Satellite sailboard offset angle optimizing method, device and equipment and storage medium

Abstract

The invention discloses a satellite panel offset angle optimization method, device and equipment and a storage medium, and the method comprises the steps: obtaining a satellite orbit parameter, and calculating an orbit incident angle and illumination duration according to the satellite orbit parameter; calculating an illumination quantity parameter for judging an optimal illumination condition according to the orbit incidence angle and the illumination duration; and determining a sailboard offset angle corresponding to the optimal illumination condition according to the illumination quantity parameter. By comprehensively considering various illumination quantity parameters, the satellite sailboard is controlled to incline along the optimal sailboard offset angle, so that the optimal illumination condition is realized, and the stability of satellite operation is ensured.

Description

Technical Field

[0001] This application relates to the field of space engineering, and in particular to a method, apparatus, device and storage medium for optimizing the offset angle of a satellite solar panel. Background Technology

[0002] Currently, solar energy is the sole energy source for most spacecraft and satellite-related equipment. In these systems, the power controller obtains energy from the solar array and controls it to generate a stable bus voltage, meeting the power needs of various devices within the satellite. Under long-term satellite operation conditions, optimizing on-orbit solar energy through a solar panel drive strategy is an effective method; this involves adjusting the satellite's solar panel offset angle to optimize on-orbit illumination conditions.

[0003] Therefore, it is necessary to provide improved technical solutions to overcome the above-mentioned technical problems existing in the prior art. Summary of the Invention

[0004] The purpose of this application is to provide a method, apparatus, device and storage medium for optimizing the offset angle of a satellite solar panel. By comprehensively considering various illumination parameters, the method controls the satellite solar panel to tilt along the optimal offset angle to achieve optimal illumination conditions and ensure the stability of satellite operation.

[0005] To achieve the above objectives: In a first aspect, embodiments of this application provide a method for optimizing the offset angle of a satellite solar panel, including: Obtain satellite orbit parameters, and calculate orbital incident angle and illumination duration based on the satellite orbit parameters; Based on the orbital incident angle and illumination duration, calculate the illumination parameters used to determine the optimal illumination conditions; The optimal illumination condition corresponding to the sail offset angle is determined based on the illumination parameters.

[0006] In one embodiment, calculating the orbital incident angle and illumination duration based on the satellite orbital parameters includes: The orbital incident angle and illumination duration are obtained through simulation calculation, and the data of the orbital incident angle and illumination duration are sampled at a preset duration.

[0007] In one embodiment, before calculating the illuminance parameters used to determine optimal lighting conditions, the method further includes: Based on the orbital incident angle, calculate the orbital illumination angle under different sail offset angles.

[0008] In one embodiment, the calculation of the orbital illumination angle under different sail offset angles includes: Based on the preset satellite solar panel information, the functional relationship between the orbital illumination angle, the orbital incident angle, and the solar panel offset angle is determined.

[0009] In one embodiment, the calculation of the illuminance parameters used to determine optimal lighting conditions includes: Based on the illumination duration and the orbital illumination angle under different sail offset angle conditions, the illumination coefficient under different sail offset angle conditions with a preset sampling period is calculated. Based on the illumination coefficient, the variance and sum of the illumination coefficient under different sail offset angles are calculated respectively, and used as the illumination parameters for determining the optimal illumination conditions.

[0010] In one embodiment, determining the sail offset angle corresponding to the optimal lighting conditions based on the illuminance parameters includes: The sail offset angle corresponding to the minimum variance of the illumination coefficient and the maximum sum is determined as the sail offset angle corresponding to the optimal illumination condition.

[0011] Secondly, embodiments of this application provide a satellite solar panel offset angle optimization device, comprising: The orbital parameter acquisition module is used to acquire satellite orbital parameters and calculate the orbital incident angle and illumination duration based on the satellite orbital parameters. The illuminance parameter calculation module is used to calculate the illuminance parameters for determining the optimal lighting conditions based on the orbital incident angle and the duration of illumination. The offset angle optimization module is used to determine the offset angle of the sail corresponding to the optimal lighting conditions based on the light intensity parameters.

[0012] In one embodiment, the device further includes a one-dimensional drive mechanism for controlling the satellite solar panel to tilt along the solar panel offset angle to achieve optimal lighting conditions.

[0013] Thirdly, embodiments of this application provide an electronic device, including: a memory and a processor, wherein the memory stores executable program code, and when the executable program code is executed by the processor, it implements the steps of the satellite solar panel offset angle optimization method as described in the first aspect.

[0014] Fourthly, embodiments of this application provide a readable storage medium, characterized in that the readable storage medium stores a computer program, which, when executed by a processor, implements the steps of the satellite solar panel offset angle optimization method as described in the first aspect.

