Method and system for predicting power of solar cell array of all-electric propulsion satellite
By correcting the ground model with on-orbit measured data, the problem of inaccurate prediction of solar array output power during the orbit change of all-electric propulsion satellites was solved, achieving higher accuracy power prediction and supporting dynamic optimization of orbit change strategies.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- CHINA ACADEMY OF SPACE TECHNOLOGY
- Filing Date
- 2026-01-21
- Publication Date
- 2026-05-26
AI Technical Summary
Existing technologies make it difficult to accurately assess the output power of solar arrays during orbit changes of all-electric propulsion satellites, especially when they experience different radiation zones and solar bursts, resulting in a large deviation between the predicted and actual values from ground models.
By dynamically correcting the ground model using on-orbit measured data, selecting the shunt stage under power supply status to obtain telemetry data, calculating the current prediction deviation coefficient, and using the average deviation coefficient to correct the ground predicted current, the prediction accuracy is improved.
It significantly improves the accuracy of solar array output current and power prediction, supports dynamic adjustment of orbit change strategies, and ensures the efficient operation of electrically propelled satellites.
Smart Images
Figure CN122087254A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of satellite power system technology, and in particular to a method, system, computer device, and computer-readable storage medium for predicting the power of a solar array in an all-electric propulsion satellite. Background Technology
[0002] Currently, electric propulsion technology has been successfully applied to multiple existing satellite platforms due to its high specific impulse, and next-generation satellite platforms are also mainly based on all-electric propulsion technology. Compared to chemical propulsion satellites, all-electric propulsion satellites generally start at a lower orbit for orbit changes. With the current thrust level of electric thrusters, it takes six months to a year to change orbit to geostationary orbit (GEO). The entire transfer orbit lasts for a long time, requiring ensuring sufficient power supply from the solar array during the sunshine period, and timely assessment of the solar array's output power margin to ensure dynamic adjustment of the electric propulsion orbit change strategy.
[0003] GEO satellites generally employ a fully adjustable bus architecture; therefore, the core of evaluating the output power of the solar array is the evaluation of the output current. The output current is mainly affected by factors such as irradiance, temperature, solar panel angle, and the Sun-Earth factor. While factors like temperature, solar panel angle, and the Sun-Earth factor can generally be obtained relatively accurately through on-orbit telemetry or calculation, irradiance dose requires specialized equipment for measurement. Satellites without specific research missions typically do not have such equipment, making it difficult to obtain accurate irradiance dose data directly in orbit.
[0004] Currently, the radiation dose prediction for solar arrays on chemically propelled satellites widely employs the Earth's radiation belt model AP8 / AE8, which is further substituted into ground-based solar array output power prediction models. Practice has shown that this method has high accuracy in predicting radiation in GEO orbit, thus allowing for relatively accurate prediction of on-orbit output current and power. However, all-electric propulsion satellites undergo orbital maneuvers involving different paths, including multiple crossings of the Van Allen radiation belts where radiation doses are severe. Furthermore, prolonged orbital maneuvers may encounter random events such as solar bursts. Therefore, the predicted values obtained from the aforementioned models may deviate significantly from the actual on-orbit values due to variations in radiation dose.
[0005] In summary, based on the predicted output power of the solar array during the ground development phase, it is necessary to further realize real-time on-orbit power prediction and correction, thereby providing strong support for the flexible adjustment of the orbit change strategy of all-electric propulsion satellites. Summary of the Invention
[0006] To address the problems in existing technologies, this invention proposes a method, system, storage medium, and computer equipment for predicting the power of the solar array of an all-electric propulsion satellite. By fusing on-orbit measured data to dynamically correct the ground model, the accuracy of predicting the output power of the solar array of an all-electric propulsion satellite during complex orbit changes is improved.
[0007] To achieve the above-mentioned technical effects, on the one hand, the present invention provides a method for predicting the power of a solar array in an all-electric propulsion satellite, comprising the following steps:
[0008] S1. During the satellite development phase, an output power prediction model is established based on ground test data of the solar cell array; the output power prediction model is used to predict the output current of the solar cell array and multiply it by the bus voltage to obtain the output power.
