Simulation processing method and device for satellite

Abstract

The embodiment of the invention provides a simulation processing method and device for satellites, and the method comprises the steps: determining load attribute data and subsystem attribute data corresponding to a target satellite, the load attribute data being attribute data of a plurality of satellite loads carried to the target satellite, and the subsystem attribute data being attribute data of the plurality of satellite loads carried to the target satellite; the subsystem attribute data is attribute data of a plurality of satellite subsystems for constructing the target satellite, and each satellite subsystem operates based on a plurality of satellite loads; constructing a plurality of simulation load models corresponding to the plurality of satellite loads according to the load attribute data, constructing a plurality of simulation subsystems corresponding to the plurality of satellite subsystems according to the subsystem attribute data, and operating the plurality of simulation load models and the plurality of simulation subsystems; and determining load power consumption simulation data of each satellite load according to the plurality of simulation load models and the plurality of simulation subsystems in operation, and determining a satellite power consumption simulation result of the target satellite based on the load power consumption simulation data.

Description

Technical Field

[0001] The embodiments of this specification relate to the field of satellite technology, and in particular, to a simulation processing method for satellites; one or more embodiments of this specification also relate to a simulation processing device for satellites, a computing device, a computer-readable storage medium, and a computer program product. Background Art

[0002] With the development of aerospace technology, artificial satellite technology has been widely used in various scenarios. Therefore, the demand for building artificial satellite systems is also increasing.

[0003] Currently, in the process of building satellite systems, there is a problem that the power consumption of satellite systems cannot be accurately estimated, which makes it impossible to design and build satellite systems with better performance. Therefore, how to accurately estimate the power consumption of satellite systems in the process of designing satellite systems has become an urgent problem to be solved. Summary of the invention

[0004] In view of this, an embodiment of this specification provides a simulation processing method for a satellite. One or more embodiments of this specification also relate to a simulation processing device for a satellite, a computing device, a computer-readable storage medium, and a computer program product to solve the technical defects existing in the prior art.

[0005] According to a first aspect of an embodiment of this specification, a simulation processing method for a satellite is provided, including: Determine payload attribute data and subsystem attribute data corresponding to the target satellite, wherein the payload attribute data is attribute data of multiple satellite payloads carried on the target satellite, and the subsystem attribute data is attribute data of multiple satellite subsystems constituting the target satellite, and each satellite subsystem operates based on the multiple satellite payloads; Constructing a plurality of simulation load models corresponding to the plurality of satellite loads according to the load attribute data, constructing a plurality of simulation subsystems corresponding to the plurality of satellite subsystems according to the subsystem attribute data, and running the plurality of simulation load models and the plurality of simulation subsystems; According to the multiple simulation payload models and the multiple simulation subsystems in operation, the payload power consumption simulation data of each satellite payload is determined, and based on the payload power consumption simulation data, the satellite power consumption simulation result of the target satellite is determined.

[0006] According to a second aspect of an embodiment of this specification, a simulation processing device for a satellite is provided, including: A data determination module is configured to determine payload attribute data and subsystem attribute data corresponding to the target satellite, wherein the payload attribute data is attribute data of multiple satellite payloads carried on the target satellite, and the subsystem attribute data is attribute data of multiple satellite subsystems constituting the target satellite, and each satellite subsystem operates based on the multiple satellite payloads; A model construction module is configured to construct a plurality of simulation load models corresponding to the plurality of satellite loads according to the load attribute data, construct a plurality of simulation subsystems corresponding to the plurality of satellite subsystems according to the subsystem attribute data, and run the plurality of simulation load models and the plurality of simulation subsystems; The result determination module is configured to determine the payload power consumption simulation data of each satellite payload according to the multiple simulation payload models and the multiple simulation subsystems in operation, and determine the satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data.

[0007] According to a third aspect of an embodiment of this specification, a computing device is provided, including: Memory and processor; The memory is used to store computer programs / instructions, and the processor is used to execute the computer programs / instructions. When the computer programs / instructions are executed by the processor, the steps of the above-mentioned simulation processing method for the satellite are implemented.

[0008] According to a fourth aspect of the embodiments of this specification, a computer-readable storage medium is provided, which stores a computer program / instruction, and when the computer program / instruction is executed by a processor, the steps of the above-mentioned simulation processing method for a satellite are implemented.

[0009] According to a fifth aspect of the embodiments of this specification, a computer program product is provided, including a computer program / instruction, which implements the steps of the above-mentioned simulation processing method for a satellite when executed by a processor.

[0010] The simulation processing method for satellites provided in one or more embodiments of the present specification can construct and configure multiple simulation payload models corresponding to multiple satellite payloads of the target satellite based on the payload attribute data corresponding to the target satellite, and construct multiple simulation subsystems corresponding to the multiple satellite subsystems of the target satellite according to the subsystem attribute data of the target satellite. By running multiple simulation payload models and multiple simulation subsystems, the actual operation of the satellite payload is simulated, so as to accurately determine the payload power consumption simulation data of each satellite payload, and determine the satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data; avoid the problem of being unable to accurately estimate the power consumption of the satellite system in the process of building the satellite system; and realize the use of accurate satellite power consumption simulation results to design and build a satellite system with better performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 It is an application schematic diagram of a simulation processing method for a satellite provided by an embodiment of this specification; Figure 2 It is a flow chart of a simulation processing method for a satellite provided by an embodiment of this specification; Figure 3 It is a processing flow chart of a simulation processing method for a satellite provided by an embodiment of this specification; Figure 4 It is a structural schematic diagram of a simulation processing device for a satellite provided by an embodiment of this specification; Figure 5 It is a structural block diagram of a computing device provided by an embodiment of this specification. DETAILED DESCRIPTION

[0012] Many specific details are described in the following description to facilitate a full understanding of this specification. However, this specification can be implemented in many other ways than those described herein, and those skilled in the art can make similar generalizations without violating the connotation of this specification, so this specification is not limited to the specific implementation disclosed below.

[0013] The terms used in one or more embodiments of this specification are only for the purpose of describing specific embodiments, and are not intended to limit one or more embodiments of this specification. The singular forms of "a", "said" and "the" used in one or more embodiments of this specification and the appended claims are also intended to include plural forms, unless the context clearly indicates other meanings. It should also be understood that the term "and / or" used in one or more embodiments of this specification refers to and includes any or all possible combinations of one or more associated listed items.

