A digital twin satellite power supply simulation control method

Abstract

The invention discloses a digital twin satellite power supply simulation control method, which relates to the technical field of satellite power supply simulation. According to the area and number of solar panels corresponding to the satellite for which power supply simulation is required, a corresponding I-V curve is drawn under set lighting conditions, a corresponding number of sampling points are sampled on the I-V curve according to a preset resolution, and relevant data corresponding to each sampling point on the I-V curve is obtained, so as to draw a standard I-V curve. After the digital twin satellite is running, it receives a frame of configuration data, configures its own power supply simulator to the same state as that of the actual satellite, activates the solar panel power supply simulator, receives data from the digital twin satellite and the space environment simulator, and performs calculation according to the attitude position data and power supply and power consumption of the satellite, outputs the voltage value and current value obtained by the calculation and returns them synchronously to the digital twin satellite, and the digital twin satellite judges the current working condition of the solar panel.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite power supply simulation, and in particular to a digital twin satellite power supply simulation control method. Background Art

[0002] In recent years, digital twin technology has attracted widespread attention and research from the global industry and academia. Digital twin is an effective means to digitize, network and intelligentize traditional industries.

[0003] Digital twins establish dynamic virtual models of physical entities in a digital way, with multiple dimensions, multiple time and space scales, multiple disciplines, and multiple physical quantities, and reproduce the properties, behaviors, rules, etc. of physical entities in real environments with the help of real-time data. As an important technology for depicting, simulating, optimizing, and enhancing the physical world in the information world, digital twins are an effective way to achieve interaction and integration between the physical world and the information world, an effective means of deeply integrating New IT technologies, and an effective way to promote the transformation of global industrial and social development towards digitalization, networking, intelligence, and service.

[0004] Digital twin satellites are satellites that closely integrate digital twin technology with key links, key scenarios, and key objects in satellite engineering, and simulate satellite engineering in physical space in real time based on models and data. In satellite engineering, power supply and power distribution systems are responsible for powering various satellite subsystems, playing a basic and key role. The differences in payload equipment on satellite platforms will affect the operating environment of the power system, so the power system participates in testing and evaluation at all stages of satellite design and manufacturing. However, the operation of solar panels depends on the space environment and cannot be easily reproduced on the ground. Therefore, digital satellites and real satellites in the design and testing stage require a power supply simulator to simulate the situation of solar panels being exposed to sunlight in space, and output corresponding voltage and current values ​​according to the configuration, position, attitude, operating time, and fault conditions of the simulated satellite. These values ​​can be called by other digital twin subsystems, and can also be output through physical power supplies for other electrical equipment on real satellites.

[0005] At present, some software has been developed at home and abroad to model solar arrays, batteries, power control and distribution devices, and the basic components of satellite power systems. For example, Power-Systema developed by Astrium SAS in France, these software have simulated the various components of satellite power and the on-orbit operation status in a relatively detailed manner, and can obtain relatively detailed simulation results, but these are all software simulations, and cannot be used as a real power supply to power test equipment, nor can they interact with other modules of the digital twin satellite.

[0006] There are also many hardware manufacturers that produce dedicated solar array simulators, but they are mainly aimed at ground photovoltaic application scenarios and cannot be easily configured to meet the needs of aerospace applications. A few professionally designed satellite solar panel power supply simulators are mainly designed and tested for large satellites. They are very expensive and have a complex architecture. They cannot meet the needs of the growing field of micro-satellites. More importantly, the real-time performance does not meet the needs and cannot be used as a module of a digital twin satellite to communicate with other modules of a digital twin satellite and be used as a digital satellite power supply device. Therefore, the present invention aims at the defect that the existing satellite solar panel power supply simulator cannot be used for digital twin satellites and has a complex and expensive structure. A simplified design scheme based on an embedded microprocessor and a network controller is proposed to achieve the purpose of reducing costs and improving performance. Summary of the invention

[0007] In order to solve the above problems, the object of the present invention is to provide a digital twin satellite power supply simulation control method.

[0008] The purpose of the present invention can be achieved by the following technical solution: A digital twin satellite power supply simulation control method comprises the following steps:

[0009] Step S1: according to the area and number of solar panels corresponding to the satellite for which power supply simulation is required, draw the corresponding IV curve under the set illumination conditions;

[0010] Step S2: sampling a corresponding number of sampling points on the IV curve according to a preset resolution, and obtaining relevant data corresponding to each sampling point on the IV curve and storing them in a memory connected to the embedded controller, thereby drawing a standard IV curve;

[0011] Step S3: After the digital twin satellite is in operation, it receives a frame of configuration data and configures its own power simulator to the same state as the actual satellite;

[0012] Step S4: activating the solar panel power supply simulator, receiving data from the digital twin satellite and the space environment simulator, and performing calculations based on the satellite's attitude position data and power supply and consumption;

[0013] Step S5: After the solution is completed, the voltage value and current value obtained by the solution are output, and the output voltage and output current are synchronously returned to the digital twin satellite;

[0014] Step S6: The digital twin satellite determines the current working condition of the solar panels, and then determines whether the actual satellite meets the expected requirements under the current energy conditions.

