Simulation method and system of low earth orbit satellite constellation

Abstract

This application provides a simulation method and system for a low-Earth orbit satellite constellation. The method includes: obtaining a configuration file for the target satellite constellation; the configuration file includes a set of target component models and a set of target atom models required by the target satellite constellation; the set of target component models includes multi-level target component models with a tree structure; the set of target atom models includes target atom models used by the final-level target component models; the target atom models are implemented using simulation modeling; extracting target component models at each level of the tree structure from a pre-built component model library, and assembling the target component models at each level according to the tree structure to obtain an initial model; extracting target atom models from a pre-built atom model library, establishing communication relationships between the target atom models and the corresponding final-level target component models in the initial model to obtain a simulation model of the target satellite constellation; and conducting simulation experiments on the target satellite constellation based on the simulation model.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of low-orbit satellite constellation simulation, and particularly relates to a simulation method and system of low-orbit satellite constellation. BACKGROUND

[0002] With the development of space technology and electronic technology, various satellite communication systems develop rapidly, satellite platforms and loads show diversified development, and in particular, low-orbit constellation communication systems show large-scale and systematic development trends. In the face of complex and systematic low-orbit constellation communication systems, the cost of investment is huge, the construction period is long, and the constellation system needs to be digitally modeled, and the system effectiveness simulation is used to support the planning, construction, operation effect evaluation, on-orbit service effectiveness and network fault analysis of the constellation communication system.

[0003] The current communication satellite modeling technology mainly adopts a method of modeling the platform, load or each subsystem of the satellite respectively, and uses a modeling language and a mathematical method to describe the functions and performances, which is suitable for modeling and simulation of a specific type or a specific design state of the satellite. The method mainly has the following disadvantages: one is that the model granularity is single, and the simulation granularity cannot be flexibly changed, and the other is that different structures or functions of the satellite must be modeled separately, and the modeling efficiency is low. Therefore, the traditional method is difficult to adapt to the modeling and simulation requirements of large-scale and heterogeneous communication satellite constellations. In view of the above situation, the present application provides a simulation method and system of low-orbit satellite constellation. SUMMARY

[0004] The purpose of the present application is to provide a simulation method and system of low-orbit satellite constellation aiming at the above problems.

[0005] In a first aspect, the present application provides a simulation method of low-orbit satellite constellation, which comprises the following steps:

[0006] obtaining a configuration file of a target satellite constellation; the configuration file comprises a target component model set and a target atomic model set required by the target satellite constellation; the target component model set comprises a plurality of hierarchical target component models with a tree structure; the target atomic model set comprises a target atomic model used by a terminal target component model; and the target atomic model is realized in a simulation modeling manner;

[0007] extracting each hierarchical target component model of the tree structure from a pre-constructed component model library, and assembling the target component models of each level according to the tree structure to obtain an initial model;

[0008] extracting the target atomic model from a pre-constructed atomic model library, establishing a communication relationship between the target atomic model and the corresponding terminal target component model in the initial model to obtain a simulation model of the target satellite constellation;

[0009] performing simulation experiments on the target satellite constellation based on the simulation model.

[0010] According to the technical scheme provided in some embodiments of the present application, the simulation method of the low-orbit satellite constellation further comprises constructing the component model library based on the following method:

[0011] determining the hierarchical relationship between the component models based on the configuration parameter differences of different types of satellites in the constellation group to be modeled, wherein the hierarchical relationship comprises component models having a parent-child relationship from top to bottom, wherein the same function of different types of satellites is used as a parent component model, and the configuration parameters of the same function are used to construct different child component models under the condition of meeting the division requirements;

[0012] constructing component models of different levels to obtain the component model library.

[0013] According to the technical scheme provided in some embodiments of the present application, the simulation method of the low-orbit satellite constellation further comprises constructing the atomic model library based on the following method:

[0014] performing envelope analysis on the final-stage component model to construct an atomic model of the final-stage component model.

[0015] According to the technical scheme provided in some embodiments of the present application, the envelope analysis on the final-stage component model to construct an atomic model of the final-stage component model comprises:

[0016] performing envelope analysis on the final-stage component model to obtain different algorithm requirements of the same function of the component model;

[0017] determining the corresponding mathematical method and modeling language for each algorithm requirement, and establishing the corresponding atomic model based on the corresponding mathematical method and modeling language;

[0018] constructing the atomic model library based on at least one atomic model corresponding to each final-stage component model.

[0019] According to the technical scheme provided in some embodiments of the present application, for a satellite of a first type, the hierarchical relationship of the component model at least comprises:

[0020] a first-level component model, which at least comprises an I-type satellite platform and a narrowband service load distribution system;

[0021] a second-level component model, which at least comprises a G1-type power supply and distribution subsystem and an attitude and orbit control subsystem corresponding to the I-type satellite platform, and a narrowband service feeder load and a narrowband service user load corresponding to the narrowband service load distribution system;

[0022] A three-level component model, the three-level component model at least comprising a low-power power supply component and a small-capacity power distribution unit corresponding to a G1 type power and distribution subsystem, a sensor component, a control computer and an actuator corresponding to an attitude and orbit control subsystem, a Ka feeder beam antenna and a feeder processing unit corresponding to a narrowband service feeder load, and a narrowband service processing unit and a narrowband user beam antenna corresponding to a narrowband service user load.