[0015] This application provides a method, apparatus, device, and storage medium for optimizing the satellite solar panel offset angle. The method includes: acquiring satellite orbital parameters and calculating the orbital incident angle and illumination duration based on the satellite orbital parameters; calculating illumination parameters for determining optimal illumination conditions based on the orbital incident angle and illumination duration; and determining the solar panel offset angle corresponding to the optimal illumination conditions based on the illumination parameters. This application comprehensively considers multiple illumination parameters to control the satellite solar panel to tilt along the optimal solar panel offset angle, thereby achieving optimal illumination conditions and ensuring the stability of satellite operation. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a flowchart illustrating the satellite solar panel offset angle optimization method provided in an embodiment of the present invention. Figure 2 This is a schematic diagram of the satellite solar panel offset angle optimization device provided in an embodiment of the present invention; Figure 3 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention. Detailed Implementation

[0018] Exemplary embodiments will now be described in detail, examples of which are illustrated in the accompanying drawings. When the following description relates to the drawings, unless otherwise indicated, the same numbers in different drawings denote the same or similar elements. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with this application. Rather, they are merely examples of apparatuses and methods consistent with some aspects of this application as detailed in the appended claims.

[0019] 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, components, features, and elements with the same names in different embodiments of this application may have the same meaning or different meanings, the specific meaning of which must be determined by its interpretation in that specific embodiment or further in conjunction with the context of that specific embodiment.

[0020] It should be understood that although the terms first, second, third, etc., may be used herein to describe various information, such information should not be limited to these terms. These terms are used only to distinguish information of the same type from one another. For example, without departing from the scope of this document, first information may also be referred to as second information, and similarly, second information may also be referred to as first information. Depending on the context, the word "if," as used herein, can be interpreted as "when," "when," or "in response to determination." Furthermore, as used herein, the singular forms "a," "an," and "the" are intended to also include the plural forms unless the context indicates otherwise. It should be further understood that the terms "comprising," "including," indicate the presence of the stated feature, step, operation, element, component, item, kind, and / or group, but do not exclude the presence, occurrence, or addition of one or more other features, steps, operations, elements, components, items, kinds, and / or groups. The terms "or" and "and / or" as used herein are to be interpreted as inclusive, or mean any one or any combination thereof. Therefore, "A, B, or C" or "A, B, and / or C" means "any one of the following: A; B; C; A and B; A and C; B and C; A, B, and C". Exceptions to this definition will only occur if the combination of elements, functions, steps, or operations is inherently mutually exclusive in some way.

[0021] It should be understood that although the steps in the flowcharts of this application's embodiments are shown sequentially according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless explicitly stated herein, there is no strict order restriction on the execution of these steps, and they can be executed in other orders. Moreover, at least some of the steps in the figures may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily completed at the same time, but can be executed at different times, and their execution order is not necessarily sequential, but can be performed alternately or in turn with other steps or at least a portion of the sub-steps or stages of other steps.

[0022] It should be noted that step designations such as S101 and S102 are used in this document for the purpose of more clearly and concisely describing the corresponding content, and do not constitute a substantial limitation on the order. In specific implementation, those skilled in the art may execute S102 first and then S101, etc., but these should all be within the protection scope of this application.

[0023] It should be understood that the specific embodiments described herein are merely illustrative of this application and are not intended to limit this application.

[0024] In the following description, the use of suffixes such as "module," "part," or "unit" to denote elements is solely for the purpose of illustrative purposes and has no specific meaning in itself. Therefore, "module," "part," or "unit" may be used interchangeably.

[0025] First Embodiment See Figure 1 This application provides a method for optimizing the offset angle of a satellite solar panel. This method can be executed by a satellite solar panel offset angle optimization device provided in this application. This device can be implemented using software and / or hardware. In this embodiment, the satellite solar panel offset angle optimization device is taken as the executing entity of the method. The satellite solar panel offset angle optimization method provided in this embodiment includes the following steps: Step S110: Obtain satellite orbit parameters and calculate orbital incident angle and illumination duration based on satellite orbit parameters.

[0026] It is understandable that the orbital incident angle changes periodically every day, and the duration of illumination is determined by the number of satellite orbital parameters. When the satellite orbital parameters are determined, the duration of illumination for each orbit varies periodically with the satellite's position in the orbit.

[0027] In one embodiment, calculating the orbital incident angle and illumination duration based on the satellite orbital parameters includes: The orbital incident angle and illumination duration are obtained through simulation calculation, and data of the orbital incident angle and illumination duration are sampled at a preset duration.