[0015] Further, according to the area and number of solar panels corresponding to the satellite for which power supply simulation is required, the process of drawing the corresponding IV curve under the set illumination conditions includes:

[0016] Select a satellite that needs to be simulated for power supply. The satellite is an actual satellite that needs to be operated in orbit in space. Obtain the number of solar panels corresponding to the actual satellite, recorded as N. Obtain the area corresponding to each solar panel. Number several solar panels and record them as i, i = 1, 2, 3, ..., n, where n is a natural number greater than 0. The area of ​​the solar panel numbered i is recorded as S[i]. Add up the areas of n solar panels to obtain the total power generation area, which is recorded as S. 总 ;

[0017] have

[0018] The total power generation area S 总 The unit is m^2. The following illumination conditions are set: 1.353kW / m^2, AM0, 25℃. Under this illumination condition, an IV curve that conforms to the actual operation of the current satellite is drawn.

[0019] Furthermore, the process of sampling a corresponding number of sampling points on the IV curve according to a preset resolution, obtaining relevant data corresponding to each sampling point on the IV curve, and then drawing a standard IV curve includes:

[0020] The IV curve is divided into several sections according to the preset resolution, and the sections are numbered and recorded as j, j = 1, 2, 3, ..., m, where m is a natural number greater than 0. The middle point of each section is used as the sampling point for sampling, and the starting point and end point of the section numbered j are recorded as P1 and P2, respectively. j and P2 j ;

[0021] Get P1 j The corresponding voltage and current values ​​on the IV curve are recorded as P1 j [A] and P1 j [V], get P2 j The corresponding voltage and current values ​​on the IV curve are recorded as P2 j [A] and P2 j [V], according to P1 j [A] and P2 j [A] and P1 j [V] and P2 j [V] Obtain the relevant data corresponding to each sampling point on the IV curve, including the sampling voltage and sampling current. The sampling voltage and sampling current of the sampling point corresponding to the segment numbered j are recorded as V采样 [j] and A 采样 [j], then V 采样 [j]=(P1 j [V]+P2 j [V]) / 2, A 采样 [j]=(P1 j [A]+P2 j [A]) / 2;

[0022] The actual satellite includes an embedded controller and a memory connected to the embedded controller. The operating form corresponding to the embedded controller is obtained, and it is determined whether there is attack information in the operating form. If so, a security review of the embedded controller is performed. If not, the embedded controller enters the relevant data corresponding to each sampling point and stores it in the memory. The drawing software is used to import all the relevant data stored in the memory, and then the drawing software draws the corresponding standard IV curve.

[0023] Furthermore, the process of determining whether there is attack information in the running form and conducting a security review includes:

[0024] Get several operation evaluation items recorded in the operation form, get the evaluation indicators set for each operation evaluation item, and then get the number of operation evaluation items that meet the respective evaluation indicators, record this number as τ, set the alarm threshold, and record it as τ 告警 , when τ ≥ τ 告警 When τ<τ 告警 , it means that there is no attack information in the running form;

[0025] Configure a security word bag corresponding to each operation evaluation item. The security word bag is used to record several legal words corresponding to the current operation evaluation item. The operation evaluation item is disassembled into several evaluation words, and then the data part corresponding to the evaluation words belonging to the legal words in the operation evaluation item is marked as security information, and the data part corresponding to the evaluation words not belonging to the legal words in the operation evaluation item is located as attack information. The security information is retained, and all attack information is eliminated.

[0026] Furthermore, the process of receiving a frame of configuration data after the digital twin satellite is in operation and configuring its own power simulator to the same state as the actual satellite includes:

[0027] Obtain all satellite-related data corresponding to the actual satellite, build a digital twin satellite corresponding to the actual satellite through digital twin technology, and run the digital twin satellite within the set satellite operation time period. The digital twin satellite receives a frame of configuration data. The format of the configuration data includes: frame header, energy system identifier, configuration frame identifier, photovoltaic module parameters, satellite configuration parameters and frame tail. Among them, the frame header is the data starting point of a frame of configuration data, and the frame tail is the data cutoff point of a frame of configuration data. The energy system identifier is used as the unique identity authentication identifier of the current digital twin satellite, and the configuration frame identifier is used as the distinguishing identifier of the current configuration data. The photovoltaic module parameters include Voc, Isc, Vm, Im and Rs, and the satellite configuration parameters include the number of photovoltaic modules in series and the number of photovoltaic modules in parallel.

[0028] When the digital twin satellite successfully receives a frame of configuration data, the power simulator corresponding to the current digital twin satellite is configured according to the corresponding photovoltaic module parameters and satellite configuration parameters. When the configuration is completed, the digital twin satellite is synchronized with the actual satellite to the same state.