[0023] According to the technical solutions provided by some embodiments of the present application, for the second type of satellite, the hierarchical relationship of the component model comprises:

[0024] A first-level component model, the first-level component model at least comprising an I type satellite platform and a broadband service load distribution system;

[0025] A second-level component model, the second-level component model at least comprising a G1 type power and distribution subsystem and an attitude and orbit control subsystem corresponding to the I type satellite platform, and a broadband service feeder load and a broadband service user load corresponding to the broadband service load distribution system;

[0026] A three-level component model, the three-level component model at least comprising a low-power power supply component and a small-capacity power distribution unit corresponding to a G1 type power and distribution subsystem, a sensor component, a control computer and an actuator corresponding to an attitude and orbit control subsystem, a Ka feeder beam antenna and a feeder processing unit corresponding to a narrowband service feeder load, and a narrowband service processing unit and a narrowband user beam antenna corresponding to a narrowband service user load.

[0027] According to the technical solutions provided by some embodiments of the present application, for the third type of satellite, the hierarchical relationship of the component model comprises:

[0028] A first-level component model, the first-level component model at least comprising an II type satellite platform and a comprehensive service load distribution system;

[0029] A second-level component model, the second-level component model at least comprising a G2 type power and distribution subsystem and an attitude and orbit control subsystem corresponding to the II type satellite platform, and a comprehensive service feeder load, a broadband service user load and a narrowband service user load corresponding to the comprehensive service load distribution system;

[0030] A three-level component model, the three-level component model at least comprising a high-power power supply component and a large-capacity power distribution unit corresponding to a G2 type power and distribution subsystem, a sensor component, a control computer and an actuator corresponding to an attitude and orbit control subsystem, a QV feeder beam antenna and a feeder processing unit corresponding to a comprehensive service feeder load, a broadband service processing unit and a broadband user beam antenna corresponding to a broadband service user load, and a narrowband service processing unit and a narrowband user beam antenna corresponding to a narrowband service user load.

[0031] In a second aspect, the application provides a simulation system of a low-orbit satellite constellation, comprising:

[0032] a configuration file obtaining module configured to obtain a configuration file of a target satellite constellation; the configuration file comprises a target component model set and a target atomic model set required by the target satellite constellation; the target component model set comprises a plurality of hierarchical target component models having a tree structure; the target atomic model set comprises target atomic models used by terminal target component models; and the target atomic models are implemented in a simulation modeling manner;

[0033] a first extraction module configured to extract the hierarchical target component models having the tree structure from a pre-constructed component model library, and assemble the hierarchical target component models according to the tree structure to obtain an initial model;

[0034] a second extraction module configured to extract the target atomic models from a pre-constructed atomic model library, and establish a communication relationship between the target atomic models and corresponding terminal target component models in the initial model to obtain a simulation model of the target satellite constellation;

[0035] a simulation experiment module configured to perform a simulation experiment on the target satellite constellation based on the simulation model.

[0036] According to certain embodiments of the application, the simulation system of the low-orbit satellite constellation further comprises:

[0037] a first construction module configured to construct a component model library;

[0038] a second construction module configured to construct an atomic model library.

[0039] According to certain embodiments of the application, the first construction module comprises:

[0040] a hierarchical relationship determination submodule configured to determine a hierarchical relationship between component models based on configuration parameter differences of different types of satellites in a constellation group to be modeled; in the hierarchical relationship, the component models have a parent-child relationship from top to bottom, wherein the same function of different types of satellites is used as a parent component model, and configuration parameters of the same function are used to construct different child component models under the condition that the division requirements are met;

[0041] a component model construction submodule configured to construct component models of different levels to obtain the component model library;

[0042] the second construction module comprises:

[0043] an envelope analysis submodule configured to perform envelope analysis on the final-stage component model to obtain different algorithm requirements of the same function of the component model;

[0044] an atomic model construction submodule configured to determine a corresponding mathematical method and modeling language for each algorithm requirement, and establish a corresponding atomic model based on the corresponding mathematical method and modeling language;

[0045] an atomic model library construction submodule configured to construct the atomic model library based on at least one atomic model corresponding to each final-stage component model.

[0046] Compared with the prior art, the method has the following advantages:

[0047] (1) The method improves the modeling efficiency and supports rapid reconstruction of the model, and is suitable for batch modeling of large-scale heterogeneous objects. Based on the component model library and the atomic model library, the heterogeneous object can be reconstructed and modeled by modifying the model configuration file, which has the advantages of rapidity and efficiency;

[0048] (2) The method can effectively reduce the difficulty of modeling of complex heterogeneous systems. Through the hierarchical decomposition of the component model library, each complex modeling object is decomposed into several components with relatively simple functions, and only the final-stage component with the smallest functional envelope needs to be designed one by one, which significantly reduces the difficulty of modeling and model development of complex heterogeneous objects;

[0049] (3) The method improves the reusability of the model and reduces the comprehensive cost of modeling. By constructing the component model library through hierarchical decomposition design, the repeated code in the atomic model due to functional overlap is minimized, and the same component model and atomic model are reused through the model configuration table, which improves the reusability of the model and reduces the workload of model development, thereby reducing the comprehensive cost of modeling;

[0050] (4) The method improves the flexibility and task adaptability of heterogeneous object modeling. For different simulation task requirements, the tree-shaped component model library can be flexibly cut and different atomic models with different calculation accuracies can be flexibly selected, so that the model can meet the simulation task requirements and minimize the simulation calculation amount and the consumption of computing resources, thereby having better task adaptability;

[0051] (5) The method of this invention is highly versatile and the modeling process is easy to standardize. This invention proposes a standardized and detailed design process for component model libraries and atomic model libraries, provides design principles, unifies design steps, facilitates standardized operations, and can be promoted and applied to heterogeneous object modeling in other fields. Attached Figure Description

[0052] Figure 1 A flowchart illustrating the simulation method for a low-Earth orbit satellite constellation provided in Embodiment 1 of this application;