[0014] It should be understood that although the terms first, second, etc. may be used to describe various information in one or more embodiments of this specification, this information should not be limited to these terms. These terms are only used to distinguish the same type of information from each other. For example, without departing from the scope of one or more embodiments of this specification, the first may also be referred to as the second, and similarly, the second may also be referred to as the first. Depending on the context, the word "if" as used herein may be interpreted as "at the time of" or "when" or "in response to determining".

[0015] In addition, it should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, stored data, displayed data, etc.) involved in one or more embodiments of this specification are all information and data authorized by the user or fully authorized by all parties, and the collection, use and processing of relevant data must comply with the relevant laws, regulations and standards of the relevant countries and regions, and provide corresponding operation entrances for users to choose to authorize or refuse.

[0016] In this specification, a simulation processing method for a satellite is provided. One or more embodiments of this specification also involve a simulation processing device for a satellite, a computing device, a computer-readable storage medium and a computer program product, which are described in detail one by one in the following embodiments.

[0017] See also Figure 1 , Figure 1 A schematic diagram of an application of a simulation processing method for a satellite according to an embodiment of the present specification is shown. Figure 1 It can be seen that the user sends the load configuration data and subsystem configuration information to the server 104 through the client 102. The server 104 builds the power consumption model corresponding to each load on the simulation platform according to the load configuration data, and builds the corresponding satellite subsystem model according to the subsystem configuration information of each subsystem, and runs the power consumption model and the satellite subsystem model; according to the call operation of the model of each subsystem for the load, the power consumption model is run to perform specific operations, so as to determine the load power consumption data within one orbit or a period of time. According to the load power consumption data, the total power consumed by various loads within one orbit or a period of time is calculated, and the total power consumed by each load is added to obtain the satellite energy cost within one orbit or a period of time; the total satellite energy cost is fed back to the client, and the model design is optimized based on the optimization instruction issued by the client.

[0018] See also Figure 2 , Figure 2 A flowchart of a simulation processing method for a satellite provided according to an embodiment of the present specification is shown, which specifically includes the following steps.

[0019] Step 202: Determine the payload attribute data and subsystem attribute data corresponding to the target satellite, wherein the payload attribute data is the attribute data of multiple satellite payloads carried on the target satellite, and the subsystem attribute data is the attribute data of multiple satellite subsystems constructing the target satellite, and each satellite subsystem operates based on the multiple satellite payloads.

[0020] The target satellite may be understood as any artificial satellite or satellite system, for example, the target satellite may be a low-orbit communication constellation, a low earth orbit satellite, a medium earth orbit satellite, a geostationary orbit satellite, a geosynchronous orbit satellite, a communication satellite, a meteorological satellite, a navigation satellite, etc., without specific limitation. In one or more embodiments provided in this specification, the target satellite may be a low-orbit communication constellation, which refers to a satellite network consisting of a group of communication satellites located in low earth orbit.

[0021] Satellite payloads can be understood as different types of equipment or systems that can be carried on the target satellite. Each payload has its specific functions and service objectives. For example, the satellite payload can be A payload, B payload, C payload, D payload, E payload, F payload, and other payloads.

[0022] The payload attribute data can be understood as the attribute data corresponding to the satellite payload. Since the satellite payloads that can be carried on the target satellite are of many types, have complex working conditions and multiple working modes, they also have different usage requirements in different time periods and different regions. In order to accurately calculate the satellite energy expenditure, it is necessary to determine the attribute information of each payload according to the actual situation of the mission profile and working mode, and establish power consumption models of various payloads (i.e., simulation payload models) based on this. For example, the payload attribute data can be payload power consumption, payload working period, payload working sequence, etc.

[0023] The load power consumption may be appropriate load power consumption data selected according to the type and function of the load, and the load power consumption may be used as an input parameter of the load power consumption model. The load power consumption may refer to the average power consumed by the load in a certain working mode, which reflects the demand level of the load on the power system.

[0024] The load working period can be determined according to the mission profile and working mode, and can refer to the length of time that the load operates in a certain working mode, which reflects the continuity of the load's demand for the power system.

[0025] The load working sequence can be determined according to the mission profile and working mode, and the working sequence of various loads in one orbit or within a period of time. The load working sequence can refer to the order in which the loads operate in a certain working mode, which reflects the conflicting requirements of the loads on the power system.

[0026] An embodiment of the present specification provides attribute data of a satellite payload in a simulation processing method for a satellite, and the attribute information can be a single-circuit energy balance parameter diagram of the satellite; in the process of constructing multiple simulation payload models and the multiple simulation subsystems, the design is carried out based on the inherent principle of satellite energy balance design; the relevant parameters such as 100% working power consumption of payload A, 7 minutes working of payload B and payload C, 25% working of payload A for 27 minutes, no working of payload B, and no working of payload C are described as attribute data; the corresponding power consumption calculation is described by a constraint module, and the parameters are connected as input to the constraint module (i.e., a simulation algorithm module, which is implemented by an algorithm formula and is used to calculate the power consumption of the satellite payload).

[0027] The satellite subsystem can be understood as the subsystem that constitutes the target satellite. For example, the satellite subsystem can be a measurement and control subsystem, an electric propulsion subsystem, an attitude and orbit control subsystem, an integrated electronic subsystem, a power supply subsystem, and other subsystems.

[0028] The subsystem attribute data may be understood as attribute data corresponding to the satellite subsystem. For example, the subsystem attribute information may be system configuration data of the satellite subsystem, or payload information associated with the satellite subsystem.

[0029] It should be noted that each satellite subsystem operates based on the multiple satellite payloads, which can be understood as the satellite subsystem needs to call or use various types of payloads to implement the subsystem functions during operation.

