Modeling simulation method for satellite energy system
By decomposing the functional interface of satellite energy system and standardizing the index, and building a standard interface unit model for simulation, the immature problem of satellite energy system simulation in the existing technology is solved, and rapid performance evaluation and efficient energy management are achieved.
Patent Information
- Application Number
- CN202411619487.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-11-13
- Publication Date
- 2025-04-01
AI Technical Summary
The prior art is difficult to effectively simulate satellite energy systems under different simulation particle size requirements and topology through standard interface models, resulting in the in-orbit performance evaluation method of satellite in-orbit energy flows being immature.
By decomposing the functional interface of the energy system and standardizing the definition of each equipment indicator, under the set space environment and satellite in orbit conditions, a standard interface unit model is used to simulate important parameters such as electric heating of the energy system, and a standard simulation model of the electrical interface and thermal interface is constructed.
It realizes rapid performance evaluation and management of satellite energy systems, reduces the risks of design and verification work, provides real-time operating status evaluation, and improves energy management efficiency.
Smart Images
Figure CN119740351A_ABST
Abstract
Description
Technical Field
[0001] The present application as a whole relates to a modeling and simulation method for a satellite energy system, which is suitable for rapid performance evaluation and management of energy flows when a satellite is in orbit. Background Art
[0002] With the rapid development of the aerospace industry, the development of the satellite field presents the characteristics of mass production, short cycle, low cost and diversified user needs. The energy system, as the safety bottom line to ensure the stable operation of the satellite in orbit, is one of the key subsystems of the satellite. The performance evaluation of the mechanical, electrical and thermal interface characteristics of the energy system through simulation at different stages of the design can greatly shorten the time and cost of satellite energy system development, which is of great significance to standardizing the energy system design process and reducing the risks in energy system design and verification work. At the same time, it can also accurately simulate the energy usage status on the satellite and provide real-time operation status evaluation for the energy system in orbit.
[0003] However, with the advancement of digital technology, modeling and simulation technologies have been applied in many aspects of my country's aerospace field. Among them, a lot of research has been done on the digital modeling and simulation of satellite energy systems. However, the method of simulating energy systems with different simulation granularity requirements and different topologies through standard interface models to achieve rapid performance evaluation of satellite on-orbit energy flows is not mature enough. Summary of the invention
[0004] By decomposing the functional interface of the energy system and standardizing the indicators of each device, under the set space environment and satellite on-orbit conditions, the important parameters of the energy system such as electricity and heat are simulated through the standard interface unit model, providing real-time operation status evaluation for satellite design and energy system on-orbit.
[0005] The present application provides a satellite energy system modeling and simulation method, comprising the following steps:
[0006] S1: Based on the on-orbit activities of the energy system, the functional indicators of the entire energy system are converted into specific parameter indicators of multiple single machines within the system. Different parameter indicators correspond to different energy subsystems within the energy system, where the energy subsystem is a single machine device or a module of a single machine device in the energy system;
[0007] S2: A standardized architectural description of the parameter indicators of each energy subsystem in the energy system. The architectural description includes the granularity of modeling and simulation combination of each component and component parameter in each energy subsystem;
[0008] S3: Construct the electrical interface standard simulation model and thermal interface standard simulation model of the energy system. The electrical interface standard simulation model is used to simulate the energy flow operation state of the energy system under different orbit conditions and satellite working conditions, and the thermal interface standard simulation model is used to simulate the temperature change and temperature control process of each energy subsystem in the energy system.
[0009] S4: Setting simulation parameters, inputting the simulation parameters together with the architecture description obtained in step S2 into the electrical interface standard simulation model and the thermal interface standard simulation model obtained in step 3 to perform energy system performance simulation.
[0010] In at least one embodiment, the energy subsystem is a power generation subsystem, an energy storage subsystem, a power regulation and control subsystem, and a power conversion subsystem in the energy system.
[0011] In at least one embodiment, the energy subsystem is a related module in the power regulation control subsystem of the energy system, including an S3R module, an S4R module, a discharge regulation module, a BEA module, and an MEA module. The energy storage subsystem includes related modules of the battery pack in the energy system, including a battery pack and a battery management unit.