[0053] Figure 2 This is a schematic diagram of the hierarchical tree structure of a component model library in Embodiment 1 of this application;

[0054] Figure 3 This is a schematic diagram of the target satellite constellation in Embodiment 1 of this application;

[0055] Figure 4 for Figure 3 A schematic diagram of the composition of a mid-A type star;

[0056] Figure 5 for Figure 3 A schematic diagram of the composition of a medium B-type star;

[0057] Figure 6 for Figure 3 A schematic diagram of the composition of a medium-C type star;

[0058] Figure 7 A flowchart illustrating the design process of the component model library provided in Embodiment 1 of this application;

[0059] Figure 8 This is a schematic diagram of the component model library established in Embodiment 1 of this application;

[0060] Figure 9 A flowchart illustrating the design of the atomic model library provided in Embodiment 1 of this application;

[0061] Figure 10 This is a schematic diagram of the structure of the atomic model library established in Embodiment 1 of this application;

[0062] Figure 11 This is a schematic diagram of a heterogeneous satellite model applicable to constellation service beam coverage and interference simulation tasks in Embodiment 1 of this application;

[0063] Figure 12-1 This is a schematic diagram of a Type A satellite model applicable to the constellation service processing capability simulation task in Embodiment 1 of this application;

[0064] Figure 12-2 This is a schematic diagram of a Type B satellite model applicable to the constellation service processing capability simulation task in Embodiment 1 of this application;

[0065] Figure 12-3 FIG. 1 is a schematic diagram of a C-type satellite model suitable for constellation service processing capability simulation tasks in Embodiment 1 of the present application. DETAILED DESCRIPTION

[0066] In order for those skilled in the art to better understand the technical solutions of the present application, the present application is described in detail below with reference to the accompanying drawings, and the description in this part is only exemplary and explanatory, and should not have any limiting effect on the protection scope of the present application.

[0067] Embodiment 1

[0068] The present embodiment provides a simulation method of a low-orbit satellite constellation, a flowchart of the method is shown in FIG. 1, and the method comprises the following steps: Figure 1

[0069] S1, obtaining a configuration file of a target satellite constellation; the configuration file comprises a target component model set and a target atomic model set required by the target satellite constellation; the target component model set comprises a plurality of hierarchical target component models with a tree structure; the target atomic model set comprises a target atomic model adopted by a terminal-level target component model; the target atomic model is realized in a simulation modeling manner;

[0070] S2, extracting each hierarchical target component model with a tree structure from a pre-constructed component model library, and assembling the target component models of each level according to the tree structure to obtain an initial model;

[0071] S3, extracting the target atomic model from a pre-constructed atomic model library, establishing a communication relationship between the target atomic model and the corresponding terminal-level target component model in the initial model to obtain a simulation model of the target satellite constellation;

[0072] S4, performing a simulation experiment on the target satellite constellation based on the simulation model.

[0073] Specifically, the configuration file of the target satellite constellation in step S1 is determined according to the simulation task requirements, and the configuration process comprises component model configuration and atomic model configuration. The principle of configuration is: on the basis of meeting the task requirements, try to trim unnecessary component models, and select lightweight atomic models for terminal component models, so as to improve simulation efficiency and reduce consumption of computing resources; each component model obtained after trimming is a target component model, and all target component models form a target component model set; the atomic model corresponding to the terminal target component model in the target component model is a target atomic model, and all target atomic models form a target atomic model set.

[0074] The component model library used in step S2 is constructed based on the following method: ​

[0075] a. Determine the hierarchical relationship between component models based on the configuration parameter differences of different types of satellites in the constellation to be modeled. In the hierarchical relationship, there are parent-child relationships from top to bottom, wherein the same function of different types of satellites is used as a parent component model, and the configuration parameters of the same function are used to build different child component models under the condition of meeting the division requirements;

[0076] b. Build component models of different levels to obtain the component model library.

[0077] The construction of the component model library adopts a design method of starting from the target modeling object and decomposing layer by layer from top to bottom. First, the target modeling object is analyzed for heterogeneity and simulation granularity, and the target modeling object is decomposed into a plurality of first-level component models; then the same design method is used to analyze the first-level component models one by one, and for the first-level component models that have a second-level simulation granularity requirement, they should be further decomposed into a plurality of second-level component models, and this method is used to decompose layer by layer downward, until the last level, and finally a hierarchical and tree-structured component model library is formed; wherein the component models at each level mainly describe the functional envelope and interface of the modeling object, and are mainly used to constrain the interface and connection relationship of different models, but do not describe the behavior logic or physical characteristics of the modeling object.

[0078] When analyzing the target modeling object, the heterogeneity analysis should be performed first, and then the simulation granularity analysis; wherein when analyzing the heterogeneity of the target modeling object, the differences of the target modeling object are analyzed, if they are all isomorphic, then there is no need to further decompose the next level of component models; if they are heterogeneous, then the simulation envelope needs to be further analyzed; the simulation granularity is the granularity of simulation modeling, the coarsest simulation granularity is defined as the first-level granularity, and the finer one is defined as the second-level granularity, and so on. The simulation granularity analysis is performed layer by layer according to the principle of from coarse to fine, that is, according to the simulation requirements to determine whether the next level of modeling with finer granularity is needed, until the simulation requirements of the finest granularity are met.

[0079] The method for determining whether to continue to decompose to the next level is as follows:

[0080] If the current level of modeling object is isomorphic, then it is not necessary to decompose to the next level;

[0081] If the current level of modeling object is heterogeneous, then it needs to be determined whether there is a modeling requirement of the next level of simulation granularity, if there is no finer granularity simulation requirement, then it is not necessary to decompose to the next level; if there is, then it needs to be further decomposed to the next level, until the simulation requirements of the finest granularity of the modeling object are met.

