacturing process of each satellite component based on the quality characteristic indicators of each subsystem; Step S5: Substituting the measured values ​​or accurate design values ​​of the mass characteristics of each satellite component into the three-dimensional model of the entire satellite to calculate the calculated values ​​of the satellite mass characteristics; Step S6: Based on the measured values ​​of the mass characteristics of the entire satellite, the calculation model is modified and the entire satellite layout is iteratively modified until the measured values ​​meet the accuracy requirements.

2. The high-precision mass characteristic calculation method for small satellites according to claim 1, characterized in that: Taking into account the sufficient space margin for final assembly operations, each unit will be placed at the lateral center of mass balance position of the entire satellite, and a design margin will be reserved based on the difference between the actual measured weight and the design weight of each unit.

3. The high-precision mass characteristic calculation method for small satellites according to claim 1, characterized in that: When calculating the budget value of the satellite's mass characteristics, the mass characteristics of the three-dimensional models of each satellite component are substituted into the calculation. The calculation module includes the stand-alone models of each subsystem, the propulsion module, the cable network module, the satellite counterweight module, the structure module, and the thermal control module.

4. The high-precision mass characteristic calculation method for small satellites according to claim 1, characterized in that: The step S6 includes: determining whether the measured value of the quality characteristic meets the index requirements. If so, the quality characteristic calculation is completed; if not, it means that the current measured value is inconsistent with the calculated value, and the center of mass deviation exceeds the design requirements. At this time, by correcting the mass characteristic calculation model, adjusting the layout position of the satellite components, and returning to step S5 until the measured value meets the accuracy requirements.

5. The high-precision mass characteristic calculation method for small satellites according to claim 4, characterized in that: The layout positions of the satellite components include: When the deviation between the measured mass characteristic value and the index requirement is within 5 mm, i.e. the deviation is small, the center of mass balance accuracy of the entire satellite is corrected by adjusting the layout of thermal control and propulsion or the direction of the cable network; When the deviation between the measured mass characteristic value and the index requirement is within 5 to 15 mm, that is, the deviation is large, the balance accuracy of the center of mass of the entire satellite is corrected by adjusting the layout position of the heavier single unit; When the deviation between the measured value of the quality characteristic and the index requirement exceeds 15mm, that is, the deviation is very large, the calculated value shall be corrected by adding counterweight blocks at appropriate positions until it meets the accuracy requirements.

6. The high-precision mass characteristic calculation method for small satellites according to claim 5, characterized in that: The layout principles for adding counterweights include: The counterweight block does not change the existing shape and number of interfaces of the structural plate. The counterweight block makes use of the existing single-machine mounting holes of the satellite as much as possible and is installed under the single machine or bracket. The counterweight block does not affect the implementation of thermal control and the overall circuit routing. The counterweight block occupies as little space as possible within the satellite. The counterweight block should not exceed the envelope of the entire satellite, nor affect the external interface of the satellite. The change in the moment of inertia of the satellite when it is retracted and deployed should not exceed the control margin.

7. A high-precision mass characteristic calculation system suitable for small satellites, characterized in that: include: Module M1: Construct a 3D model of the entire satellite based on its overall layout; Module M2: Calculate the mass characteristics of each satellite component in the entire satellite layout coordinate system based on the three-dimensional model to obtain a mass characteristic budget value of the entire satellite; Module M3: Decomposing the quality characteristic indicators into each satellite component according to the quality characteristic budget value of the whole satellite; Module M4: Controls the manufacturing process of satellite components based on the quality characteristics of each subsystem; Module M5: Substitute the measured values ​​or precise design values ​​of the mass characteristics of each satellite component into the three-dimensional model of the entire satellite to calculate the calculated values ​​of the satellite mass characteristics; Module M6: Based on the measured values ​​of the mass characteristics of the entire satellite, the calculation model is modified and the entire satellite layout is iteratively modified until the measured values ​​meet the accuracy requirements.

8. The high-precision mass characteristic calculation system for small satellites according to claim 7, characterized in that: Taking into account the sufficient space margin for final assembly operations, each unit will be placed at the lateral center of mass balance position of the entire satellite, and a design margin will be reserved based on the difference between the actual measured weight and the design weight of each unit.

9. The high-precision mass characteristic calculation system for small satellites according to claim 7, characterized in that: When calculating the budget value of the satellite's mass characteristics, the mass characteristics of the three-dimensional models of each satellite component are substituted into the calculation. The calculation modules include the stand-alone models of each subsystem, the propulsion module, the cable network module, the satellite counterweight module, the structure module and the thermal control module.

10. The high-precision mass characteristic calculation system for small satellites according to claim 7, characterized in that: The module M6 includes: judging whether the measured value of the quality characteristic meets the index requirements. If so, the quality characteristic calculation is completed; if not, it means that the current measured value is inconsistent with the calculated value, and the center of mass deviation exceeds the design requirements. At this time, by correcting the mass characteristic calculation model, adjusting the layout position of the satellite components, and returning to module M5 until the measured value meets the accuracy requirements.

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