[0029] Furthermore, the process of activating the solar panel power supply simulator and receiving data from the digital twin satellite and the space environment simulator for solving includes:

[0030] Build a space environment simulator corresponding to the actual satellite, use the space environment simulator to obtain the space environment data of the actual satellite during operation, build a solar panel power supply simulator required for power supply simulation of the current actual satellite, and activate the solar panel power supply simulator. When the solar panel power supply simulator is activated, all data corresponding to the digital twin satellite and the space environment simulator are synchronously received at the set receiving frequency through the serial port corresponding to the solar panel simulator;

[0031] The format of all data received by the solar panel power supply simulator is: frame header-energy system identification-ground shadow area identification-satellite position data-satellite panel temperature-angle between sunlight and panel normal vector-total satellite orbit operation time-satellite panel fault status-satellite load operation and fault status-parity check code-frame tail;

[0032] After the solar panel power supply simulator receives all the data, it continues to perform calculations based on the actual satellite attitude position data and power supply and consumption conditions. The calculation contents are as follows:

[0033] The standard IV curve is offset in the voltage direction (x-axis) or current direction (y-axis). The offset is calculated as follows:

[0034] V offset =η v *μ v [a(tt Ref)+b(1353*(cos(β)-1))]*Fv;

[0035] I offset =η c *μ c [c(tt Ref )+d(1353*(cos(β)-1))]*Fc;

[0036] Where: a is the voltage temperature coefficient, b is the voltage illumination coefficient, c is the current temperature coefficient, d is the current illumination coefficient, β is the angle between the incident angle of sunlight and the normal vector of the sailboard, η v represents the voltage attenuation due to radiation, η c Indicates the current attenuation caused by radiation, the value range is 0-1, t indicates the start time of the solution, t Ref Indicates the end time of the solution, μ v and μ c It is used to indicate the voltage and current performance attenuation caused by satellite panel failure, etc., and the value range is 0-1. Fv represents the voltage fault coefficient, and Fc represents the battery pack current fault factor, and the value range is 0-1.

[0037] Furthermore, after the solution is completed, the process of outputting the voltage and current values ​​obtained by the solution, and synchronously returning the output voltage and output current to the digital twin satellite includes:

[0038] When the solar panel power supply simulator is fully solved, the voltage and current values ​​obtained by the solution are output and recorded as V 解算 and A 解算 , sum up all V 解算 The corresponding calculated voltage is used as the output voltage, and all A 解算 The corresponding solved current is used as the output current, and the synchronization frequency is set. The output voltage and output current solved by the solar panel simulator are returned to the corresponding digital twin satellite according to the synchronization frequency. The integrated electronic module set up by the digital twin satellite receives them in the following format, which is expressed as follows: frame header-output voltage-output current-CRC check-frame tail.

[0039] Furthermore, the process of the digital twin satellite judging the working condition of the current solar panels and then judging whether the actual satellite meets the expected demand under the current energy condition includes:

[0040] When the integrated electronic module of the digital twin satellite receives the output voltage and output current, it compares the output voltage and output current with the preset working voltage and working current, and then judges the working condition of the solar panels corresponding to the current actual satellite. The output voltage, output current, working voltage and working current are recorded as V 输出 , A输出 、V 工作 and A 工作 , when V 输出 ≥V 工作 , A 输出 ≥A 工作 If both of them are true, it is judged that the current working condition of the solar panel is normal operation. 输出 ≥V 工作 and A 输出 ≥A 工作 If any one of the above conditions is not true, the current working condition of the solar panel is judged to be abnormal operation;

[0041] When the working condition of the solar panels is abnormal, it is directly determined that the actual satellite cannot meet the corresponding expected demand under the current energy conditions. When the working condition of the solar panels is normal, the power consumption of different devices on the actual satellite is simulated to obtain the total device power consumption corresponding to the entire actual satellite, and determine whether the total device power consumption is lower than the preset power consumption threshold, and then generate different power consumption evaluation states, including qualified power consumption and abnormal power consumption;

[0042] If the total device power consumption is less than the power consumption threshold, the power consumption evaluation status is qualified;

[0043] If the total device power consumption is greater than or equal to the power consumption threshold, the power consumption assessment status is abnormal power consumption.

[0044] Compared with the prior art, the beneficial effects of the present invention are: through the digital twin technology, the virtual and the real are combined to realize the power supply simulation of the actual operating satellite to the greatest extent at the lowest cost. It does not simply simulate the solar panels, but comprehensively considers the satellite power supply and the power consumption of the equipment on the satellite. The working principle is different from the currently common SAS solar array simulator. It does not require a dedicated SAS stand-alone machine to generate a real IV curve, but uses a mathematical formula to generate an IV curve instead of the IV curve generated by the real physical device. The simulation effect is more realistic and reasonable, and the cost is lower. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 It is a flow chart of the present invention. DETAILED DESCRIPTION

[0046] like Figure 1 As shown, a digital twin satellite power supply simulation control method includes the following steps:

[0047] Step S1: according to the area and number of solar panels corresponding to the satellite for which power supply simulation is required, draw the corresponding IV curve under the set illumination conditions;