[0009] S2. When the satellite is in the electric propulsion orbit change phase after launch, select a sequential switch shunt adjustment circuit that is in power supply state as a reference shunt stage; obtain the on-orbit actual output current of the reference shunt stage at the current moment, the corresponding solar panel angle and the telemetry data of the solar panel temperature;
[0010] S3. Based on the solar panel angle at the working point, the solar panel temperature, the predicted radiation dose at the ground at the current moment, and the calculated Sun-Earth factor, input the output power prediction model to obtain the first predicted ground current of the reference shunt stage at the current moment;
[0011] S4. Calculate the current prediction deviation coefficient of the reference shunt stage at the current moment based on the actual on-orbit output current and the first ground predicted current;
[0012] S5. Repeat steps S2 to S4 according to a preset time interval to obtain the current prediction deviation coefficient corresponding to n consecutive different times, and calculate its average value to obtain the average current prediction deviation coefficient of the reference shunt stage.
[0013] S6. Obtain the second ground predicted current of all shunt stages, including the reference shunt stage, at the time to be predicted through the output power prediction model, and correct it using the average current prediction deviation coefficient to obtain the corrected predicted current of each shunt stage.
[0014] S7. Based on the predicted current after correction of each shunt stage, sum and calculate the predicted total current of the solar cell array;
[0015] S8. Calculate the expected total power of the solar cell array based on the expected total current of the solar cell array.
[0016] Furthermore, the selection rule for the reference shunt stage is as follows: the target shunt stage is in a powered state, and all solar arrays on the entire solar panel corresponding to the target shunt stage are in a powered state.
[0017] Furthermore, the current prediction deviation coefficient is the ratio of the actual on-orbit output current of the reference shunt stage to the first predicted ground current.
[0018] Furthermore, the average current prediction deviation coefficient is the average value of the current prediction deviation coefficient corresponding to n consecutive different times.
[0019] Furthermore, the selection rule for the time interval is as follows: when the satellite is within the inner Van Allen radiation belt, the interval is a single orbital period; when the satellite is outside the inner Van Allen radiation belt, the interval is a day.
[0020] Furthermore, the corrected predicted current is the product of the second ground predicted current and the average current predicted deviation coefficient.
[0021] Furthermore, the ground test data is AM0 illumination test data.
[0022] On the other hand, the present invention also provides a system for predicting the power of a solar array on an all-electric propulsion satellite, the system being used to implement the method described above, the system comprising:
[0023] The model building module is used to build an output power prediction model based on ground test data of the solar cell array during the satellite development phase.
[0024] The data acquisition module is used to select the reference shunt stage where all corresponding arrays are in a powered state during on-orbit operation, and to acquire its actual on-orbit output current, solar panel angle and solar panel temperature telemetry data.
[0025] The deviation calculation module is used to calculate the predicted ground current based on the output power prediction model, and to calculate the current prediction deviation coefficient and its average value based on the actual on-orbit output current.
[0026] The correction prediction module is used to correct the predicted current at the prediction time output by the output power prediction model using the average current prediction deviation coefficient.
[0027] The total power prediction module is used to calculate the total expected output power of the solar array based on the corrected expected current of each shunt stage and the bus voltage.
[0028] Additionally, a computer-readable storage medium and a computer device are provided, the storage medium being used to store a computer program for performing the above-described method for predicting the power of a solar array in an all-electric propulsion satellite.
[0029] The computer device includes a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, it implements the method for predicting the power of the all-electric propulsion satellite solar array as described above.