[0012] In at least one embodiment, in step S1, the parameter index of each energy subsystem also includes specification information of the energy subsystem.
[0013] Among them, the parameter indicators of the power generation subsystem include the model specifications, volt-ampere characteristics, conversion efficiency, fill factor, temperature coefficient, attenuation factor, and weight of the solar cell single chip;
[0014] The parameter indicators of the energy storage subsystem include the model, weight, size, thermal capacity, average operating voltage, and rated capacity of the battery cells and battery management unit;
[0015] The parameter indicators of the power regulation control subsystem include the weight and size of each module of the power controller, output electrical parameters and thermal characteristic parameters.
[0016] In at least one embodiment, in step S2, the combined granularity of modeling and simulation includes power supply function simulation, charging shunt function simulation, discharge function simulation and combined power supply function simulation of the energy system.
[0017] In at least one embodiment, in step S3, the simulation of the electrical interface standard simulation model includes: the energy system supplies power to the entire satellite, battery charging and discharging, shunt transmission, and joint power supply process; and the energy and information flow exchanged between each single machine under the simulation granularity requirements.
[0018] In at least one embodiment, in step S3, the temperature change of the energy subsystem is simulated as the heat flow outside the solar array space, including: direct sunlight, reflected sunlight from the earth and infrared radiation from the earth, thermal radiation and conduction exchange between the solar array and the celestial body; the heat generated by the battery pack and the power controller during charging, discharging and shunting, and the transfer and temperature change process.
[0019] In at least one embodiment, in step S3, the simulation of the temperature control of the energy subsystem includes: a process in which the heating belt on the battery performs temperature adjustment according to a closed-loop temperature threshold.
[0020] In at least one embodiment, in step S2, the architecture description includes: solar cells are combined in series and parallel to form a solar cell array; lithium-ion battery cells are combined in series and parallel to form a lithium-ion battery pack; the power controller selects some or all modules for simulation according to the different topology of the satellite power supply and distribution system.
[0021] In at least one embodiment, in step S4,
[0022] The simulation parameters include the satellite’s on-orbit space environment parameters, on-orbit operating conditions, and operating modes.
[0023] Satellite on-orbit space environment parameters include satellite orbit parameters and lighting conditions;
[0024] The satellite's on-orbit operating conditions include the power consumption of the satellite payload.
[0025] The method provided in this application can achieve the following beneficial effects:
[0026] 1. Discover innovations in the early stages of design: Energy system equipment is a highly reliable device, and its product design or equipment manufacturing innovation is difficult. Product manufacturing is not designed in the early stages of system design. Discovering system innovations through modeling and simulation can reduce innovation costs.
[0027] 2. Optimize energy configuration: By establishing standard simulation models of the energy system output electrical and thermal interfaces that the system is more concerned about, the hardware configuration of the energy system design phase is optimized in multiple dimensions such as power supply mode, power carrying capacity and thermal response, and the optimal solution for the energy system is found for subsequent models in terms of spacecraft quality control, energy balance and system on-orbit safety.
[0028] 3. The standardized simulation model is highly versatile and reusable. It can adapt to the different topological structures and bus forms of multiple types of satellite energy systems, better adapt to the complex and changeable energy system needs, and improve energy management efficiency.
[0029] 4. Rapid on-orbit status assessment: By establishing energy system simulation modeling, it is possible to accurately simulate the on-board energy usage status, provide real-time operation status assessment for the energy system on-orbit, and provide a simulation basis for the satellite's on-orbit energy security. BRIEF DESCRIPTION OF THE DRAWINGS
[0030] The following will further explain the above characteristics, technical features, advantages and implementation methods of the present application in a clear and understandable manner through the description of the preferred embodiments and in combination with the accompanying drawings. The following drawings are only intended to illustrate and explain the present application, and do not limit the scope of the present application. Among them:
[0031] Figure 1 A flow chart of a satellite energy system modeling and simulation method according to an embodiment of the present application is shown. DETAILED DESCRIPTION
[0032] In order to have a clearer understanding of the technical features, purposes and effects of the present application, the specific implementation methods of the present application are now described with reference to the accompanying drawings.