[0082] The final result of the component model library design is a hierarchical and tree-structured structure with the target modeling object as the root node, and each component model is related to each other. The hierarchical tree structure of the component model library is shown in Figure 2 .

[0083] In use, the target component models contained in the configuration file are extracted from the component model library and assembled in a tree structure to obtain an initial model, which is a collection of necessary target component models meeting the task requirements.

[0084] The atomic model library used in step S3 is constructed based on the following method: envelope analysis is performed on the final-stage component models to construct atomic models of the final-stage component models. The method specifically includes: performing envelope analysis on the final-stage component models to obtain different algorithm requirements of the same function of the component models; determining a corresponding mathematical method and modeling language for each algorithm requirement, and establishing a corresponding atomic model based on the corresponding mathematical method and modeling language; and constructing the atomic model library based on the at least one atomic model corresponding to each final-stage component model.

[0085] Unlike the component model which mainly describes the function and interface of the modeling object, the atomic model describes the behavior logic and physical characteristics of the modeling object through specific mathematical methods and modeling languages, and realizes the function and interface defined by a specific component model, and is the smallest model unit that can be instantiated and run.

[0086] The relationship between the atomic model and the component model is that if a certain atomic model realizes the function and interface defined by a certain specific component model, the atomic model is said to correspond to the component model. Each atomic model corresponds to a certain specific component model, but for the same function and interface defined by a component model, multiple atomic models can be designed according to different algorithm implementation methods or simulation accuracies, so as to realize simulation of different methods or different accuracies, that is, the corresponding relationship between the component model and the atomic model is a one-to-many relationship, that is, each atomic model has and only has one corresponding component model; and a component model can have multiple atomic models corresponding thereto.

[0087] The atomic model design should be based on the component model library, sequentially traverse all the final-stage component models in the component model library, and complete the atomic component model design one by one until all the final-stage component models in the component model library have one or more atomic models corresponding thereto. When establishing the atomic model, first, the simulation envelope analysis of the modeling object is performed on all the final-stage component models one by one, that is, according to the maximum envelope of the simulation requirements of the modeling object, it is determined whether different mathematical methods need to be modeled respectively; second, according to the analysis result, one or more atomic models corresponding to each final-stage component model are designed until the simulation envelope requirements of the modeling object are met.

[0088] Next, a specific example is used to describe the above method steps in detail.

[0089] Figure 3A composition diagram of a certain isomerous low-orbit communication constellation (i.e. a target satellite constellation), which is composed of a plurality of satellites designed in different states and working in different orbits. According to the different orbit altitudes, it is divided into an H1 star group working in H1 altitude and an H2 star group working in H2 altitude; according to the different satellite design states, it is divided into A-type stars, B-type stars and C-type stars; wherein the H1 star group contains K B-type stars, and the H2 star group contains M A-type stars and N C-type stars;

[0090] Figure 4 A composition diagram of A-type stars, which are the first type of satellites, and the hierarchical relationship of the component model of the A-type stars at least includes:

[0091] A primary component model, which at least includes an I-type satellite platform and a narrowband service load distribution system;

[0092] A secondary component model, which at least includes a G1-type power supply and distribution subsystem and an orbit control subsystem corresponding to the I-type satellite platform, and a narrowband service feeder load and a narrowband service user load corresponding to the narrowband service load distribution system;

[0093] A tertiary component model, which at least includes a low-power power supply component and a small-capacity power distribution unit corresponding to the G1-type power supply and distribution subsystem, a sensor component, a control computer and an actuator corresponding to the orbit control subsystem, a Ka feeder beam antenna and a feeder processing unit corresponding to the narrowband service feeder load, and a narrowband service processing unit and a narrowband user beam antenna corresponding to the narrowband service user load.

[0094] Figure 5 A composition diagram of B-type stars, which are the second type of satellites, and the hierarchical relationship of the component model of the B-type stars at least includes:

[0095] A primary component model, which at least includes an I-type satellite platform and a wideband service load distribution system;

[0096] A secondary component model, which at least includes a G1-type power supply and distribution subsystem and an orbit control subsystem corresponding to the I-type satellite platform, and a wideband service feeder load and a wideband service user load corresponding to the wideband service load distribution system;

[0097] A tertiary component model, which at least includes a low-power power supply component and a small-capacity power distribution unit corresponding to the G1-type power supply and distribution subsystem, a sensor component, a control computer and an actuator corresponding to the orbit control subsystem, a Ka feeder beam antenna and a feeder processing unit corresponding to the narrowband service feeder load, and a narrowband service processing unit and a narrowband user beam antenna corresponding to the narrowband service user load.

[0098] Figure 6 This is a schematic diagram of the components of a C-type satellite, which is a third type of satellite. The hierarchical relationship of the components of a C-type satellite includes at least the following:

[0099] A primary component model, which includes at least a Type II satellite platform and an integrated operational payload distribution system;

[0100] The secondary component model includes at least the G2 power supply and distribution subsystem and attitude and orbit control subsystem corresponding to the Type II satellite platform, as well as the integrated service load distribution system, broadband service user load and narrowband service user load.

[0101] The three-level component model includes at least a high-power power supply component and a large-capacity power distribution unit corresponding to the G2 type power supply and distribution subsystem, a sensor component, a control computer and an actuator corresponding to the attitude and orbit control subsystem, a QV-fed beam antenna and a feed processing unit corresponding to the integrated service feed load, a broadband service processing unit and a broadband user beam antenna corresponding to the broadband service user load, and a narrowband service processing unit and a narrowband user beam antenna corresponding to the narrowband service user load.