[0030] The method and system for predicting the power of the solar array of an all-electric propulsion satellite described in this invention, compared with the prediction method based on ground models during the development stage that is widely used in the satellite field, can further improve the accuracy of predicting the output current of the solar array by effectively combining on-orbit telemetry data. This allows for a more accurate assessment of the overall satellite power margin and has strong engineering application value and promotional significance for dynamically adjusting the power of each subsystem of the satellite to ensure efficient orbit change and for quickly formulating emergency plans in case of failure. Attached Figure Description
[0031] Figure 1 This is a flowchart illustrating the steps of the all-electric propulsion satellite solar array power prediction method according to an embodiment of the present invention;
[0032] Figure 2 This is a schematic diagram of the satellite hardware circuit on which the output power prediction model of the all-electric propulsion satellite solar array power prediction method of the present invention is based;
[0033] Figure 3 This is a flowchart illustrating the specific implementation of the all-electric propulsion satellite solar array power prediction method described in this invention.
[0034] Figure 4 This is a schematic diagram of the specific circuit structure of the solar cell array, solar panel drive mechanism, and power controller in the all-electric propulsion satellite solar cell array power prediction method of the present invention.
[0035] Figure 5 This is a schematic diagram of the structure of the all-electric propulsion satellite solar array power prediction system provided in another embodiment of the present invention;
[0036] Figure 6 A schematic diagram of the structure of the computer device provided by the present invention. Detailed Implementation
[0037] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.
[0038] It should be noted that references to "an embodiment," "embodiment," "example embodiment," etc., in this specification refer to the described embodiment including specific features, structures, or characteristics, but not every embodiment must include these specific features, structures, or characteristics. Furthermore, such expressions do not refer to the same embodiment. Moreover, when describing specific features, structures, or characteristics in conjunction with embodiments, whether or not explicitly described, it is indicated that incorporating such features, structures, or characteristics into other embodiments is within the knowledge of those skilled in the art.
[0039] Furthermore, certain terms are used in the specification and subsequent claims to refer to specific components or parts. Those skilled in the art will understand that manufacturers may use different names or terms to refer to the same component or part. This specification and subsequent claims do not distinguish components or parts by differences in name, but rather by differences in function. The terms "comprising" and "including" used throughout the specification and subsequent claims are open-ended and should be interpreted as "including but not limited to." Additionally, the term "connection" here includes any direct and indirect electrical connection means. Indirect electrical connection means include connections made through other means.
[0040] This invention provides a method and system for predicting the power output of a solar array in an all-electric propulsion satellite. By modifying the output results of the solar array based on the solar array output power prediction model established during the conventional satellite development phase and combining it with on-orbit telemetry data, a more accurate prediction of the solar array output power during future satellite operation can be achieved.
[0041] To enable those skilled in the art to reproduce and implement the present invention, the various steps of the method and system for predicting the power of the solar array of an all-electric propulsion satellite will be described in detail below with reference to the accompanying drawings and specific embodiments. These embodiments are specific illustrations of the present invention, and their descriptions are helpful in understanding the present invention, but should not be construed as limiting the present invention.
[0042] Figure 1 This invention illustrates a method for predicting the power of a solar array on an all-electric propulsion satellite, according to an embodiment of the present invention. This method significantly improves the accuracy of power prediction during long-term orbit change phases by dynamically correcting a ground model through the fusion of on-orbit measured satellite data. The method includes the following steps:
[0043] S1: During the satellite development phase, an output power prediction model is established based on ground test data of the solar cell array. This output power prediction model is used to predict the output current of the solar cell array, which is then multiplied by the bus voltage to obtain the output power. In this embodiment, the ground test data is AM0 (zero atmospheric mass) illumination test data.
[0044] The solar array output power prediction model is based on, for example, Figure 2 The satellite hardware circuit shown consists of a solar array, a solar panel drive mechanism (SADA), and a power controller (PCU). The solar array comprises N solar panels, each with M1 to M2 solar panels. N There are X solar cell arrays in total. There are Y subarrays, corresponding to Y sequential switching shunt regulator circuits (S3R) in the PCU. As the overall satellite load changes, each S3R is in a shunt, power supply, or shunt / power supply regulation state, and the corresponding subarray is simultaneously in a shunt, power supply, or shunt / power supply regulation state. Each S3R circuit is equipped with a telemetry I for the solar array input current. S3Ri Each sailboard is equipped with a remote temperature sensor (T). i .