[0048] Step S2: sampling a corresponding number of sampling points on the IV curve according to a preset resolution, and obtaining relevant data corresponding to each sampling point on the IV curve and storing them in a memory connected to the embedded controller, thereby drawing a standard IV curve;

[0049] Step S3: After the digital twin satellite is in operation, it receives a frame of configuration data and configures its own power simulator to the same state as the actual satellite;

[0050] Step S4: activating the solar panel power supply simulator, receiving data from the digital twin satellite and the space environment simulator, and performing calculations based on the satellite's attitude position data and power supply and consumption;

[0051] Step S5: After the solution is completed, the voltage value and current value obtained by the solution are output, and the output voltage and output current are synchronously returned to the digital twin satellite;

[0052] Step S6: The digital twin satellite determines the current working condition of the solar panels, and then determines whether the actual satellite meets the expected requirements under the current energy conditions.

[0053] It should be further explained that, in a specific implementation process, according to the area and number of solar panels corresponding to the satellite for which power supply simulation is required, the process of drawing the corresponding IV curve under the set illumination conditions includes:

[0054] Select a satellite that needs to be simulated for power supply, which is an actual satellite that needs to be operated in orbit in space, obtain the number of solar panels corresponding to the actual satellite, record the number as N, obtain the area corresponding to each solar panel, number the solar panels, record the number as i, then i = 1, 2, 3, ..., n, where n is a natural number greater than 0;

[0055] The area of ​​the solar panel numbered i is recorded as S[i], and the areas of n solar panels are accumulated to obtain the corresponding total power generation area, which is recorded as S 总 ;

[0056] Then there is

[0057] The area of ​​each solar panel is in square meters, recorded as m^2, so the total power generation area S 总 The unit is also m^2. The illumination condition is set. The illumination condition is expressed as: 1.353kW / m^2, AM0, 25°C. Under this illumination condition, an IV curve that meets the actual operation of the current satellite is drawn.

[0058] It should be noted that 1.353kW / m^2 represents the light intensity required per square meter (m^2) of the solar panel, and the total required light intensity is 1.353kW / m^2*S 总 AM0 means atmospheric mass zero, which is particularly important in the field of solar energy. It is a standardized solar spectrum that represents the situation of sunlight passing through the earth's atmosphere to reach the surface. The AM0 spectrum represents the state of sunlight before it directly hits the earth's atmosphere, that is, the spectrum in space; 25℃ represents the ambient temperature required for solar panels.

[0059] It should be further explained that, in a specific implementation process, a corresponding number of sampling points are sampled on the IV curve according to a preset resolution, and relevant data corresponding to each sampling point on the IV curve is obtained and stored in a memory connected to the embedded controller, and then the process of drawing the standard IV curve includes:

[0060] A preset resolution, which is the horizontal interval distance for sampling the IV curve, is used to divide the IV curve into a plurality of sections according to the resolution, and the plurality of sections are numbered, and the number is j, then j=1, 2, 3, ..., m, where m is a natural number greater than 0;

[0061] The middle point of each segment is used as the sampling point for sampling the corresponding IV curve. The sampling point at the segment starting point corresponding to the corresponding segment is marked as P1, and the sampling point at the segment ending point corresponding to the corresponding segment is marked as P2. The segment starting point corresponding to the segment numbered j is marked as P1. j , the corresponding segment end point is recorded as P2 j ;

[0062] Get P1 j The corresponding voltage and current values ​​on the IV curve are recorded as P1 j [A] and P1 j [V], get P2 j The corresponding voltage and current values ​​on the IV curve are recorded as P2 j [A] and P2 j [V];

[0063] Then according to P1 j [A] and P2 j [A] and P1 j [V] and P2 j [V] Obtain the relevant data corresponding to each sampling point on the IV curve, the relevant data includes the sampling voltage and the sampling current, and record the sampling voltage and sampling current of the sampling point corresponding to the segment numbered j as V 采样 [j] and A采样 [j], then V 采样 [j]=(P1 j [V]+P2 j [V]) / 2, A 采样 [j]=(P1 j [A]+P2 j [A]) / 2;

[0064] The actual satellite includes an embedded controller and a memory connected to the embedded controller, obtains a running form corresponding to the embedded controller, and determines whether there is attack information in the running form. If so, a security review is performed on the embedded controller, and then all attack information is located through the security review, and the attack information is removed. If not, the embedded controller enters relevant data corresponding to each sampling point and stores it in the memory;

[0065] Further, the content of judging whether there is attack information is as follows: obtaining several operation evaluation items recorded in the operation form, obtaining the evaluation indicators set for each operation evaluation item, and then obtaining the number of operation evaluation items that meet the respective evaluation indicators, recording the number as τ, setting the alarm threshold, and recording the alarm threshold as τ 告警 , when τ ≥ τ 告警 When τ<τ 告警 , it means that there is no attack information in the running form;