[0028] It is understandable that satellite orbital parameters are input into simulation software to calculate the orbital incidence angle and illumination duration over a certain time range. For example, the Satellite Tool Kit (STK) software can be used to simulate and calculate the orbital incidence angle and illumination duration. Since the orbital incidence angle and illumination duration vary relatively little within a day, data sampling can be performed on a daily basis. It is worth noting that this minimum unit interval can be adjusted as needed; for more precise analysis, smaller intervals can be used.

[0029] Step S120: Calculate the illuminance parameters used to determine the optimal lighting conditions based on the orbital incident angle and illumination duration.

[0030] It is understandable that the most significant factor affecting the efficiency of solar cells in acquiring solar energy is the illumination conditions. These conditions are related to the energy generated per unit area under direct sunlight in space, the photoelectric conversion efficiency of the solar cells, the area of ​​the solar panels, the solar panel coverage rate, the orbital illumination angle, and the duration of illumination. Given that the energy generated per unit area under direct sunlight in space, the photoelectric conversion efficiency of the solar cells, the solar panel area, and the solar panel coverage rate are fixed, determining the most suitable orbital illumination angle and duration of illumination is crucial. Furthermore, the orbital incident angle is directly related to the orbital illumination angle.

[0031] In one embodiment, before calculating the illuminance parameter used to determine the optimal lighting conditions, the method further includes: Calculate the orbital illumination angle under different sail offset angles based on the orbital incident angle.

[0032] It can be understood that the orbital illumination angle is the angle between sunlight and the surface of the solar panel. This angle is directly related to the actual energy received by the solar panel. Therefore, determining a suitable orbital illumination angle directly affects the lighting conditions.

[0033] In one embodiment, calculating the orbital illumination angle under different sail offset angles includes: Based on the preset satellite solar panel information, the functional relationship between the orbital illumination angle, the orbital incident angle, and the solar panel offset angle is determined.

[0034] It is understandable that the orbital illumination angle is directly related to the orbital incident angle (i.e., the angle between sunlight and the orbital plane) and the solar panel offset angle (i.e., the offset angle of the solar panel relative to the satellite body). For example, taking a low Earth orbit inclined circular orbit as an example, the functional relationship between the orbital illumination angle, the orbital incident angle, and the solar panel offset angle is α = 90 - β + θ, where α is the orbital illumination angle, β is the orbital incident angle, and θ is the solar panel offset angle.

[0035] In one embodiment, calculating the illuminance parameter used to determine optimal lighting conditions includes: Based on the duration of illumination and the orbital illumination angle under different sail offset angles, the illumination coefficient under different sail offset angles with a preset sampling period is calculated. Based on the illumination coefficient, the variance and sum of the illumination coefficient under different sail offset angles are calculated respectively, which are used as the illumination parameters for determining the optimal illumination conditions.

[0036] For example, with 1° intervals for the sail offset angle, the illuminance coefficients f1, f2...fn (n is 365) are iterated over a year under different sail offset angles from 0 to 90°. The formula for calculating the illuminance coefficient on day i is as follows:

[0037] Where fi is the illumination coefficient on day i, Ti is the illumination duration on day i, and αi is the orbital illumination angle on day i.

[0038] Furthermore, the formulas for calculating the variance of the illumination coefficient and the cumulative sum are as follows:

[0039]

[0040] in, Let μ be the variance of the illumination coefficient, and μ be the mean. The summation is calculated as follows:

[0041] Step S130: Determine the offset angle of the sailboard corresponding to the optimal lighting conditions based on the illuminance parameters.

[0042] It is understandable that by comprehensively considering the solar panel illumination and its variance, the goal is to reduce the fluctuation of the illumination energy intake value per orbit while ensuring a large total illumination energy intake. This allows the satellite to obtain more stable energy, which is more conducive to the stable operation of the payload per orbit.

[0043] In one embodiment, determining the sail offset angle corresponding to the optimal lighting conditions based on illuminance parameters includes: The optimal sail offset angle is determined by identifying the values ​​that minimize the variance of the illumination coefficient and maximize its sum.

[0044] It is understandable that when the variance of the illumination coefficient is small, it means that the daily illumination conditions are relatively stable; when the cumulative sum of the illumination coefficients is large, it means that the total energy received by the windsurfing system is high throughout the entire cycle, and the energy utilization rate is high.

[0045] In summary, the implementation method of this application, by comprehensively considering the solar panel illumination and the variance of solar panel illumination, controls the satellite solar panel to tilt along the optimal solar panel offset angle, so as to reduce the fluctuation of the solar panel illumination intake value per orbit under the premise of a large total solar panel illumination intake, so that the satellite can obtain more stable energy and is more conducive to the stable operation of the payload per orbit.