[0030] In one or more embodiments provided in this specification, the simulation processing method for a satellite provided in this specification can be applied to a server, which can receive data sent by a user through a client, and return the satellite power consumption simulation result determined by the data to the client for display to the user, thereby facilitating the user to design or construct the target satellite based on the satellite power consumption simulation result. The specific implementation method is as follows: The determining of the payload attribute data and subsystem attribute data corresponding to the target satellite includes: receiving the payload attribute data and the subsystem attribute data corresponding to the target satellite sent by a client, wherein the payload attribute data and the subsystem attribute data are sent by the client when a user performs a data upload operation on the client; After determining the satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data, the method further includes: The satellite power consumption simulation result is sent to the client.

[0031] Among them, the server end applied by the simulation processing method for satellite provided in this specification can be a server, a cloud server, a data processing system, and the client end can be a mobile terminal, a smart device, etc.

[0032] Specifically, the user can perform a data upload operation through the data processing page provided by the client (such as a web page, an application page), thereby providing the payload attribute data and the subsystem attribute data to the client; the client will send the payload attribute data and the subsystem attribute data to the server to calculate the satellite power consumption simulation results.

[0033] After the server completes the calculation of the satellite power consumption simulation result based on the data, the satellite power consumption simulation result is sent to the client for display to the user, so that the user can design, build or adjust the target satellite based on the satellite power consumption simulation result.

[0034] Step 204: construct multiple simulation payload models corresponding to the multiple satellite payloads according to the payload attribute data, construct multiple simulation subsystems corresponding to the multiple satellite subsystems according to the subsystem attribute data, and run the multiple simulation payload models and the multiple simulation subsystems.

[0035] The simulation load model can be understood as a mathematical model or simulation model corresponding to the satellite payload, which is used to simulate the operation of the real satellite payload, so as to determine the power consumption data of the satellite payload; the simulation load model can be a power consumption model or energy expenditure model corresponding to the satellite payload.

[0036] The simulation subsystem can be understood as a mathematical model or simulation model corresponding to the satellite subsystem, which is used to simulate the operation of the real satellite subsystem, so as to determine the power consumption data of the satellite payload.

[0037] In one or more embodiments provided in this specification, the payload attribute data includes payload configuration data, payload power consumption data, payload operation time data, and payload operation sequence data corresponding to the satellite payload, and the subsystem attribute data includes subsystem configuration data corresponding to the satellite subsystem and satellite payload call data; The step of constructing a plurality of simulation payload models corresponding to the plurality of satellite payloads according to the payload attribute data comprises: Constructing the plurality of simulation payload models corresponding to the plurality of satellite payloads according to the payload configuration data, the payload power consumption data, the payload operation time data, and the payload operation sequence data; Constructing a plurality of simulation subsystems corresponding to the plurality of satellite subsystems according to the subsystem attribute data includes: Constructing a plurality of simulation subsystems corresponding to the plurality of satellite subsystems according to the subsystem configuration data and the satellite payload call data, wherein the plurality of simulation subsystems operate by calling satellite payloads.

[0038] Among them, the payload configuration data can be understood as the data of the model and configuration of the satellite payload; the payload power consumption data can be understood as the payload power consumption; the payload operation time data can be understood as the payload working period of the satellite payload; the payload operation sequence data can be understood as the payload working sequence of the satellite payload; the subsystem configuration data can be understood as the data of the model and system configuration of the subsystem; the satellite payload call data can be understood as the identification information of the satellite payload that needs to be called during the operation of the satellite subsystem.

[0039] The satellite payload call data is used to establish an association relationship between each satellite subsystem and the satellite payload. The simulation subsystem establishes a call or usage relationship with the previously associated satellite payload through the satellite payload call data.

[0040] For example, this method can construct a power consumption model corresponding to the satellite payload according to the data of the model and configuration of the satellite payload, payload power consumption, payload working period, payload working sequence, etc., using a simulation platform.

[0041] Moreover, according to the data of the model and system configuration corresponding to the satellite subsystem, using a simulation platform, construct a subsystem simulation model corresponding to the satellite subsystem, and establish an association relationship between the power consumption model of the payload and the subsystem simulation model using the satellite payload call data, facilitating subsequent smooth simulation operation.

[0042] The simulation platform can be understood as a platform that uses digital models to support system description and engineering activities.

[0043] It should be noted that the constructed power consumption model of the payload and the subsystem simulation model can be understood as the satellite model of the target satellite. Taking the satellite energy balance analysis as an example, in the forward satellite design process, use the MBSE model to construct the mission profile and working mode, and develop the on-board energy overhead model in combination with the mission profile and working mode.

[0044] Step 206: Determine the payload power consumption simulation data of each satellite payload according to the plurality of simulation payload models and the plurality of simulation subsystems during operation, and determine the satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data.

[0045] Among them, the payload power consumption simulation data can be understood as the power consumption data of the satellite payload obtained by simulating by running multiple simulation payload models and the multiple simulation subsystems. For example, the payload power consumption simulation data can be the amount of electricity consumed by the satellite payload during operation.

[0046] The satellite power consumption simulation result may be understood as the total power consumption of the load during the operation of the target location obtained by simulation, for example, the amount of power consumed by the target location during the operation.

[0047] Using the above example, according to the load power consumption, load working period and load working order, the total power consumed by various loads during operation (i.e., load power consumption simulation data) is calculated, and the satellite energy cost is accumulated. The satellite energy cost can refer to the total power consumed by all loads on the satellite within a certain period of time, which reflects the overall demand level of the satellite for the power system.

[0048] In one or more embodiments provided in this specification, in order to accurately calculate the total power consumption of the satellite payload, the power consumption of the satellite payload within a preset number of orbits or a preset time range can be calculated, and then the total power consumption of the satellite payload within the preset number of orbits or a preset time range can be determined, so as to facilitate more accurate calculation of the satellite power consumption. The specific implementation method is as follows: Determining the load power consumption simulation data of each satellite load according to the multiple simulation load models and the multiple simulation subsystems in operation includes: Determine each simulation load model to be run when the multiple simulation subsystems are called, and calculate the corresponding load power consumption simulation data of each simulation load model within a preset time range or a preset track range.

[0049] The preset time range can be understood as a preset time range, which can be set according to the actual application scenario. For example, the preset time range can be 12 hours, 6 hours, etc.; The preset track range can be understood as a preset number of track circles or a track area in a preset track. For example, the preset track range can be a circle of track, or a specific area in a circle of track.