[0033] like Figure 1 As shown, the present application discloses a satellite energy system modeling and simulation method, the steps are as follows:
[0034] S1: Decompose the on-orbit functions of the energy system and convert the functional indicators of the energy system into multiple parameter indicators.
[0035] Based on the main activities of the energy system on orbit, the functional indicators of the entire energy system are converted into multiple parameter indicators, each of which corresponds to an energy subsystem within the energy system. The energy subsystem is a single device of the energy system or a module of a single device. For example, the single device can be a power generation device (solar cell array), energy storage device (battery, etc.), power regulation and control device (power controller), power conversion device (DC / DC module, etc.) in the energy system.
[0036] S2: A standardized architectural description of the parameter indicators of each energy subsystem in the energy system.
[0037] The architecture description includes the modeling and simulation combination granularity of defining each component and component parameter in each energy subsystem. For example, the modeling and simulation combination granularity of defining each component and component parameter in the power generation equipment, each component and component parameter in the energy storage equipment, and each module and module parameter in the power controller.
[0038] The combined granularity of modeling and simulation includes the power supply function simulation, charging and shunt function simulation, discharge function simulation and combined power supply function simulation of the energy system.
[0039] The architecture description combines one or more devices for modeling and simulation according to the granularity requirements of the simulation.
[0040] S3: Construct the electrical interface standard simulation model and thermal interface standard simulation model of the energy system;
[0041] The electrical interface standard simulation model is used to simulate the energy flow operation status of the energy system under different orbital conditions and satellite working conditions, including: the energy system supplies power to the entire satellite, battery charging and discharging, shunt transmission, and joint power supply process; the energy and information flow exchanged between each single machine under the simulation granularity requirements.
[0042] The thermal interface standard simulation model is used to simulate the temperature changes and temperature control processes of each energy subsystem within the energy system.
[0043] The temperature change of the energy subsystem is simulated as the heat flow outside the solar array space, including: direct sunlight, reflected sunlight from the earth and infrared radiation from the earth, thermal radiation and conduction exchange between the solar array and the stars; the heat generated by the battery pack and the power controller during charging, discharging and shunting, and the transfer and temperature change process.
[0044] The simulation of temperature control of the energy subsystem includes the process of adjusting the temperature of the heating belt on the battery according to the closed-loop temperature threshold.
[0045] S4: Set simulation parameters such as satellite on-orbit space environment parameters, on-orbit operating conditions and working modes, input the simulation parameters together with the architecture description obtained in step S2 into the standard model obtained in step 3, simulate the energy system performance, and display it in the required format.
[0046] In step S1, the energy subsystem may be power generation equipment, energy storage equipment, and power controller related modules in the satellite energy system. The power generation equipment includes but is not limited to body-mounted solar arrays and deployable solar arrays; the energy storage equipment includes but is not limited to lithium-ion battery packs and battery pack management units; the power controller related modules include but are not limited to S3R modules, S4R modules, discharge regulation modules (BDR), BEA modules, and MEA modules.
[0047] In step S1, the parameter index of each energy subsystem also includes the specification information of the energy subsystem.
[0048] For example, the parameter indicators of power generation equipment include the model specifications, volt-ampere characteristics, conversion efficiency, fill factor, temperature coefficient, attenuation factor, weight and other parameters of the solar cell.
[0049] The parameter indicators of energy storage equipment include the model, weight and size, thermal capacity, average operating voltage, rated capacity and other characteristic parameters of battery cells and battery management units.
[0050] The parameter indicators of the power control equipment include the weight and size of each module of the power controller, output electrical parameters, and thermal characteristic parameters.
[0051] In step S2, the architecture description includes: solar cells are connected in series and in parallel to form a solar cell array; lithium-ion battery cells are connected in series and in parallel to form a lithium-ion battery pack; the power controller selects part or all of the modules for simulation according to the different topologies of the satellite power supply and distribution system.
[0052] In step S4, the on-orbit space environment parameters and the on-orbit working conditions of the satellite are set, including but not limited to: orbital parameters of the satellite, lighting conditions, power consumption of the satellite payload and other related parameters.