[0046] Second Embodiment Based on the first embodiment of this application, a satellite solar panel offset angle optimization device is provided in this embodiment, see reference. Figure 2 The device includes: The orbit parameter acquisition module 21 is used to acquire satellite orbit parameters and calculate the orbital incident angle and illumination duration based on the satellite orbit parameters; The illumination parameter calculation module 22 is used to calculate the illumination parameters for determining the optimal illumination conditions based on the orbital incident angle and illumination duration. The offset angle optimization module 23 is used to determine the offset angle of the sail corresponding to the optimal lighting conditions based on the illuminance parameters.

[0047] In one embodiment, a one-dimensional drive mechanism is also included for controlling the satellite solar panel to tilt along the solar panel offset angle to achieve optimal lighting conditions.

[0048] It is understandable that satellites that need to perform long-term Earth-oriented operations, and which are one-dimensional driven solar panels, can optimize lighting conditions by tilting at an offset angle along a single directional axis, under the constraints of cost and configuration.

[0049] In one embodiment, the orbital parameter acquisition module 21 is further configured to: The orbital incident angle and illumination duration are obtained through simulation calculation, and data of the orbital incident angle and illumination duration are sampled at a preset duration.

[0050] In one embodiment, the illuminance parameter calculation module 22 is further configured to: Calculate the orbital illumination angle under different sail offset angles based on the orbital incident angle.

[0051] In one embodiment, the illuminance parameter calculation module 22 is further configured to: Based on the preset satellite solar panel information, the functional relationship between the orbital illumination angle, the orbital incident angle, and the solar panel offset angle is determined.

[0052] In one embodiment, the illuminance parameter calculation module 22 is further configured to: Based on the duration of illumination and the orbital illumination angle under different sail offset angles, the illumination coefficient under different sail offset angles with a preset sampling period is calculated. Based on the illumination coefficient, the variance and sum of the illumination coefficient under different sail offset angles are calculated respectively, which are used as the illumination parameters for determining the optimal illumination conditions.

[0053] In one embodiment, the offset angle optimization module 23 is further configured to: The optimal sail offset angle is determined by identifying the values ​​that minimize the variance of the illumination coefficient and maximize its sum.

[0054] It should be noted that the description of the satellite solar panel offset angle optimization device is similar to the description of the satellite solar panel offset angle optimization method, and the beneficial effects of the same method will not be repeated. For technical details not disclosed in the embodiments of the satellite solar panel offset angle optimization device of this invention, please refer to the description of the embodiments of the satellite solar panel offset angle optimization method of this invention.

[0055] Third Embodiment Based on the same inventive concept as the foregoing embodiments, this application provides an electronic device, such as... Figure 3 As shown, the device includes: a processor 301 and a memory 302 storing a computer program; wherein, Figure 3 The processor 301 shown in the diagram does not indicate that there is only one processor 301, but only indicates the positional relationship of processor 301 relative to other devices. In practical applications, there can be one or more processors 301; similarly, Figure 3 The memory 302 shown in the diagram has the same meaning, that is, it is only used to indicate the positional relationship of memory 302 relative to other devices. In practical applications, there can be one or more memories 302. When the processor 301 runs the computer program, it implements the satellite solar panel offset angle optimization method described above.

[0056] The device may also include at least one network interface 303. The various components of the device are coupled together via a bus system 304. It is understood that the bus system 304 is used to implement communication between these components. In addition to a data bus, the bus system 304 also includes a power bus, a control bus, and a status signal bus. However, for clarity, in... Figure 3 The general designated all buses as Bus System 304.

[0057] The memory 302 can be volatile memory or non-volatile memory, or both. Non-volatile memory can be read-only memory (ROM), programmable read-only memory (PROM), erasable programmable read-only memory (EPROM), electrically erasable programmable read-only memory (EEPROM), ferromagnetic random access memory (FRAM), flash memory, magnetic surface memory, optical disc, or compact disc read-only memory (CD-ROM); magnetic surface memory can be disk storage or magnetic tape storage. Volatile memory can be random access memory (RAM), used as an external cache. By way of example, but not limitation, many forms of RAM are available, such as Static Random Access Memory (SRAM), Synchronous Static Random Access Memory (SSRAM), Dynamic Random Access Memory (DRAM), Synchronous Dynamic Random Access Memory (SDRAM), Double Data Rate Synchronous Dynamic Random Access Memory (DDRSDRAM), Enhanced Synchronous Dynamic Random Access Memory (ESDRAM), SyncLink Dynamic Random Access Memory (SLDRAM), and Direct Rambus Random Access Memory (DRRAM).The memory 302 described in the embodiments of this application is intended to include, but is not limited to, these and any other suitable types of memory.