[0050] Continuing with the above example, this method can calculate the total power consumed by various payloads within one orbit or a period of time based on the payload power consumption, payload working period and payload working order, and add them up to obtain the satellite energy cost.

[0051] In one or more embodiments provided in this specification, after determining the satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data, the method further includes: Determining, from the plurality of satellite payloads, an associated satellite payload associated with a target satellite subsystem, wherein the target satellite subsystem is any one of the plurality of satellite subsystems; The satellite power consumption simulation result and the payload power consumption simulation data of the associated satellite payload are sent to a subsystem construction unit corresponding to the target satellite subsystem to construct the satellite subsystem.

[0052] The associated satellite payload may be understood as a satellite payload that can be called or used by a target satellite subsystem, and the operation of the target satellite subsystem requires the support of the capabilities of the associated satellite payload.

[0053] The subsystem construction unit can be understood as a unit used to design, build or maintain the target satellite subsystem. The unit can be a server, cloud server, data center or satellite design system; users can design, build or maintain the target satellite subsystem through the subsystem construction unit.

[0054] Specifically, for a target satellite subsystem, an associated satellite payload is determined for it from a plurality of satellite payloads, and then the satellite power consumption simulation result and the payload power consumption simulation data of the associated satellite payload are sent to a subsystem construction unit corresponding to the target satellite subsystem; The satellite power consumption simulation results and payload power consumption simulation data are displayed to the user by utilizing the subsystem construction unit, and the user can design, construct or maintain the target satellite subsystem based on the data displayed by the subsystem construction unit.

[0055] In the above embodiment, the satellite power consumption simulation results and the payload power consumption simulation data of the associated satellite payload are sent to the subsystem construction unit corresponding to the target satellite subsystem for satellite subsystem construction, thereby avoiding the problem of being unable to accurately estimate the power consumption of the satellite system during the process of building the satellite system; and achieving the use of accurate satellite power consumption simulation results to design and build a satellite system with better performance.

[0056] In one or more embodiments provided in this specification, determining the satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data includes: Determining total power consumption simulation data of the target satellite based on the payload power consumption simulation data of each satellite payload; Determine energy capacity data of the target satellite based on an energy storage simulation unit of the target satellite, and determine energy generation data of the target satellite based on an energy generation simulation unit of the target satellite; The satellite power consumption simulation result of the target satellite is determined based on the total power consumption simulation data, the energy capacity data, and the energy generation data.

[0057] Among them, the total power consumption simulation data can be understood as the total power consumed by all payloads on the target satellite within a certain period of time, the energy storage simulation unit can be understood as a battery, and the energy capacity data can be understood as the battery capacity; the energy generation simulation unit can be a solar panel; and the energy generation data can be the area of ​​the solar panel.

[0058] Specifically, the total power consumption simulation data of the target satellite is determined by adding the load power consumption simulation data of each satellite load; Furthermore, determining energy capacity data of the target satellite based on the energy storage simulation unit of the target satellite, and determining energy generation data of the target satellite based on the energy generation simulation unit of the target satellite; Then, based on the total power consumption simulation data, the energy capacity data, and the energy generation data, the satellite power consumption simulation result of the target satellite is determined, which may be specifically: Input the total power consumption simulation data, the energy capacity data and the energy generation data into the power consumption calculation unit corresponding to the target satellite for calculation and processing, and obtain the bus voltage and discharge depth change data of the target satellite; The bus voltage and the discharge depth change data are used as the satellite power consumption simulation results of the target satellite.

[0059] Continuing with the above example, based on the battery capacity, solar panel area and power consumption of each load, the bus voltage and discharge depth changes (i.e., satellite power consumption simulation results) are simulated and fed back to the MBSE subsystem architecture model to optimize the satellite system design.

[0060] In one or more embodiments provided in this specification, In the simulation processing method for satellites provided in this specification, during the model integration and driving process, the SysML model can be used to drive the constellation coverage characteristic analysis module to calculate the coverage capability, so as to accurately estimate the coverage capability of the satellite. The specific implementation method is as follows: The simulation processing method for a satellite also includes: Constructing a simulated satellite corresponding to the target satellite according to the payload attribute data and the subsystem attribute data, and operating the simulated satellite; Determining satellite coverage parameters generated by the simulated satellite during operation; In the case where it is determined that the satellite coverage parameter does not satisfy the satellite coverage detection condition, determining a satellite coverage subsystem associated with the satellite coverage parameter from the simulated satellite, adjusting the subsystem parameters of the satellite coverage subsystem to obtain an adjusted simulated satellite, and continuing to operate the adjusted simulated satellite; When it is determined that the satellite coverage parameters meet the satellite coverage detection condition, the satellite coverage parameters are provided to a satellite construction unit for satellite construction.

[0061] Among them, the satellite coverage parameters can be the coverage data of satellites at different latitudes, the coverage multiplicity of gateway stations, the coverage multiplicity of terminals, the number of visible satellites of ground targets at any time, the positional relationship between low-orbit constellations and ground targets, etc.

[0062] The satellite coverage subsystem can be understood as the system that realizes satellite communication and navigation functions in the target satellite.

[0063] Following the above example, the coverage performance analysis module of the constellation is driven by the SysML model to calculate the coverage capability. For simulation result verification, the coverage performance of the constellation configuration design can be verified in simulation software such as STK to ensure that the design meets the mission requirements. The specific coverage analysis method is: Coverage characteristics analysis: latitude band grid modeling and regional grid modeling are performed to analyze the satellite coverage at different latitudes and evaluate the coverage range and performance.

[0064] Communication coverage performance analysis: Communication coverage performance is analyzed from four aspects: gateway coverage multiplicity, terminal coverage multiplicity, global latitude band coverage multiplicity and global grid coverage multiplicity.

[0065] Navigation coverage performance analysis: Calculate the number of visible satellites of ground targets at any time and evaluate the navigation coverage multiplicity and positioning accuracy.

[0066] Aerial coverage analysis: Calculate the positional relationship between the low-orbit constellation and ground targets, select satellites that can cover ground targets, and determine the aerial coverage weight.