[0102] First, build a component model library.

[0103] Using satellites as the modeling object, component model decomposition design is performed, and the design process is as follows: Figure 7 As shown, the modeling objects in this embodiment are satellites with three different design states: Type A, Type B, and Type C. Independent initial orbital parameters need to be established for each satellite model to ultimately construct a complete constellation model. Among the three types of satellites, Type A and Type B satellites have the same platform design state but are configured with different payloads, while Type C satellites use a different platform and payloads. Therefore, the modeling objects are heterogeneous, requiring simulation granularity analysis.

[0104] In this example, the first-level simulation granularity requires different considerations of the satellite's various orbital distributions and different payload services, simulating and analyzing the Earth coverage of each satellite's carried services. At this simulation granularity, the satellite model needs to calculate its position and attitude at each moment, and combine this with the user beam coverage capability of the carried services to comprehensively simulate the Earth coverage formed by the satellite. Therefore, the first-level simulation granularity requires separate simulations of the platform (i.e., orbital distribution) and the payload. Based on the results of the heterogeneous analysis of the satellite modeling object and the first-level simulation granularity analysis, the satellite's first-level component model is designed as follows: a satellite platform first-level component model and a satellite payload first-level component model; the functions and interface definitions of the first-level components are shown in Table 1.

[0105] Table 1

[0106]

[0107] Next, each primary component needs to be analyzed one by one, and the simulation granularity requirements of different signal satellites are compared. If there are differences and there is a simulation requirement of secondary granularity, it needs to be further decomposed to design a secondary component model.

[0108] a、Satellite platform primary component model decomposition design

[0109] For the satellite platform primary component model, the modeling object is limited to the satellite platform, and the payload part no longer needs to be considered. In this embodiment, the heterogeneous analysis of the satellite platform is that it includes two different design states of type I platform and type II platform, that is, there is heterogeneity; the simulation requirement of secondary granularity is that while simulating the attitude and orbit keeping capability of the satellite platform, the power supply capability difference of different platforms also needs to be simulated in order to simulate the energy supply margin of different satellites and meet the task requirements of satellite capability margin simulation. According to this analysis, the satellite platform component model should continue to be decomposed to design two secondary component models, namely, the power supply and distribution secondary component model and the attitude and orbit control secondary component model; the secondary component functions and interface definitions are shown in Table 2.

[0110] Table 2

[0111]

[0112] a1、Power supply and distribution secondary component model decomposition design

[0113] Firstly, the modeling object heterogeneity analysis is carried out: the power supply and distribution subsystem of the real satellite is divided into two design states of G1 type and G2 type, wherein the G1 type power supply and distribution subsystem is composed of low-power power supply components and medium-capacity power distribution units, and the G2 type power supply and distribution subsystem is composed of high-power power supply components and large-capacity power distribution units, that is, there is heterogeneity. Secondly, the simulation granularity analysis is carried out: in this example, for the power supply and distribution subsystem, it is required to model the G1 type and G2 type power supply and distribution subsystems to simulate the difference in their power supply and distribution capabilities, but the power supply capability of the power supply component and the power distribution capability of the power distribution unit no longer need to be simulated separately, that is, there is no simulation requirement of tertiary granularity. According to this analysis, the power supply and distribution secondary component model has met the most fine-grained simulation requirement, and there is no need to continue to decompose the tertiary component model, and this branch has reached the end level.

[0114] a2、Attitude and orbit control secondary component model decomposition design

[0115] Firstly, the modeling object heterogeneity analysis is carried out: the attitude and orbit control subsystem of the real satellite adopts the same design state, and this branch does not have secondary heterogeneity, so this branch has reached the end level.

[0116] So far, all the secondary branches of the satellite platform primary component model have been traversed, and the decomposition design of the satellite payload primary component model can be carried out.

[0117] b. Satellite payload primary assembly model decomposition design

[0118] The satellite payload subsystems are taken as modeling objects to carry out heterogeneous analysis, including three design states of narrowband service payload, wideband service payload and integrated service payload, wherein the narrowband service payload subsystem includes narrowband service user payload and narrowband service feeder payload; the wideband service payload subsystem includes wideband service user payload and wideband service feeder payload; and the integrated service payload subsystem includes narrowband service user payload, wideband service user payload and integrated service feeder payload, that is, there is heterogeneity. Simulation granularity analysis: in this case, the specific functions of the user service payload and the feeder payload need to be simulated respectively, that is, there is a secondary simulation granularity requirement. According to the above analysis, the satellite payload primary assembly model is decomposed into two secondary assembly models, namely, the user service payload secondary assembly model and the feeder payload secondary assembly model.

[0119] b1. Feeder payload secondary assembly model decomposition design

[0120] The feeder payload in the satellite payload subsystem is taken as a modeling object to carry out heterogeneous analysis, including two design states of Ka feeder payload and QV feeder payload, both of which have the same feeder processing unit, but the Ka feeder payload is equipped with a Ka feeder beam forming unit for supporting narrowband service feeder, and the QV feeder payload is equipped with a QV feeder beam forming unit for supporting wideband service feeder and integrated service feeder, and there is heterogeneity. Simulation granularity analysis: in this case, the specific functions of the feeder beam forming unit and the feeder processing unit need to be simulated respectively, that is, there is a tertiary simulation granularity requirement. According to the above analysis, the feeder payload secondary assembly model is decomposed into two tertiary assembly models, namely, the feeder beam tertiary assembly model and the feeder processing tertiary assembly model.