[0066] Furthermore, the content of the security review is as follows: configuring a security word bag corresponding to each operation evaluation item, the security word bag is used to record a number of legal words corresponding to the current operation evaluation item, disassembling the operation evaluation item into a number of evaluation words, and then marking the data part corresponding to the evaluation words belonging to the legal words in the operation evaluation item as security information, positioning the data part corresponding to the evaluation words not belonging to the legal words in the operation evaluation item as attack information, retaining the security information, and removing all the attack information;

[0067] It should be noted that when attack information exists in the running form, it means that the embedded controller is in a dangerous environment, and the relevant data corresponding to the sampling point will not be entered, ensuring data security. When all the attack information in the running form is removed, the dangerous environment is transformed into a safe environment, and subsequent operations of entering relevant data are performed;

[0068] Use drawing software to import all relevant data stored in the memory, and then use the drawing software to draw a corresponding standard IV curve. The standard IV curve can characterize the power supply capacity of the solar panel under different load conditions.

[0069] It should be further explained that, in the specific implementation process, the process of receiving a frame of configuration data after the digital twin satellite is running and configuring its own power simulator to the same state as the actual satellite includes:

[0070] Obtain all satellite-related data corresponding to the actual satellite, and then build a digital twin satellite corresponding to the actual satellite through digital twin technology, set the satellite operation time period, operate the digital twin satellite during the satellite operation time period, and receive a frame of configuration data from the digital twin satellite. The format of the configuration data includes: frame header, energy system identifier, configuration frame identifier, photovoltaic module parameters, satellite configuration parameters, and frame tail;

[0071] Among them, the frame header is the data starting point of a frame of configuration data, the frame tail is the data cutoff point of a frame of configuration data, the energy system identifier is used as the unique identity authentication identifier of the current digital twin satellite, the configuration frame identifier is used as the distinguishing identifier of the current configuration data, the photovoltaic module parameters include Voc, Isc, Vm, Im and Rs, and the satellite configuration parameters include the number of photovoltaic modules in series and the number of photovoltaic modules in parallel;

[0072] When the digital twin satellite successfully receives a frame of configuration data, the power supply simulator corresponding to the current digital twin satellite is configured according to the corresponding photovoltaic module parameters and satellite configuration parameters, so that the configured digital twin satellite has the same power supply capacity as the actual satellite.

[0073] It should be noted that "Voc" represents the open circuit voltage of the actual satellite corresponding power supply. The open circuit voltage refers to the voltage of the battery when no load is connected. In other words, when the positive and negative ports of the actual satellite corresponding power supply are not connected, the output voltage is the open circuit voltage; "Isc" represents the short circuit current of the actual satellite corresponding power supply. The short circuit current refers to the current output by the battery when the positive and negative ports are short-circuited; "Vm" usually refers to the maximum power point voltage of the actual satellite corresponding power supply. The maximum power point voltage refers to the voltage at the maximum power output of the battery under specific light and temperature conditions; "Im" usually refers to the maximum power point current of the solar cell. The maximum power point current refers to the current at the maximum power output of the battery under specific light and temperature conditions; "Rs" usually refers to the series resistance of the actual satellite corresponding power supply. The series resistance refers to the influence of the internal resistance of the battery on the flow of current. The series resistance is an important parameter of the actual satellite corresponding power supply. It is one of the factors affecting the performance of the battery. The series resistance will cause a difference between the actual working voltage and the ideal working voltage of the battery, thereby affecting the output power of the battery. Generally, the smaller the series resistance, the better the performance of the battery.

[0074] It should be further explained that, in the specific implementation process, the process of activating the solar panel power supply simulator, receiving data from the digital twin satellite and the space environment simulator, and performing calculations based on the satellite's attitude position data and power supply and consumption includes:

[0075] Constructing a space environment simulator corresponding to an actual satellite, and using the space environment simulator to obtain space environment data of the actual satellite during operation, wherein the space environment data includes the temperature of the satellite sailboard, the mark of the earth shadow area, and the total time the satellite is in orbit;

[0076] Build a solar panel power supply simulator required for power supply simulation of the current actual satellite, and activate the solar panel power supply simulator. When the solar panel power supply simulator is activated, all data corresponding to the digital twin satellite and the space environment simulator are synchronously received through the serial port corresponding to the solar panel simulator at a set receiving frequency of once per second;

[0077] The format of all data received by the solar panel power supply simulator is: frame header-energy system identifier-ground shadow area identifier-satellite position data-satellite panel temperature-angle between sunlight and panel normal vector-total satellite on-orbit operation time-satellite panel fault status-satellite load operation and fault status-parity check code-frame tail;

[0078] After the solar panel power supply simulator receives all the above data, it continues to perform calculations based on the actual satellite attitude position data and power supply and consumption conditions. The calculation contents are as follows:

[0079] When simulating the voltage and current that a satellite solar panel can actually generate in space, the standard IV curve will be offset in the voltage direction (X-axis) or the current direction (Y-axis) according to the specific space environment characteristics. The offset is calculated according to the following formula:

[0080] V offset =η v *μ v [a(tt Ref )+b(1353*(cos(β)-1))]*Fv;