[0045] Specifically, the development of the output power prediction model relies on the AM0 illumination test completed before satellite launch. See also Figure 3 Before the delivery of solar array products, an AM0 illumination test will be conducted on the ground. This test will obtain the current-voltage characteristic curve (IV curve) of each solar array. Since GEO satellites (all-electric propulsion satellites) generally use S3R technology to obtain a fully adjustable bus, the current value at the corresponding bus voltage operating point on the IV curve under AM0 conditions can be determined. This allows for the establishment of a model to predict the output power of each solar array. Based on the irradiance dose, solar panel temperature, solar panel angle, and solar-terrestrial factor at a certain operating point during the predicted orbit change period, the output current I of the solar array at that operating point can be predicted. 地面预计 .
[0046] S2: When the satellite is in the electric propulsion orbit change phase after launch, select a sequential switch shunt adjustment circuit that is in a powered state as a reference shunt stage; obtain the on-orbit actual output current of the reference shunt stage, the corresponding solar panel angle and the telemetry data of the solar panel temperature at the current moment; specifically, the selection rule of the reference shunt stage is: the target shunt stage is in a powered state, and all solar panels on the entire solar panel where all solar cell arrays corresponding to the target shunt stage are located are in a powered state.
[0047] In practice, after satellite launch, the solar array deploys in orbit and the satellite begins its electric propulsion orbit change. Due to the significant power demand of the entire satellite during the all-electric propulsion orbit change process, most of the S3Rs are in a powered state. To address this, this embodiment records the telemetry value I of the on-orbit output current of a certain reference shunt stage (S3Ri) solar array at time t. S3Ri-t-在轨实际 θ (the angle of the solar panel telemetry (or the value calculated based on the overall satellite attitude telemetry)) t The remote temperature T of the solar panel corresponding to the shunt stage is measured. t S3R i The selection principle is that the entire shunt stage is in a power supply state, and all arrays on the solar panel where the corresponding array of the shunt stage is located are in a power supply state, so as to ensure that the temperature of the solar panel remains stable around time t. If the temperature change is large when S3Ri is in the shunt / power supply regulation state, it will introduce a certain prediction deviation.
[0048] S3: Based on the solar panel angle at the operating point, the solar panel temperature, the radiation dose predicted from the ground at the current moment, and the calculated Sun-Earth factor at the current moment, the output power prediction model is input to obtain the first predicted ground current of the reference shunt stage at the current moment; that is, this embodiment combines on-orbit telemetry data θ t T t In addition to the expected radiation dose and the calculated Sun-Earth factor, the on-orbit expected current I was calculated using the solar array output power prediction model established during the satellite development phase. S3Ri-t-地面预计 .
[0049] S4: Based on the actual on-orbit output current and the first predicted ground current, calculate the current prediction deviation coefficient of the reference shunt stage at the current moment; specifically, the current prediction deviation coefficient is the ratio of the actual on-orbit output current to the first predicted ground current. That is, calculate the output current prediction deviation coefficient of the S3Ri shunt stage solar cell array as I. S3Ri-err =I S3Ri-t-在轨实际 / I S3Ri-t-地面预计 This coefficient primarily reflects the deviation in the predicted irradiation dose.
[0050] S5: Repeat steps S2 to S4 according to a preset time interval to obtain the current prediction deviation coefficient corresponding to n consecutive different times, and calculate its average value to obtain the average current prediction deviation coefficient applicable to all shunt stages; wherein, the selection rule of the time interval is: when the satellite is within the inner Van Allen radiation zone, the interval is a single orbital period; when the satellite is outside the inner Van Allen radiation zone, the period is a day.
[0051] In practice, a certain time interval t is selected. 周期 Repeat the above calculation steps with a certain number of working points n to obtain t+t 周期 t+2*t 周期 ...t+n*t 周期 The deviation coefficient corresponding to the operating point. Where t 周期 Selection principle: For lower orbits, especially those corresponding to the inner Van Allen radiation belts, t 周期 The selection can be based on the orbit duration; for orbital ranges outside the inner Van Allen radiation belts where the radiation dose is relatively significantly reduced, t 周期 The selection can be based on a daily period; the selection principle for n is to take into account factors such as telemetry error and occasional changes in the space environment, and the preferred value of n is 3 to 5.