[0121] b11. Feeder beam tertiary assembly model decomposition design

[0122] The feeder payload beam forming unit of the satellite is taken as a modeling object to carry out heterogeneous analysis, including two design states of Ka beam forming unit and QV beam forming unit, and there is heterogeneity. Simulation granularity analysis: there is no need for more fine-grained simulation of the Ka feeder beam forming unit and the QV beam forming unit, that is, there is no tertiary simulation granularity requirement. According to this analysis, the feeder beam tertiary assembly model has met the most fine-grained simulation requirement, and there is no need to continue to decompose the next level of assembly model, and this branch has reached the end level.

[0123] b12. Feeder processing tertiary assembly model decomposition design

[0124] The feeder processing unit of the satellite is taken as the modeling object to carry out heterogeneous analysis: since the A, B and C type satellites all adopt the same design state of the feeder processing unit, there is no heterogeneity. Therefore, the feeder processing three-level component model does not need to continue to decompose the next level component model, and this branch has reached the end level.

[0125] b2, user service load two-level component model decomposition design

[0126] The user service load two-level component model branch is decomposed and designed according to the same method until the end level.

[0127] As shown in Figure 8 , the component model library designed according to the application is a hierarchical tree structure, which takes the target modeling object as the root node and describes the connection relationship between the component models.

[0128] Second, build the atomic model library.

[0129] The design process of the atomic model library is shown in Figure 9 , in the component model library of the heterogeneous satellite in this example, the satellite platform part includes two end-level component models: power supply and distribution two-level component model and attitude and orbit control two-level component model. The corresponding atomic models need to be designed one by one.

[0130] a1, atomic model design corresponding to the power supply and distribution two-level component model

[0131] In this example, the atomic model corresponding to the power supply and distribution two-level component model needs to meet the modeling requirements of the G1 type and G2 type power supply and distribution subsystems respectively, therefore, the atomic models are established for the G1 and G2 type power supply and distribution subsystems, and the different characteristics are described by modeling language and mathematical methods respectively, which can meet the simulation envelope requirements, therefore, the G1 type power supply and distribution atomic model and the G2 type power supply and distribution atomic model are designed respectively, corresponding to the power supply and distribution two-level component model.

[0132] b1, atomic model design corresponding to the attitude and orbit control two-level component model

[0133] First, carry out simulation envelope analysis of the modeling object, in this example, the attitude and orbit control system needs to be modeled in two different ways: a high-precision attitude and orbit control model that can accurately simulate the real satellite attitude and orbit control error with high precision, and a lightweight attitude and orbit control model that can complete fast calculation with minimum resource consumption, which are applied to different simulation scenarios respectively, therefore, the high-precision attitude and orbit control atomic model and the lightweight attitude and orbit control atomic model are designed respectively, corresponding to the attitude and orbit control two-level component model.

[0134] According to the same method, corresponding atomic models can be designed for all end-level component models of the satellite load part, and the final result is shown in Figure 10 .

[0135] Thirdly, according to the simulation task requirements, the configuration file of the target satellite constellation is determined.

[0136] In this example, the simulation tasks of the built model include: constellation service beam coverage and interference simulation task and constellation service processing capacity simulation task, which will be described in the following two simulation tasks.

[0137] a) Constellation service beam coverage and interference simulation task

[0138] This task needs to accurately evaluate the service coverage capability of the whole constellation to the ground according to the position, attitude and service beam coverage capability of each satellite, and quantitatively analyze the interference caused by the overlap of service beam coverage between different satellites.

[0139] According to the above task requirements and model configuration principles, the component model configuration is as follows: the power supply and distribution secondary component of the platform part is cut; the feeder load secondary component of the load part is cut; the user service processing tertiary component model under the user service load secondary component is cut; in addition, for the satellite load primary component of the C-type satellite, two user service load secondary components should be configured according to the design state.

[0140] The atomic model configuration is as follows: in order to ensure the simulation accuracy of the attitude and orbit control, the attitude and orbit control secondary component should be selected with high-precision attitude and orbit control atomic model; for the A-type star user beam tertiary component, the narrowband user beam atomic model should be selected according to the design state; for the B-type star user beam tertiary component, the wideband user beam atomic model should be selected according to the design state; for the two user beam tertiary components of the C-type satellite, the narrowband user beam atomic model and the wideband user beam atomic model should be selected according to the design state respectively.

[0141] According to the above configuration method, the target component model set and the target atomic model set can be obtained, and the model configuration file can be described in JSON file format. Different model configuration files can be developed to meet different simulation task requirements.

[0142] b) Constellation service processing capacity simulation task

[0143] This task needs to comprehensively evaluate the maximum processing capacity of different services of the whole constellation according to the processing capacity of each satellite for the carried services (including user service processing and feeder processing), and quantitatively analyze the energy supply margin of the power supply and distribution system of each type of satellite.

[0144] According to the above task requirements and model configuration principles, the component model configuration is as follows: the power supply and distribution secondary component of the platform part needs to be added; the feeder load secondary component of the load part needs to be added; for the satellite load of the C-type satellite, two user service load secondary components are still configured according to the design state.

[0145] The atomic model is configured as follows: since the task does not have the requirement of high-precision attitude and orbit control simulation, the attitude and orbit control secondary component should be selected and matched with a lightweight attitude and orbit control atomic model; for the three types of satellites A, B and C, the corresponding atomic model is selected according to the design state.

[0146] According to the above configuration method, the target component model set and the target atomic model set can be obtained, and the model configuration file can be described in JSON file format. Different model configuration files can be developed to meet different simulation task requirements, so as to be flexible and adaptable.

[0147] Fourthly, the simulation model of the target satellite constellation is obtained and simulation experiments are performed.