[0067] In one or more embodiments provided in this specification, a SysML model may be used to drive a system capacity analysis module to perform capacity characteristic calculations, thereby accurately estimating the capacity of the satellite. The specific implementation method is as follows: The method further comprises: Determining satellite communication data generated by the simulated satellite during operation; In the case where it is determined that the satellite communication data does not satisfy the satellite communication detection condition, determining a satellite communication subsystem associated with the satellite communication data from the simulated satellite, adjusting a subsystem parameter of the satellite communication subsystem to obtain an adjusted simulated satellite, and continuing to operate the adjusted simulated satellite; When it is determined that the satellite communication data meets the satellite communication detection condition, the satellite communication data is provided to a satellite construction unit for satellite construction.

[0068] Continuing with the above example, in the process of capacity analysis, we first model the constellation network capacity, establish communication pipelines to ensure business transmission, analyze different pipeline establishment strategies for multiple businesses, and improve network capacity.

[0069] Based on this modeling, the capacity calculation is performed as follows: Link capacity calculation: refers to calculating the capacity of the forward link, reverse link and intersatellite link.

[0070] Network graph construction: refers to building a network graph, including satellites, users, and gateways as nodes, and wireless links as edges.

[0071] System capacity solution: refers to solving the system capacity based on the network diagram using the maximum flow method or business flow method.

[0072] Influencing factor analysis: refers to analyzing the impact of factors such as gateway station deployment, link bandwidth, and routing strategy on system capacity.

[0073] Capacity analysis example: This example uses a specific constellation configuration as an example to perform simulation analysis and evaluate the achievable system throughput.

[0074] It should be noted that the joint simulation of coverage and system capacity can be carried out by combining SysML models and simulation platforms.

[0075] In addition, for constellation configuration maintenance analysis, a high-precision perturbation model can be used to analyze the drift law of constellation configuration and design configuration maintenance control strategies. For energy balance analysis, a satellite energy simulation model can be built to perform dynamic calculation of energy balance and full life cycle energy balance analysis.

[0076] The simulation processing method for satellites provided in one or more embodiments of the present specification can construct and configure multiple simulation payload models corresponding to multiple satellite payloads of the target satellite based on the payload attribute data corresponding to the target satellite, and construct multiple simulation subsystems corresponding to the multiple satellite subsystems of the target satellite according to the subsystem attribute data of the target satellite. By running multiple simulation payload models and multiple simulation subsystems, the actual operation of the satellite payload is simulated, so as to accurately determine the payload power consumption simulation data of each satellite payload, and determine the satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data; avoid the problem of being unable to accurately estimate the power consumption of the satellite system in the process of building the satellite system; and realize the use of accurate satellite power consumption simulation results to design and build a satellite system with better performance.

[0077] The following combination Figure 3Taking the application of the satellite simulation processing method provided in this specification in the integrated simulation verification scenario of the satellite system based on forward design as an example, the satellite simulation processing method is further described. Figure 3 A processing flow chart of a simulation processing method for a satellite provided in an embodiment of the present specification is shown, which specifically includes the following steps.

[0078] Step 302: pre-acquire the payload configuration data of the payload on the satellite and the subsystem configuration information of the subsystem in the real environment.

[0079] Among them, the payload includes: A load, B load, C load, D load, E load, F load, etc.; the subsystem includes: measurement and control subsystem, electric propulsion subsystem, attitude and orbit control subsystem, integrated electronic subsystem, power supply subsystem and other subsystems.

[0080] The load configuration data includes: load model, configuration parameters, etc.; the subsystem configuration information includes subsystem configuration parameters, call data for the load, etc.

[0081] Step 304: construct a power consumption model corresponding to each load on the simulation platform according to the load configuration data, and construct a corresponding satellite subsystem model according to the subsystem configuration information of each subsystem.

[0082] Step 306: Run the power consumption model and the satellite subsystem model, and according to the call operation of each subsystem model for the payload, run the power consumption model to perform specific operations, so as to determine the payload power consumption data within one orbit or a period of time.

[0083] The load power consumption data includes: load power consumption, load working period and load working sequence.

[0084] The load power consumption may be appropriate load power consumption data selected according to the type and function of the load, and the load power consumption may be used as an input parameter of the load power consumption model. The load power consumption may refer to the average power consumed by the load in a certain working mode, which reflects the demand level of the load on the power system.

[0085] The load working period can be determined according to the mission profile and working mode, and can refer to the length of time that the load operates in a certain working mode, which reflects the continuity of the load's demand for the power system.

[0086] The load working sequence can be determined according to the mission profile and working mode, and the working sequence of various loads in one orbit or within a period of time. The load working sequence can refer to the order in which the loads operate in a certain working mode, which reflects the conflicting requirements of the loads on the power system.

[0087] Step 308: Calculate the total power consumed by various loads within a circle of track or within a period of time based on the load power consumption data.

[0088] Specifically, the data such as the load power consumption, load working period and load working order simulated by the power consumption model are input into the constraint module for calculation to obtain the total load power consumption corresponding to the satellite.

[0089] The total load power consumption refers to the total power consumed by various loads within a circle of track or within a period of time calculated based on load power consumption, load working period and load working sequence.

[0090] Step 310: Add up the total power of each payload to obtain the satellite energy consumption within one orbit or a period of time.

[0091] Specifically, by accumulating the total power consumption of the payloads corresponding to the satellite, the satellite energy cost can be obtained.

[0092] Satellite energy expenditure: refers to the total amount of electricity consumed by all payloads on the satellite within a certain period of time, which reflects the overall demand level of the satellite for the power system.

[0093] Step 312: Based on the total satellite energy consumption, battery capacity, and solar panel area, calculate and simulate the changes in bus voltage and discharge depth.

[0094] Step 314: Feedback the simulation results to the MBSE platform. The designers adjust the parameters of each subsystem architecture model in the MBSE platform based on the simulation results to optimize the satellite system design.

[0095] The simulation results include changes in bus voltage and discharge depth.

[0096] In addition, it should be noted that this solution can also use SysML models to drive the constellation coverage characteristics and system capacity analysis modules to calculate the coverage capability and capacity characteristics of satellites; by verifying the coverage performance of the constellation configuration design in simulation software such as STK, it is ensured that the design meets the mission requirements. For example, communication coverage performance analysis, navigation coverage performance analysis, aviation coverage analysis, etc.