[0081] I offset =η c *μ c [c(tt Ref )+d(1353*(cos(β)-1))]*Fc;

[0082] Among them: a is the voltage temperature coefficient, b is the voltage illumination coefficient, c is the current temperature coefficient, d is the current illumination coefficient, and β is the angle between the incident angle of sunlight and the normal vector of the sailboard. During the entire life cycle of the satellite in orbit, the performance of the solar panel will continue to decline due to the radiation of high-energy rays in the universe, so η is used. v represents the voltage attenuation due to radiation, η c Indicates the current attenuation caused by radiation. These two values ​​are related to the total time the solar panel is in orbit, and the value range is 0-1;

[0083] t represents the start time of the solution, t Ref Indicates the end time of the solution;

[0084] μ v and μ c It is used to indicate the voltage and current performance degradation caused by satellite panel failure, etc., with a value range of 0-1. Fv and Fc indicate the fault factors of the power supply system. Fv represents the voltage fault coefficient, with a value range of 0-1. For example, there are 7 battery components in series, and the corresponding fault factor of a single series short circuit is (7-1) / 7=0.85. Fc indicates the current fault factor of the battery pack. For example, there are 15 battery components in parallel, and the corresponding fault factor of a parallel failure is (15-1) / 15=0.93. Fv and Fc are determined according to the proportion of faulty panels.

[0085] It should be further explained that in the specific implementation process, after the solution is completed, the process of outputting the voltage and current values ​​obtained by the solution, and synchronously returning the output voltage and output current to the digital twin satellite includes:

[0086] When the solar panel power supply simulator is fully solved, the voltage and current values ​​obtained by the solution are output, and the voltage value is recorded as V 解算 , and record the current value as A 解算 , summing up the solved voltages corresponding to all the voltage values ​​obtained by the solution as the output voltage, and summing up the solved currents corresponding to all the current values ​​obtained by the solution as the output current;

[0087] The synchronization frequency is set, and the synchronization frequency is recorded as f. The output voltage and output current calculated by the solar panel simulator are returned to the corresponding digital twin satellite according to the synchronization frequency. The integrated electronic module set by the digital twin satellite receives it in the following format, and the format is expressed as follows:

[0088] Frame header - output voltage - output current - CRC check - frame tail.

[0089] It should be further explained that, in the specific implementation process, the digital twin satellite determines the working condition of the current solar panels, and then determines whether the actual satellite meets the expected demand under the current energy conditions. The process includes:

[0090] When the integrated electronic module of the digital twin satellite receives the output voltage and output current, it compares the output voltage and output current with the preset working voltage and working current respectively, and then determines the working condition of the solar panels corresponding to the actual satellite at present;

[0091] The output voltage is recorded as V 输出 , the output current is recorded as A 输出 , the working voltage is recorded as V 工作 , the working current is recorded as A 工作 , the working voltage represents the minimum voltage value when the actual satellite corresponding solar panel maintains normal operation, and the working current represents the minimum current value when the actual satellite corresponding solar panel maintains normal operation;

[0092] When V 输出 ≥V 工作 , A 输出 ≥A 工作 If both of them are true, it is judged that the current working condition of the solar panel is normal operation. 输出 ≥V 工作 and A 输出 ≥A 工作 If any one of the above conditions is not true, the current working condition of the solar panel is judged to be abnormal operation;

[0093] When the solar panels are working abnormally, it is directly determined that the actual satellite cannot meet the corresponding expected demand under the current energy conditions. When the solar panels are working normally, the power consumption of different devices on the actual satellite is simulated. The contents of simulating the power consumption of the actual satellite are as follows:

[0094] Since the functions of all devices on the digital twin satellite are simulated, some devices only have software and no corresponding physical devices that actually consume energy. In order to simulate the power consumption of different devices on the actual satellite, a load simulator composed of power resistors is set in the solar panel power supply simulator.

[0095] According to the power and working voltage of each device installed on the actual satellite, the corresponding working current and equivalent resistance of each device are calculated, and a power resistor array is formed by using power resistors with different resistance values ​​corresponding to the equivalent resistance. The power consumption of each device is simulated separately, and then the total device power consumption corresponding to the entire actual satellite is obtained. It is judged whether the total device power consumption is lower than the preset power consumption threshold, and then different power consumption evaluation states are generated;

[0096] The power consumption evaluation status includes qualified power consumption and abnormal power consumption;

[0097] If the total device power consumption is less than the power consumption threshold, the power consumption evaluation status is qualified;

[0098] If the total device power consumption is greater than or equal to the power consumption threshold, the power consumption assessment status is abnormal power consumption;

[0099] It should be noted that a multi-way relay board is set up in the solar panel power supply simulator. By using the multi-way relay board to control which power resistors are connected to the power bus according to instructions, the power supply situation of the actual satellite can be simulated on the digital twin satellite, making it easier to observe the status of the power supply system.

[0100] The above embodiments are only used to illustrate the technical method of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that the technical method of the present invention may be modified or replaced by equivalents without departing from the spirit and scope of the technical method of the present invention.