[0053] It should be understood that although this specification is described according to various embodiments, not every embodiment contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.
[0054] The above description is only an illustrative embodiment of the present application and is not intended to limit the scope of the present application. Any equivalent changes, modifications and combinations made by any technician in the field without departing from the concept and principle of the present application shall fall within the scope of protection of the present application.
Claims
1. A satellite energy system modeling and simulation method, comprising the following steps: S1: Based on the on-orbit activities of the energy system, the functional indicators of the entire energy system are converted into specific parameter indicators of multiple single machines within the system. Different parameter indicators correspond to different energy subsystems within the energy system, where the energy subsystem is a single machine device or a module of a single machine device in the energy system; S2: A standardized architectural description of the parameter indicators of each energy subsystem in the energy system. The architectural description includes the granularity of modeling and simulation combination of each component and component parameter in each energy subsystem; S3: Construct the electrical interface standard simulation model and thermal interface standard simulation model of the energy system. The electrical interface standard simulation model is used to simulate the energy flow operation state of the energy system under different orbit conditions and satellite working conditions, and the thermal interface standard simulation model is used to simulate the temperature change and temperature control process of each energy subsystem in the energy system. S4: Setting simulation parameters, inputting the simulation parameters together with the architecture description obtained in step S2 into the electrical interface standard simulation model and the thermal interface standard simulation model obtained in step 3 to perform energy system performance simulation.
2. The method according to claim 1, wherein: The energy subsystem includes the power generation subsystem, energy storage subsystem, power regulation and control subsystem, and power conversion subsystem in the energy system.
3. The method according to claim 1, wherein: The power regulation and control subsystem includes the relevant modules of the power controller in the energy system, including the S3R module, S4R module, discharge regulation module, BEA module, and MEA module; the energy storage subsystem includes the relevant modules of the battery pack in the energy system, including the battery group and battery management unit.
4. The method according to claim 1, wherein: In step S1, the parameter indicators of each energy subsystem also include the specification information of the energy subsystem. Among them, the parameter indicators of the power generation subsystem include the model specifications, volt-ampere characteristics, conversion efficiency, fill factor, temperature coefficient, attenuation factor, and weight of the solar cell module; The parameter indicators of the energy storage subsystem include the model, weight, size, thermal capacity, average operating voltage, and rated capacity of the battery cells and battery management unit; The parameter indicators of the power regulation control subsystem include the weight and size of each module of the power controller, output electrical parameters and thermal characteristic parameters.
5. The method according to claim 1, wherein: In step S2, the combined granularity of modeling and simulation includes power supply function simulation, charging shunt function simulation, discharge function simulation and combined power supply function simulation of the energy system.
6. The method according to claim 1, wherein: In step S3, the simulation of the electrical interface standard simulation model includes: the energy system supplies power to the entire satellite, battery charging and discharging, shunt transmission, and joint power supply process; and the energy and information flow exchanged between each single machine under the simulation granularity requirements.
7. The method according to claim 1, wherein: In step S3, the temperature change of the energy subsystem is simulated as the heat flow outside the solar array space, including: direct sunlight, reflected sunlight from the earth and infrared radiation from the earth, thermal radiation and conduction exchange between the solar array and the stars; the heat generated by the battery pack and the power controller during charging, discharging and shunting, and the transfer and temperature change process.
8. The method according to claim 1, wherein: In step S3, the simulation of the temperature control of the energy subsystem includes: a process in which the heating belt on the battery performs temperature adjustment according to a closed-loop temperature threshold.
9. The method according to claim 1, wherein: In step S2, the architecture description includes: solar cells are connected in series and in parallel to form a solar cell array; lithium-ion battery cells are connected in series and in parallel to form a lithium-ion battery pack; the power controller selects part or all of the modules for simulation according to the different topologies of the satellite power supply and distribution system.
10. The method according to claim 1, wherein: In step S4, The simulation parameters include the satellite’s on-orbit space environment parameters, on-orbit operating conditions, and operating modes. The satellite’s on-orbit space environment parameters include the satellite’s orbital parameters and lighting conditions; the satellite’s on-orbit operating conditions include the satellite’s payload power consumption.