[0148] According to the model configuration file obtained in the above step, the corresponding models are called from the component model library and the atomic model library, and the communication relationship between the associated models is established, so that one or more target object models meeting the simulation task can be quickly constructed. In this embodiment, the simulation model of the target constellation includes A-type simulation model, B-type simulation model and C-type simulation model. The results of the heterogeneous satellite model suitable for the constellation business beam coverage and interference simulation task are as shown in Figure 11 , the results of the heterogeneous satellite model suitable for the constellation business processing capacity simulation task are as shown in Figure 12-1 , Figure 12-2 and Figure 12-3 . Finally, based on the above simulation model, the corresponding simulation experiments can be performed on the target satellite constellation.

[0149] The present application overcomes the shortcomings of the existing modeling method, such as single model granularity, low efficiency of heterogeneous object modeling, and difficulty in adapting to different simulation task requirements, and proposes a simulation method for low-orbit satellite constellation based on a component model library and an atomic model library, to solve the technical problem of flexible and rapid modeling of large-scale and heterogeneous communication satellite constellations.

[0150] Based on a set of self-designed component model library, atomic model library and a custom model reconstruction configuration interface, the present application can select component models and atomic models according to different modeling requirements, so as to realize batch and rapid modeling of homogeneous or heterogeneous communication satellites according to different granularities. The present application not only has flexibility in satellite modeling, but also improves the efficiency of communication satellite digital modeling, and meets the requirements of rapid modeling of large-scale and heterogeneous communication satellite constellations. The present application can quickly construct a large number of communication satellite simulation models, and is suitable for system effectiveness simulation of large-scale communication constellation systems.

[0151] Embodiment 2

[0152] The embodiment provides a simulation system of a low-orbit satellite constellation which matches the simulation method of the low-orbit satellite constellation described in embodiment 1, and the simulation system comprises a configuration file acquisition module, a first extraction module, a second extraction module and a simulation experiment module.

[0153] The acquisition module is configured to acquire a configuration file of a target satellite constellation; the configuration file comprises a target component model set and a target atomic model set required by the target satellite constellation; the target component model set comprises a plurality of hierarchical target component models with a tree structure; the target atomic model set comprises a target atomic model used by a terminal target component model; and the target atomic model is realized in a simulation modeling manner;

[0154] The first extraction module is configured to extract the hierarchical target component models with the tree structure from a pre-constructed component model library, and assemble the hierarchical target component models according to the tree structure to obtain an initial model;

[0155] The second extraction module is configured to extract the target atomic model from a pre-constructed atomic model library, and establish a communication relationship between the target atomic model and a corresponding terminal target component model in the initial model to obtain a simulation model of the target satellite constellation;

[0156] The simulation experiment module is configured to perform a simulation experiment on the target satellite constellation based on the simulation model.

[0157] Further, the simulation system further comprises a first construction module and a second construction module. The first construction module is configured to construct a component model library; and the second construction module is configured to construct an atomic model library.

[0158] The first construction module comprises a hierarchical relationship determination submodule and a component model construction submodule;

[0159] The hierarchical relationship determination submodule is configured to determine a hierarchical relationship between component models based on configuration parameter differences of different types of satellites in a constellation group to be modeled; in the hierarchical relationship, the component models have a parent-child relationship from top to bottom, wherein the same function of different types of satellites is used as a parent component model, and configuration parameters of the same function are used to construct different child component models under the condition that the division requirements are met;

[0160] The component model construction submodule is configured to construct component models of different levels to obtain the component model library.

[0161] The second construction module comprises an envelope analysis submodule, an atomic model construction submodule and an atomic model library construction submodule;

[0162] The envelope analysis submodule is configured to perform envelope analysis on the final-stage component model to obtain different algorithm requirements of the same function of the component model;

[0163] The atomic model construction submodule is configured to determine a corresponding mathematical method and modeling language for each algorithm requirement, and establish a corresponding atomic model based on the corresponding mathematical method and modeling language.

[0164] The atomic model library construction submodule is configured to construct the atomic model library based on at least one atomic model corresponding to each final-stage component model.

[0165] The simulation system of the low-orbit satellite constellation provided in this embodiment adopts the simulation method of the low-orbit satellite constellation provided in embodiment 1, and the specific method steps are referred to in embodiment 1, and this embodiment will not be described here.

[0166] The principles and implementation modes of the present application are described by using specific examples in this document, and the above examples are only used to help understand the method of the present application and its core idea. The above description is only the preferred implementation mode of the present application. It should be pointed out that, due to the limitation of language expression, there are infinite specific structures, and for ordinary skilled persons in the technical field, some improvements, refinements or changes can be made without departing from the principles of the present application, and the above technical features can be combined in an appropriate manner. These improvements, refinements, changes or combinations, or the direct application of the inventive concept and technical solution to other occasions without improvement, shall be regarded as the protection scope of the present application.

Claims

1. A simulation method of a low earth orbit satellite constellation, characterized in that, The method comprises the following steps: Obtaining a configuration file of a target satellite constellation; the configuration file comprises a target component model set and a target atomic model set required by the target satellite constellation; the target component model set comprises a plurality of hierarchical target component models with a tree structure; the target atomic model set comprises target atomic models adopted by end-level target component models; the target atomic models are implemented in a simulation modeling manner; Extracting the hierarchical target component models with the tree structure from a pre-constructed component model library, and assembling the hierarchical target component models according to the tree structure to obtain an initial model; Extracting the target atomic models from a pre-constructed atomic model library, and establishing a communication relationship between the target atomic models and corresponding end-level target component models in the initial model to obtain a simulation model of the target satellite constellation; Performing a simulation experiment on the target satellite constellation based on the simulation model; The atomic model library is constructed based on the following method: Performing envelope analysis on the end-level component models to construct atomic models of the end-level component models; It comprises: performing envelope analysis on the end-level component models to obtain different algorithm requirements of the same function of the component models; For each algorithm requirement, determine the corresponding mathematical method and modeling language, and establish the corresponding atomic model based on the corresponding mathematical method and modeling language; Based on at least one atomic model corresponding to each end-level component model, the atomic model library is constructed.