[0052] Then, the average of the calculated n current prediction deviation coefficients is taken to obtain the average current prediction deviation coefficient I. S3Ri-err-av .
[0053] S6: Obtain the second ground predicted current of all shunt stages, including the reference shunt stage, at the time to be predicted through the output power prediction model, and correct it using the average current prediction deviation coefficient to obtain the corrected predicted current; the corrected predicted current of each shunt stage is specifically the product of the second ground predicted current and the average current prediction deviation coefficient.
[0054] This embodiment predicts the output current of the solar array at a future time t1. First, based on the predicted temperature, solar panel angle, and Earth-Sun factor at time t1, the predicted on-orbit current I of all shunt stages, including the reference shunt stage, is calculated using the solar array output power prediction model established during the satellite development phase. S3Ri-t1-地面预计1 (i=1~Y), then consider the average current prediction deviation factor I. S3Ri-err-av The corrected predicted current I was calculated. S3Ri-t1-地面预计2 =I S3Ri-t1-地面预计1 ×I S3Ri-err-av .
[0055] S7: Calculate the expected total current of the solar cell array based on the expected current corrected for each shunt stage.
[0056] Based on the predicted current of each shunt stage calculated in step S6, the predicted total current of the solar array can be further calculated. .
[0057] S8: Calculate the expected total power of the solar array based on the expected total current of the solar array. Summate the expected total current of the solar array based on the corrected expected current of each shunt stage. That is, calculate the expected total current I of the solar array based on the calculated total current I of the solar array in step S7. SA Multiply by the bus voltage to calculate the expected total current P. SA =I SA *V BUS .
[0058] See Figure 4 Taking one hardware design as an example, the specific explanation is as follows: The satellite design has north and south wings, with three boards per wing. Each board has three subarrays, and the three subarrays correspond to one S3R shunt stage of the PCU. The current is shunted starting from the S3R shunt stage with the smallest number, based on the load size. Each S3R circuit has a telemetry I for the solar array input current. S3Ri Each sailboard is equipped with a remote temperature sensor (T). i .
[0059] When solar array products are delivered, a predictive model can be established based on ground-based AM0 illumination test data. This model can predict the output current of the S3R shunt stage solar array at any on-orbit operating time and location, given input conditions such as irradiance dose, solar panel temperature, solar panel angle, and solar-terrestrial factor, thus obtaining I.S3Ri-地面预计 After satellite launch and the electric propulsion system begins orbit change, the overall satellite power demand is high during electric propulsion operation. At this time, the solar array power margin is limited. The S3R1 shunt stage corresponding to the north wing inner panel array is in full shunt mode, S3R3 is in shunt / power supply adjustment mode, and S3R5 is in full power supply mode. Therefore, S3R5 is selected to record the telemetry value I of the first solar array output current. S3R5-在轨实际1 and the corresponding remote temperature measurement value T of the outer panel 3-1 Remote measurement value θ of the north wing sail angle N-1 The solar-terrestrial factor and radiation dose at the corresponding location are calculated and substituted into the ground-based prediction model to obtain I. S3R5-地面预计1-1 and the current prediction deviation coefficient I S3R-err-1 =I S3R5-在轨实际-1 / I S3R5-地面预计1-1 Select the deviation coefficient data I from the first 5 orbital changes. S3R-err-1 ~I S3R-err-5 Calculate the average current prediction deviation coefficient Based on this, the output current value of the S3Ri solar array in the 6th cycle is predicted, based on the predicted temperature T in the 6th cycle. 3-6 North wing sail angle θ N-6 Inputs such as the Earth-Sun factor and radiation dose are used to calculate the predicted on-orbit current I for shunt stages 1-6 using the solar array output power prediction model established during the satellite development phase. S3R1-地面预计1-6 ~I S3R6-地面预计1-6 This allows us to obtain the corrected on-orbit predicted current I for shunt stages 1-6. S3R1-在轨预计2~6 ~I S3R6-在轨预计2~6 =I S3R1-地面预计1-6 ~I S3R6-地面预计1-6 *I S3R-err-av Output current of the south and north wing arrays under full power supply conditions. .