[0058] Fourth embodiment Based on the same inventive concept as the foregoing embodiments, this embodiment also provides a computer-readable storage medium storing a computer program. The computer-readable storage medium can be a magnetic random access memory (FRAM), a read-only memory (ROM), a programmable read-only memory (PROM), an erasable programmable read-only memory (EPROM), an electrically erasable programmable read-only memory (EEPROM), a flash memory, a magnetic surface memory, an optical disc, or a compact disc read-only memory (CD-ROM), etc.; it can also be various devices including one or any combination of the above-mentioned memories, such as mobile phones, computers, tablet devices, personal digital assistants, etc. When the computer program stored in the computer-readable storage medium is executed by a processor, it implements the above-described charging current adjustment method. For the specific steps implemented when the computer program is executed by the processor, please refer to [link to relevant documentation]. Figure 2 The description of the illustrated embodiments will not be repeated here.

[0059] In this application, the same or similar terms, concepts, technical solutions and / or application scenario descriptions are generally described in detail only when they appear for the first time. When they appear again, they are generally not repeated for the sake of brevity. When understanding the technical solutions and other contents of this application, the same or similar terms, concepts, technical solutions and / or application scenario descriptions that are not described in detail later can be referred to their previous relevant detailed descriptions.

[0060] In this application, the descriptions of the various embodiments have different focuses. For parts that are not described in detail or recorded in a certain embodiment, please refer to the relevant descriptions of other embodiments.

[0061] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0062] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A method for optimizing the offset angle of a satellite solar panel, characterized in that, The method includes: Obtain satellite orbit parameters, and calculate orbital incident angle and illumination duration based on the satellite orbit parameters; Based on the orbital incident angle and illumination duration, calculate the illumination parameters used to determine the optimal illumination conditions; The optimal illumination condition corresponding to the sail offset angle is determined based on the illumination parameters.

2. The method as described in claim 1, characterized in that, The calculation of the orbital incident angle and illumination duration based on the satellite orbital parameters includes: The orbital incident angle and illumination duration are obtained through simulation calculation, and the data of the orbital incident angle and illumination duration are sampled at a preset duration.

3. The method as described in claim 2, characterized in that, Before calculating the illuminance parameters used to determine optimal lighting conditions, the method further includes: Based on the orbital incident angle, calculate the orbital illumination angle under different sail offset angles.

4. The method as described in claim 2, characterized in that, The calculation of the orbital illumination angle under different sail offset angles includes: Based on the preset satellite solar panel information, the functional relationship between the orbital illumination angle, the orbital incident angle, and the solar panel offset angle is determined.

5. The method as described in claim 3, characterized in that, The calculation of the illuminance parameters used to determine optimal lighting conditions includes: Based on the illumination duration and the orbital illumination angle under different sail offset angle conditions, the illumination coefficient under different sail offset angle conditions with a preset sampling period is calculated. Based on the illumination coefficient, the variance and sum of the illumination coefficient under different sail offset angles are calculated respectively, and used as the illumination parameters for determining the optimal illumination conditions.

6. The method as described in claim 4, characterized in that, The step of determining the optimal sail offset angle corresponding to the light conditions based on the light intensity parameters includes: The sail offset angle corresponding to the minimum variance of the illumination coefficient and the maximum sum is determined as the sail offset angle corresponding to the optimal illumination condition.

7. A satellite solar panel offset angle optimization device, characterized in that, include: The orbital parameter acquisition module is used to acquire satellite orbital parameters and calculate the orbital incident angle and illumination duration based on the satellite orbital parameters. The illuminance parameter calculation module is used to calculate the illuminance parameters for determining the optimal lighting conditions based on the orbital incident angle and the duration of illumination. The offset angle optimization module is used to determine the offset angle of the sail corresponding to the optimal lighting conditions based on the light intensity parameters.

8. The apparatus as claimed in claim 7, characterized in that, The device also includes a one-dimensional drive mechanism for controlling the satellite solar panel to tilt along the solar panel offset angle to achieve optimal lighting conditions.

9. An electronic device, characterized in that, The electronic device includes a memory and a processor, wherein the memory stores executable program code, and when the executable program code is executed by the processor, it implements the steps of the satellite solar panel offset angle optimization method as described in any one of claims 1 to 6.

10. A readable storage medium, characterized in that, The readable storage medium stores a computer program that, when executed by a processor, implements the steps of the satellite solar panel offset angle optimization method as described in any one of claims 1 to 6.

Images