Claims

1. A digital twin satellite power supply simulation control method, characterized in that: The following steps are involved: Step S1: according to the area and number of solar panels corresponding to the satellite for which power supply simulation is required, draw the corresponding IV curve under the set illumination conditions; Step S2: sampling a corresponding number of sampling points on the IV curve according to a preset resolution, and obtaining relevant data corresponding to each sampling point on the IV curve and storing them in a memory connected to the embedded controller, thereby drawing a standard IV curve; Step S3: After the digital twin satellite is in operation, it receives a frame of configuration data and configures its own power simulator to the same state as the actual satellite; Step S4: activating the solar panel power supply simulator, receiving data from the digital twin satellite and the space environment simulator, and performing calculations based on the satellite's attitude position data and power supply and consumption; Step S5: After the solution is completed, the voltage value and current value obtained by the solution are output, and the output voltage and output current are synchronously returned to the digital twin satellite; Step S6: The digital twin satellite determines the current working condition of the solar panels, and then determines whether the actual satellite meets the expected demand under the current energy condition; The process of activating the solar panel power simulator and receiving data from the digital twin satellite and space environment simulator for solution includes: Build a space environment simulator corresponding to the actual satellite, use the space environment simulator to obtain the space environment data of the actual satellite during operation, build a solar panel power supply simulator required for power supply simulation of the current actual satellite, and activate the solar panel power supply simulator. When the solar panel power supply simulator is activated, all data corresponding to the digital twin satellite and the space environment simulator are synchronously received at the set receiving frequency through the serial port corresponding to the solar panel simulator; The format of all data received by the solar panel power supply simulator is: frame header-energy system identification-ground shadow area identification-satellite position data-satellite panel temperature-angle between sunlight and panel normal vector-total satellite orbit operation time-satellite panel fault status-satellite load operation and fault status-parity check code-frame tail; After the solar panel power supply simulator receives all the data, it continues to perform calculations based on the actual satellite attitude position data and power supply and consumption conditions. The calculation contents are as follows: The standard IV curve is offset in the voltage direction (x-axis) or current direction (y-axis). The offset is calculated as follows: V offset =the v *m v [a(tt Ref )+b(1353*(cos(β)-1))]* F ; I offset =the c *m c [c(tt Ref )+d(1353*(cos(β)-1))]* Fc ; Where: a is the voltage temperature coefficient, b is the voltage illumination coefficient, c is the current temperature coefficient, d is the current illumination coefficient, β is the angle between the incident angle of sunlight and the normal vector of the sailboard, η v represents the voltage attenuation due to radiation, η c Indicates the current attenuation caused by radiation, the value range is 0-1, t indicates the start time of the solution, t Ref Indicates the end time of the solution, μ v and μ c It is used to indicate the voltage and current performance degradation caused by satellite sailboard failure, etc., and the value range is 0-1. F represents the voltage fault coefficient, Fc Indicates the battery pack current fault factor, the value range is 0-1.

2. A digital twin satellite power supply simulation control method according to claim 1, characterized in that: According to the area and number of solar panels corresponding to the satellite for power simulation, the process of drawing the corresponding IV curve under the set lighting conditions includes: Select a satellite that needs to be simulated for power supply. The satellite is an actual satellite that needs to be operated in orbit in space. Obtain the number of solar panels corresponding to the actual satellite, recorded as N. Obtain the area corresponding to each solar panel. Number several solar panels and record them as i, i = 1, 2, 3, ..., n, where n is a natural number greater than 0. The area of ​​the solar panel numbered i is recorded as S[i]. Add up the areas of n solar panels to obtain the total power generation area, which is recorded as S. 总 ; have The total power generation area S 总 The unit is m^2. The following illumination conditions are set: 1.353kW / m^2, AM0, 25℃. Under this illumination condition, an IV curve that conforms to the actual operation of the current satellite is drawn.

3. A digital twin satellite power supply simulation control method according to claim 2, characterized in that: The process of sampling a corresponding number of sampling points on the IV curve according to a preset resolution, obtaining relevant data corresponding to each sampling point on the IV curve, and then drawing a standard IV curve includes: The IV curve is divided into several sections according to the preset resolution, and the sections are numbered and recorded as j, j = 1, 2, 3, ..., m, where m is a natural number greater than 0. The middle point of each section is used as the sampling point for sampling, and the starting point and end point of the section numbered j are recorded as P1 and P2, respectively. j and P2 j ; Get P1 j The corresponding voltage and current values ​​on the IV curve are recorded as P1 j [A] and P1 j [V], get P2 j The corresponding voltage and current values ​​on the IV curve are recorded as P2 j [A] and P2 j [V], according to P1 j [A] and P2 j [A] and P1 j [V] and P2 j [V] Obtain relevant data corresponding to each sampling point on the IV curve, the relevant data including sampling voltage and sampling current; The sampling voltage and sampling current of the sampling point corresponding to the segment numbered j are respectively recorded as V 采样 [j] and A 采样 [j], then V 采样 [j]=(P1 j [V]+P2 j [V]) / 2, A 采样 [j]=(P1 j [A]+P2 j [A]) / 2; The actual satellite includes an embedded controller and a memory connected to the embedded controller. The operating form corresponding to the embedded controller is obtained, and it is determined whether there is attack information in the operating form. If so, a security review of the embedded controller is performed. If not, the embedded controller enters the relevant data corresponding to each sampling point and stores it in the memory. The drawing software is used to import all the relevant data stored in the memory, and then the drawing software draws the corresponding standard IV curve.