[0097] In addition, by verifying the system capacity of the constellation configuration design in simulation software such as STK, the system's achievable throughput is evaluated, which facilitates the establishment of communication pipelines to ensure business transmission, analyzes different pipeline establishment strategies for multiple businesses, and improves network capacity.

[0098] Corresponding to the above method embodiment, this specification also provides a simulation processing device embodiment for a satellite. Figure 4FIG. 1 shows a schematic diagram of a satellite simulation processing device provided by an embodiment of the present specification. Figure 4 As shown, the device comprises: The data determination module 402 is configured to determine payload attribute data and subsystem attribute data corresponding to the target satellite, wherein the payload attribute data is attribute data of multiple satellite payloads carried on the target satellite, and the subsystem attribute data is attribute data of multiple satellite subsystems constituting the target satellite, and each satellite subsystem operates based on the multiple satellite payloads; A model building module 404 is configured to build a plurality of simulation load models corresponding to the plurality of satellite loads according to the load attribute data, build a plurality of simulation subsystems corresponding to the plurality of satellite subsystems according to the subsystem attribute data, and run the plurality of simulation load models and the plurality of simulation subsystems; The result determination module 406 is configured to determine the payload power consumption simulation data of each satellite payload according to the multiple simulation payload models and the multiple simulation subsystems in operation, and determine the satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data.

[0099] Optionally, the simulation processing device for a satellite further includes a result sending module, which is configured to: Determining, from the plurality of satellite payloads, an associated satellite payload associated with a target satellite subsystem, wherein the target satellite subsystem is any one of the plurality of satellite subsystems; The satellite power consumption simulation result and the payload power consumption simulation data of the associated satellite payload are sent to a subsystem construction unit corresponding to the target satellite subsystem to construct the satellite subsystem.

[0100] Optionally, the result determination module 406 is further configured to: Determining total power consumption simulation data of the target satellite based on the payload power consumption simulation data of each satellite payload; Determine energy capacity data of the target satellite based on an energy storage simulation unit of the target satellite, and determine energy generation data of the target satellite based on an energy generation simulation unit of the target satellite; The satellite power consumption simulation result of the target satellite is determined based on the total power consumption simulation data, the energy capacity data, and the energy generation data.

[0101] Optionally, the result determination module 406 is further configured to: Input the total power consumption simulation data, the energy capacity data and the energy generation data into the power consumption calculation unit corresponding to the target satellite for calculation and processing, and obtain the bus voltage and discharge depth change data of the target satellite; The bus voltage and the discharge depth change data are used as the satellite power consumption simulation results of the target satellite.

[0102] Optionally, the payload attribute data includes payload configuration data, payload power consumption data, payload operation time data and payload operation sequence data corresponding to the satellite payload, and the subsystem attribute data includes subsystem configuration data corresponding to the satellite subsystem and satellite payload calling data; The model building module 404 is further configured to: Constructing the plurality of simulation payload models corresponding to the plurality of satellite payloads according to the payload configuration data, the payload power consumption data, the payload operation time data, and the payload operation sequence data; The model building module 404 is further configured to: A plurality of simulation subsystems corresponding to the plurality of satellite subsystems are constructed according to the subsystem configuration data and the satellite payload calling data, wherein the plurality of simulation subsystems are operated by calling the satellite payloads.

[0103] Optionally, the result determination module 406 is further configured to: Determine each simulation load model to be run when the multiple simulation subsystems are called, and calculate the corresponding load power consumption simulation data of each simulation load model within a preset time range or a preset track range.

[0104] Optionally, the data determination module 402 is further configured to: receiving the payload attribute data and the subsystem attribute data corresponding to the target satellite sent by a client, wherein the payload attribute data and the subsystem attribute data are sent by the client when a user performs a data upload operation on the client; After determining the satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data, the method further includes: The satellite power consumption simulation result is sent to the client.

[0105] Optionally, the simulation processing device for a satellite further includes a coverage analysis module, which is configured to: Constructing a simulated satellite corresponding to the target satellite according to the payload attribute data and the subsystem attribute data, and operating the simulated satellite; Determining satellite coverage parameters generated by the simulated satellite during operation; In the case where it is determined that the satellite coverage parameter does not satisfy the satellite coverage detection condition, determining a satellite coverage subsystem associated with the satellite coverage parameter from the simulated satellite, adjusting the subsystem parameters of the satellite coverage subsystem to obtain an adjusted simulated satellite, and continuing to operate the adjusted simulated satellite; When it is determined that the satellite coverage parameters meet the satellite coverage detection condition, the satellite coverage parameters are provided to a satellite construction unit for satellite construction.

[0106] Optionally, the simulation processing device for a satellite further includes a capacity analysis module configured to: Determining satellite communication data generated by the simulated satellite during operation; In the case where it is determined that the satellite communication data does not satisfy the satellite communication detection condition, determining a satellite communication subsystem associated with the satellite communication data from the simulated satellite, adjusting a subsystem parameter of the satellite communication subsystem to obtain an adjusted simulated satellite, and continuing to operate the adjusted simulated satellite; When it is determined that the satellite communication data meets the satellite communication detection condition, the satellite communication data is provided to a satellite construction unit for satellite construction.

[0107] The simulation processing device for satellites provided in one or more embodiments of the present specification can construct and configure multiple simulation payload models corresponding to multiple satellite payloads of the target satellite based on the payload attribute data corresponding to the target satellite, and construct multiple simulation subsystems corresponding to the multiple satellite subsystems of the target satellite according to the subsystem attribute data of the target satellite. By running multiple simulation payload models and multiple simulation subsystems, the actual operation of the satellite payload is simulated, so as to accurately determine the payload power consumption simulation data of each satellite payload, and determine the satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data; thereby avoiding the problem of being unable to accurately estimate the power consumption of the satellite system during the process of building the satellite system; and realizing the use of accurate satellite power consumption simulation results to design and build a satellite system with better performance.