[0060] Figure 5 This invention illustrates a power prediction system 100 for an all-electric propulsion satellite solar array, provided in another embodiment of the present invention. System 100 is used to implement the methods described in the above embodiments and includes a model building module 10, a data acquisition module 20, a deviation calculation module 30, a correction prediction module 40, and a total power prediction module 50, wherein:
[0061] The model building module 10 is used to establish an output power prediction model based on ground test data of the solar cell array during the satellite development phase; the data acquisition module 20 is used to select a reference shunt stage where all corresponding subarrays are in a power supply state during on-orbit operation, and to acquire its actual on-orbit output current, solar panel angle (or telemetry data required to calculate the solar panel angle), and solar panel temperature telemetry data; the deviation calculation module 30 is used to calculate the ground prediction current based on the output power prediction model, and to calculate the current prediction deviation coefficient and its average value based on the actual on-orbit output current; the correction prediction module 40 is used to correct the prediction current at the prediction time output by the output power prediction model using the average current prediction deviation coefficient; and the total power prediction module 50 is used to calculate the total predicted output power of the solar cell array based on the corrected predicted current of each shunt stage and the bus voltage.
[0062] The specific implementation and operation process of each module in the system 100 described in this embodiment can be understood by referring to the relevant descriptions in the foregoing method embodiments, and all of them can achieve the functions and effects achieved by the corresponding method steps. For the sake of simplicity and to avoid repetition, they will not be described again here.
[0063] In summary, this invention selects the S3R shunt stage under stable power supply as a reference and simultaneously collects telemetry data such as its on-orbit output current, solar panel angle, and temperature. It then calculates the theoretical current using a ground model and obtains the current deviation coefficient reflecting actual irradiance attenuation. By statistically averaging multiple periodic deviation coefficients, a correction factor characterizing the systematic deviation of the current orbital stage is obtained. Finally, this correction factor is applied to predict power at any future time, achieving real-time, closed-loop correction of the ground model. Thus, this invention significantly improves the accuracy of solar array power prediction, providing reliable technical support for accurate assessment of on-orbit power margin and dynamic optimization of orbit-changing strategies for all-electric propulsion satellites.
[0064] This invention also provides a computer-readable storage medium for storing a computer program for executing the above-described method for predicting the power of a solar array in an all-electric propulsion satellite. For example, computer program instructions, when executed by a computer, can invoke or provide the methods and / or technical solutions according to this application through the operation of the computer. The program instructions for invoking the methods of this application may be stored in a fixed or removable storage medium, and / or transmitted via data streams in broadcast or other signal carrying media, and / or stored in the storage medium of a computer device operating according to the program instructions. Here, according to one embodiment of this application, it includes a... Figure 6 The computer device 400 shown preferably includes a memory 200 for storing computer programs and a processor 300 for executing computer programs. When the computer program is executed by the processor 300, the computer device 400 is triggered to execute the methods and / or technical solutions based on the foregoing embodiments.
[0065] Numerous specific details are set forth in the specification provided herein. However, it will be understood that embodiments of the invention may be practiced without these specific details. In some instances, well-known methods, structures, and techniques have not been shown in detail so as not to obscure the understanding of this specification.
[0066] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element. Furthermore, it should be noted that the scope of the methods and apparatuses in the embodiments of the present invention is not limited to performing functions in the order shown or discussed, but may also include performing functions substantially simultaneously or in the reverse order, depending on the functions involved. For example, the described methods may be performed in a different order than described, and various steps may be added, omitted, or combined. Additionally, features described with reference to certain examples may be combined in other examples.
[0067] Of course, the present invention may have other various embodiments. Without departing from the spirit and essence of the present invention, those skilled in the art can make various corresponding changes and modifications according to the present invention, but these corresponding changes and modifications should all fall within the protection scope of the appended claims.