4. A digital twin satellite power supply simulation control method according to claim 3, characterized in that: The process of determining whether there is attack information in the running form and conducting a security review includes: Get several operation evaluation items recorded in the operation form, get the evaluation indicators set for each operation evaluation item, and then get the number of operation evaluation items that meet the respective evaluation indicators, record this number as τ, set the alarm threshold, and record it as τ 告警 , when τ ≥ τ 告警 When τ<τ 告警 , it means that there is no attack information in the running form; Configure a security word bag corresponding to each operation evaluation item. The security word bag is used to record several legal words corresponding to the current operation evaluation item. The operation evaluation item is disassembled into several evaluation words, and then the data part corresponding to the evaluation words belonging to the legal words in the operation evaluation item is marked as security information, and the data part corresponding to the evaluation words not belonging to the legal words in the operation evaluation item is located as attack information. The security information is retained, and all attack information is eliminated.

5. A digital twin satellite power supply simulation control method according to claim 4, characterized in that: The process of receiving a frame of configuration data after the digital twin satellite is in operation and configuring its own power simulator to the same state as the actual satellite includes: Obtain all satellite-related data corresponding to the actual satellite, build a digital twin satellite corresponding to the actual satellite through digital twin technology, and run the digital twin satellite within the set satellite operation time period. The digital twin satellite receives a frame of configuration data. The format of the configuration data includes: frame header, energy system identifier, configuration frame identifier, photovoltaic module parameters, satellite configuration parameters and frame tail. Among them, the frame header is the data starting point of a frame of configuration data, and the frame tail is the data cutoff point of a frame of configuration data. The energy system identifier is used as the unique identity authentication identifier of the current digital twin satellite, and the configuration frame identifier is used as the distinguishing identifier of the current configuration data. The photovoltaic module parameters include Voc, Isc, Vm, Im and Rs, and the satellite configuration parameters include the number of photovoltaic modules in series and the number of photovoltaic modules in parallel. When the digital twin satellite successfully receives a frame of configuration data, the power simulator corresponding to the current digital twin satellite is configured according to the corresponding photovoltaic module parameters and satellite configuration parameters. When the configuration is completed, the digital twin satellite is synchronized with the actual satellite to the same state.

6. A digital twin satellite power supply simulation control method according to claim 5, characterized in that: After the solution is completed, the voltage and current values ​​obtained by the solution are output, and the process of synchronously returning the output voltage and output current to the digital twin satellite includes: When the solar panel power supply simulator is fully solved, the voltage and current values ​​obtained by the solution are output and recorded as V 解算 and A 解算 , sum up all V 解算 The corresponding calculated voltage is used as the output voltage, and all A 解算 The corresponding solved current is used as the output current, and the synchronization frequency is set. The output voltage and output current solved by the solar panel simulator are returned to the corresponding digital twin satellite according to the synchronization frequency. The integrated electronic module set up by the digital twin satellite receives them in the following format, which is expressed as follows: frame header-output voltage-output current-CRC check-frame tail.

7. A digital twin satellite power supply simulation control method according to claim 6, characterized in that: The process of using the digital twin satellite to judge the current working condition of the solar panels and then determine whether the actual satellite meets the expected demand under the current energy conditions includes: When the integrated electronic module of the digital twin satellite receives the output voltage and output current, it compares the output voltage and output current with the preset working voltage and working current, and then judges the working condition of the solar panels corresponding to the current actual satellite. The output voltage, output current, working voltage and working current are recorded as V 输出 , A 输出 、V 工作 and A 工作 ; When V 输出 ≥V 工作 , A 输出 ≥A 工作 If both of them are true, it is judged that the current working condition of the solar panel is normal operation. 输出 ≥V 工作 and A 输出 ≥A 工作 If any one of the above conditions is not true, the current working condition of the solar panel is judged to be abnormal operation; When the working condition of the solar panels is abnormal, it is directly determined that the actual satellite cannot meet the corresponding expected demand under the current energy conditions. When the working condition of the solar panels is normal, the power consumption of different devices on the actual satellite is simulated to obtain the total device power consumption corresponding to the entire actual satellite, and determine whether the total device power consumption is lower than the preset power consumption threshold, and then generate different power consumption evaluation states, including qualified power consumption and abnormal power consumption; If the total device power consumption is less than the power consumption threshold, the power consumption evaluation status is qualified; If the total device power consumption is greater than or equal to the power consumption threshold, the power consumption assessment status is abnormal power consumption.

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