[0108] The above is a schematic scheme of a simulation processing device for satellites in this embodiment. It should be noted that the technical scheme of the simulation processing device for satellites and the technical scheme of the simulation processing method for satellites are of the same concept, and the details not described in detail in the technical scheme of the simulation processing device for satellites can be found in the description of the technical scheme of the simulation processing method for satellites.

[0109] Figure 5The structure block diagram of a computing device 500 provided according to an embodiment of the present specification is shown. The components of the computing device 500 include but are not limited to a memory 510 and a processor 520. The processor 520 is connected to the memory 510 via a bus 530, and the database 550 is used to store data.

[0110] The computing device 500 also includes an access device 540 that enables the computing device 500 to communicate via one or more networks 560. Examples of these networks include a public switched telephone network (PSTN), a local area network (LAN), a wide area network (WAN), a personal area network (PAN), or a combination of communication networks such as the Internet. The access device 540 may include one or more of any type of network interface (e.g., a network interface card (NIC)) that is wired or wireless, such as an IEEE 802.11 wireless local area network (WLAN) wireless interface, a world-wide interoperability for microwave access (Wi-MAX) interface, an Ethernet interface, a universal serial bus (USB) interface, a cellular network interface, a Bluetooth interface, and a near field communication (NFC).

[0111] In one embodiment of the present specification, the above components of the computing device 500 and Figure 5 Other components not shown in the figure may also be connected to each other, for example, via a bus. It should be understood that Figure 5 The computing device structure block diagram shown is only for the purpose of illustration, and is not intended to limit the scope of this specification. Those skilled in the art can add or replace other components as needed.

[0112] The computing device 500 may be any type of stationary or mobile computing device, including a mobile computer or mobile computing device (e.g., a tablet computer, a personal digital assistant, a laptop computer, a notebook computer, a netbook, etc.), a mobile phone (e.g., a smart phone), a wearable computing device (e.g., a smart watch, smart glasses, etc.), or other types of mobile devices, or a stationary computing device such as a desktop computer or a personal computer (PC). The computing device 500 may also be a mobile or stationary server.

[0113] The processor 520 is used to execute the following computer executable instructions, which, when executed by the processor, implement the steps of the above-mentioned simulation processing method for the satellite.

[0114] Each embodiment in this specification is described in a progressive manner, and the same or similar parts between the embodiments can be referred to each other, and each embodiment focuses on the differences from other embodiments. In particular, for the computing device embodiment, since it is basically similar to the simulation processing method embodiment for satellites, the description is relatively simple, and the relevant parts can be referred to the partial description of the simulation processing method embodiment for satellites.

[0115] An embodiment of the present specification also provides a computer-readable storage medium storing a computer program / instruction, which implements the steps of the above-mentioned simulation processing method for a satellite when executed by a processor.

[0116] Each embodiment in this specification is described in a progressive manner, and the same or similar parts between the embodiments can be referred to each other, and each embodiment focuses on the differences from other embodiments. In particular, for the computer-readable storage medium embodiment, since it is basically similar to the simulation processing method embodiment for satellites, the description is relatively simple, and the relevant parts can be referred to the partial description of the simulation processing method embodiment for satellites.

[0117] An embodiment of the present specification also provides a computer program product, including a computer program / instruction, which implements the steps of the above-mentioned simulation processing method for a satellite when executed by a processor.

[0118] The above is a schematic scheme of a computer program product of this embodiment. It should be noted that the technical scheme of the computer program product and the technical scheme of the above-mentioned satellite simulation processing method belong to the same concept, and the details not described in detail in the technical scheme of the computer program product can be referred to the description of the technical scheme of the above-mentioned satellite simulation processing method.

[0119] The above is a description of a specific embodiment of the specification. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recorded in the claims can be performed in an order different from that in the embodiments and still achieve the desired results. In addition, the processes depicted in the drawings do not necessarily require the specific order or continuous order shown to achieve the desired results. In some embodiments, multitasking and parallel processing are also possible or may be advantageous.

[0120] The computer instructions include computer program codes, which may be in source code form, object code form, executable files or some intermediate forms, etc. The computer-readable medium may include: any entity or device capable of carrying the computer program code, recording medium, USB flash drive, mobile hard disk, magnetic disk, optical disk, computer memory, read-only memory (ROM), random access memory (RAM), electric carrier signal, telecommunication signal and software distribution medium, etc. It should be noted that the content contained in the computer-readable medium may be appropriately increased or decreased according to the requirements of patent practice. For example, in some regions, according to patent practice, computer-readable media do not include electric carrier signals and telecommunication signals.

[0121] It should be noted that, for the above-mentioned method embodiments, for the sake of simplicity of description, they are all expressed as a series of action combinations, but those skilled in the art should be aware that the embodiments of this specification are not limited by the order of the actions described, because according to the embodiments of this specification, some steps can be performed in other orders or simultaneously. Secondly, those skilled in the art should also be aware that the embodiments described in the specification are all preferred embodiments, and the actions and modules involved are not necessarily required by the embodiments of this specification.

[0122] In the above embodiments, the description of each embodiment has its own emphasis. For parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0123] The preferred embodiments of this specification disclosed above are only used to help explain this specification. The optional embodiments do not describe all the details in detail, nor do they limit the invention to only the specific implementation methods described. Obviously, many modifications and changes can be made according to the content of the embodiments of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the embodiments of this specification, so that technicians in the relevant technical field can well understand and use this specification. This specification is only limited by the claims and their full scope and equivalents.

Claims

1. A simulation processing method for a satellite, characterized in that: include: Determine payload attribute data and subsystem attribute data corresponding to the target satellite, wherein the payload attribute data is attribute data of multiple satellite payloads carried on the target satellite, and the subsystem attribute data is attribute data of multiple satellite subsystems constituting the target satellite, and each satellite subsystem operates based on the multiple satellite payloads; Constructing a plurality of simulation load models corresponding to the plurality of satellite loads according to the load attribute data, constructing a plurality of simulation subsystems corresponding to the plurality of satellite subsystems according to the subsystem attribute data, and running the plurality of simulation load models and the plurality of simulation subsystems; According to the multiple simulation payload models and the multiple simulation subsystems in operation, the payload power consumption simulation data of each satellite payload is determined, and based on the payload power consumption simulation data, the satellite power consumption simulation result of the target satellite is determined.