2. The simulation method of claim 1, wherein, It also includes constructing the component model library based on the following method: Determine the hierarchical relationship between component models based on the configuration parameter differences of different types of satellites in the to-be-modeled constellation group; in the hierarchical relationship, the component models have a parent-child relationship from top to bottom, wherein the same function of different types of satellites is used as a parent component model, and the configuration parameters of the same function are used to construct different child component models under the condition of meeting the division requirements; Constructing component models of different levels to obtain the component model library.

3. The simulation method of claim 2, wherein, For satellites of the first type, the hierarchical relationship of the component models at least comprises: A primary component model, the primary component model at least comprises an I-type satellite platform and a narrowband business load distribution system; A secondary component model, the secondary component model at least comprises a G1-type power distribution subsystem and an attitude and orbit control subsystem corresponding to the I-type satellite platform, and a narrowband business feeder load and a narrowband business user load corresponding to the narrowband business load distribution system; A tertiary component model, the tertiary component model at least comprises a low-power power supply component and a small-capacity power distribution unit corresponding to the G1-type power distribution subsystem, a sensor component, a control computer and an actuator corresponding to the attitude and orbit control subsystem, a Ka feeder beam antenna and a feeder processing unit corresponding to the narrowband business feeder load, and a narrowband business processing unit and a narrowband user beam antenna corresponding to the narrowband business user load.

4. The simulation method of claim 2, wherein, For satellites of the second type, the hierarchical relationship of the component models comprises: A primary component model, the primary component model at least comprises an I-type satellite platform and a wideband business load distribution system; The second component model at least includes a G1 power distribution subsystem and an attitude and orbit control subsystem corresponding to a Type I satellite platform, and a broadband service feeder payload and a broadband service user payload corresponding to a broadband service payload distribution system; The third component model at least includes a low-power power supply component and a medium-capacity power distribution unit corresponding to the G1 power distribution subsystem, a sensor component, a control computer and an actuator corresponding to the attitude and orbit control subsystem, a QV feeder beam antenna and a feeder processing unit corresponding to the broadband service feeder payload, and a broadband service processing unit and a broadband user beam antenna corresponding to the broadband service user payload.

5. The method for simulating a constellation of low earth orbit satellites of claim 2, wherein, For the third type of satellite, the hierarchical relationship of the component model includes: The first component model at least includes a Type II satellite platform and an integrated service payload distribution system; The second component model at least includes a G2 power distribution subsystem and an attitude and orbit control subsystem corresponding to the Type II satellite platform, and an integrated service feeder payload, a broadband service user payload and a narrowband service user payload corresponding to the integrated service payload distribution system; The third component model at least includes a high-power power supply component and a large-capacity power distribution unit corresponding to the G2 power distribution subsystem, a sensor component, a control computer and an actuator corresponding to the attitude and orbit control subsystem, a QV feeder beam antenna and a feeder processing unit corresponding to the integrated service feeder payload, a broadband service processing unit and a broadband user beam antenna corresponding to the broadband service user payload, and a narrowband service processing unit and a narrowband user beam antenna corresponding to the narrowband service user payload.

6. A simulation system of a low earth orbit satellite constellation, characterized in that, It includes: A configuration file acquisition module configured to acquire a configuration file of a target satellite constellation; the configuration file includes a target component model set and a target atomic model set required by the target satellite constellation; The target component model set includes a plurality of hierarchical target component models with a tree structure; the target atomic model set includes target atomic models used by the last-level target component models; the target atomic models are implemented in a simulation modeling manner; A first extraction module configured to extract each level of the target component model with a tree structure from a pre-constructed component model library, and assemble the target component models of each level according to the tree structure to obtain an initial model; A second extraction module configured to extract the target atomic models from a pre-constructed atomic model library, and establish a communication relationship between the target atomic models and corresponding last-level target component models in the initial model to obtain a simulation model of the target satellite constellation; A simulation experiment module configured to perform a simulation experiment on the target satellite constellation based on the simulation model; A second construction module configured to construct an atomic model library; The second construction module includes: An envelope analysis submodule configured to perform envelope analysis on the final-stage target component model to obtain different algorithm requirements of the same function of the component model; An atomic model construction submodule configured to determine a corresponding mathematical method and modeling language for each algorithm requirement, and establish a corresponding atomic model based on the corresponding mathematical method and modeling language; An atomic model library construction submodule configured to construct the atomic model library based on at least one atomic model corresponding to each final-stage component model.

7. The simulation system of a constellation of low Earth orbit satellites of claim 6, characterized in that, Further comprising: A first construction module configured to construct a component model library.

8. The simulation system of a constellation of low Earth orbit satellites of claim 7, characterized in that, The first construction module comprises: A hierarchical relationship determination submodule configured to determine a hierarchical relationship between component models based on configuration parameter differences of different types of satellites in the constellation group to be modeled; in the hierarchical relationship, the component models have a parent-child relationship from top to bottom, wherein the same function of different types of satellites is used as a parent component model, and the configuration parameters of the same function are used to construct different child component models under the condition of meeting the division requirements; A component model construction submodule configured to construct component models of different levels to obtain the component model library.

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