Claims
1. An all-electric propulsion satellite solar array power prediction method, characterized by, The method comprises the steps of: S1, during the satellite development stage, an output power prediction model is established based on the ground test data of the solar array; the output power prediction model is used to predict the output current of the solar array, and the output power is obtained by multiplying the bus voltage; S2, when the satellite is in the electric propulsion orbit transfer stage after being launched, a sequential switch shunt regulation circuit in a power supply state is selected as a reference shunt stage; telemetry data of the on-orbit actual output current of the reference shunt stage at the current time, the corresponding solar panel angle and the panel temperature are obtained; S3, the output power prediction model is inputted according to the solar panel angle of the working point, the panel temperature, the ground predicted current at the current time and the calculated day-earth factor, so as to obtain the first ground predicted current of the reference shunt stage at the current time; S4, the current prediction deviation coefficient of the reference shunt stage at the current time is calculated according to the on-orbit actual output current and the first ground predicted current; S5, steps S2-S4 are repeated at a preset time interval, the current prediction deviation coefficients corresponding to continuous n different times are obtained, and the average value is calculated to obtain the average current prediction deviation coefficient of the reference shunt stage; S6, the second ground predicted current of all shunt stages including the reference shunt stage at the to-be-predicted time is obtained through the output power prediction model, and the average current prediction deviation coefficient is corrected to obtain the predicted current of each shunt stage after correction; S7, the predicted total current of the solar array is calculated by summing the predicted current of each shunt stage after correction; S8, the predicted total power of the solar array is calculated based on the predicted total current of the solar array.
2. The all-electric push satellite solar array power prediction method according to claim 1, characterized in that, The selection rule of the reference shunt stage is that the target shunt stage is in a power supply state, and all solar cell sub-arrays on the whole panel corresponding to the target shunt stage are in a power supply state.
3. The all-electric push satellite solar array power prediction method according to claim 1, wherein, The current prediction deviation coefficient is the ratio of the on-orbit actual output current of the reference shunt stage to the first ground predicted current.
4. The all-electric push satellite solar array power prediction method according to claim 1, wherein, The average current prediction deviation coefficient is the average value of the current prediction deviation coefficients corresponding to continuous n different times.
5. The all-electric push satellite solar array power prediction method according to claim 1, wherein, The selection rule of the time interval is that when the satellite is in the inner Van Allen radiation belt range, the single orbit period is taken as the interval; when the satellite is outside the inner Van Allen radiation belt range, the day is taken as the period.
6. The all-electric push satellite solar array power prediction method according to claim 1, wherein, The predicted current after correction is the product of the second ground predicted current and the average current prediction deviation coefficient.
7. The all-electric push satellite solar array power prediction method according to claim 1, wherein, The ground test data is AM0 light exposure test data.
8. An all-electric propulsion satellite solar array power prediction system, characterized by, The system is used to implement the method according to any one of claims 1-7, and the system comprises: a model establishment module, configured to establish an output power prediction model based on the ground test data of the solar array during the satellite development stage; a data acquisition module, configured to select a reference shunt stage whose corresponding sub-arrays are all in a power supply state when in orbit, and to acquire the on-orbit actual output current, the panel angle and the panel temperature telemetry data thereof; a deviation calculation module, configured to calculate a ground predicted current based on the output power prediction model, and to calculate a current prediction deviation coefficient and an average value thereof according to the on-orbit actual output current; a correction prediction module configured to correct the predicted current at the predicted moment output by the output power prediction model using the average current prediction deviation coefficient; a total power prediction module configured to calculate the total predicted output power of the solar cell array based on the corrected predicted current of each partial flow stage and the bus voltage.
9. A computer device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, The processor implements the method of any one of claims 1-7 when executing the program.
10. A computer-readable storage medium having stored thereon a computer program, characterized in that, The program is executed by the processor to implement the method of any one of claims 1-7. The program is executed by the processor to implement the method of any one of claims 1-7.