2. The satellite simulation processing method according to claim 1, characterized in that: After determining the satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data, the method further includes: Determining, from the plurality of satellite payloads, an associated satellite payload associated with a target satellite subsystem, wherein the target satellite subsystem is any one of the plurality of satellite subsystems; The satellite power consumption simulation result and the payload power consumption simulation data of the associated satellite payload are sent to a subsystem construction unit corresponding to the target satellite subsystem to construct the satellite subsystem.

3. The satellite simulation processing method according to claim 1 or 2, characterized in that: The step of determining a satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data includes: Determining total power consumption simulation data of the target satellite based on the payload power consumption simulation data of each satellite payload; Determine energy capacity data of the target satellite based on an energy storage simulation unit of the target satellite, and determine energy generation data of the target satellite based on an energy generation simulation unit of the target satellite; The satellite power consumption simulation result of the target satellite is determined based on the total power consumption simulation data, the energy capacity data, and the energy generation data.

4. The satellite simulation processing method according to claim 3, characterized in that: The determining the satellite power consumption simulation result of the target satellite based on the total power consumption simulation data, the energy capacity data, and the energy generation data comprises: Input the total power consumption simulation data, the energy capacity data and the energy generation data into the power consumption calculation unit corresponding to the target satellite for calculation and processing, and obtain the bus voltage and discharge depth change data of the target satellite; The bus voltage and the discharge depth change data are used as the satellite power consumption simulation results of the target satellite.

5. The satellite simulation processing method according to claim 1, characterized in that: The payload attribute data includes payload configuration data, payload power consumption data, payload operation time data and payload operation sequence data corresponding to the satellite payload, and the subsystem attribute data includes subsystem configuration data corresponding to the satellite subsystem and satellite payload call data; The step of constructing a plurality of simulation payload models corresponding to the plurality of satellite payloads according to the payload attribute data comprises: Constructing the plurality of simulation payload models corresponding to the plurality of satellite payloads according to the payload configuration data, the payload power consumption data, the payload operation time data, and the payload operation sequence data; The step of constructing a plurality of simulation subsystems corresponding to the plurality of satellite subsystems according to the subsystem attribute data comprises: A plurality of simulation subsystems corresponding to the plurality of satellite subsystems are constructed according to the subsystem configuration data and the satellite payload calling data, wherein the plurality of simulation subsystems are operated by calling the satellite payloads.

6. The satellite simulation processing method according to claim 1, characterized in that: Determining the load power consumption simulation data of each satellite load according to the multiple simulation load models and the multiple simulation subsystems in operation includes: Determine each simulation load model to be run when the multiple simulation subsystems are called, and calculate the corresponding load power consumption simulation data of each simulation load model within a preset time range or a preset track range.

7. The satellite simulation processing method according to claim 1, characterized in that: The determining of the payload attribute data and subsystem attribute data corresponding to the target satellite includes: receiving the payload attribute data and the subsystem attribute data corresponding to the target satellite sent by a client, wherein the payload attribute data and the subsystem attribute data are sent by the client when a user performs a data upload operation on the client; After determining the satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data, the method further includes: The satellite power consumption simulation result is sent to the client.

8. The satellite simulation processing method according to claim 1, characterized in that: Also includes: Constructing a simulated satellite corresponding to the target satellite according to the payload attribute data and the subsystem attribute data, and operating the simulated satellite; Determining satellite coverage parameters generated by the simulated satellite during operation; In the case where it is determined that the satellite coverage parameter does not satisfy the satellite coverage detection condition, determining a satellite coverage subsystem associated with the satellite coverage parameter from the simulated satellite, adjusting the subsystem parameters of the satellite coverage subsystem to obtain an adjusted simulated satellite, and continuing to operate the adjusted simulated satellite; When it is determined that the satellite coverage parameters meet the satellite coverage detection condition, the satellite coverage parameters are provided to a satellite construction unit for satellite construction.

9. The satellite simulation processing method according to claim 8, characterized in that: After constructing a simulated satellite corresponding to the target satellite according to the payload attribute data and the subsystem attribute data and running the simulated satellite, the method further includes: Determining satellite communication data generated by the simulated satellite during operation; In the case where it is determined that the satellite communication data does not satisfy the satellite communication detection condition, determining a satellite communication subsystem associated with the satellite communication data from the simulated satellite, adjusting a subsystem parameter of the satellite communication subsystem to obtain an adjusted simulated satellite, and continuing to operate the adjusted simulated satellite; When it is determined that the satellite communication data meets the satellite communication detection condition, the satellite communication data is provided to a satellite construction unit for satellite construction.

10. A simulation processing device for a satellite, characterized in that: include: A data determination module is configured to determine payload attribute data and subsystem attribute data corresponding to the target satellite, wherein the payload attribute data is attribute data of multiple satellite payloads carried on the target satellite, and the subsystem attribute data is attribute data of multiple satellite subsystems constituting the target satellite, and each satellite subsystem operates based on the multiple satellite payloads; A model construction module is configured to construct a plurality of simulation load models corresponding to the plurality of satellite loads according to the load attribute data, construct a plurality of simulation subsystems corresponding to the plurality of satellite subsystems according to the subsystem attribute data, and run the plurality of simulation load models and the plurality of simulation subsystems; The result determination module is configured to determine the payload power consumption simulation data of each satellite payload according to the multiple simulation payload models and the multiple simulation subsystems in operation, and determine the satellite power consumption simulation result of the target satellite based on the payload power consumption simulation data.

11. A computing device, characterized in that: include: Memory and processor; The memory is used to store computer programs / instructions, and the processor is used to execute the computer programs / instructions. It is characterized in that when the computer program / instructions are executed by the processor, the steps of the method described in any one of claims 1 to 9 are implemented.

12. A computer-readable storage medium, characterized in that: It stores a computer program / instruction, characterized in that when the computer program / instruction is executed by a processor, the steps of the method described in any one of claims 1 to 9 are implemented.

13. A computer program product, characterized in that The method comprises a computer program / instruction, wherein the computer program / instruction implements the steps of the method according to any one of claims 1 to 9 when the computer program / instruction is executed by a processor.

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