Method, device and equipment for determining swing angle of solar panel based on illumination quantity of solar panel

Abstract

The invention provides a solar panel tilt angle determination method, device and equipment based on solar panel illumination quantity. The method comprises the following steps: acquiring an orbital angle sequence and a solar panel tilt angle range corresponding to a solar panel of a satellite; for any target orbital angle in the orbital angle sequence, an initial sailboard swing angle value under the target orbital angle is determined, a target function is called in an optimizer, the maximum solar sailboard illumination quantity output by the target function for the sailboard swing angle value is taken as a target, the sailboard swing angle range is taken as a constraint, the sailboard swing angle value is subjected to iterative adjustment, and the optimal sailboard swing angle value is obtained. The optimal sailboard swing angle value under the target orbit angle is obtained; wherein the illumination quantity of the solar panel is the average value of the effective illumination quantity of the sun acting on the solar panel of the satellite in an orbital period of the satellite. The method has the characteristics of high precision, small calculation amount, high calculation speed and the like.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a method, apparatus, and equipment for determining the swing angle of a solar panel based on the amount of sunlight emitted by the solar panel. Background Technology

[0002] In satellite design and application, the amount of sunlight received by a satellite's solar panels directly affects its charging capability. The evaluation of a satellite's on-orbit charging capability and the optimization of its on-orbit solar panel rotation / tilt angles are of great concern to satellite developers and users. Generally, in the design process of satellites in sun-synchronous orbits, the amount of sunlight received by the satellite's solar panels is determined by the panel installation and the orbital parameters. The angle (the complementary angle between the solar vector and the orbital plane normal vector) is directly evaluated without simulation calculations. However, for non-sunsynchronous orbits, simple evaluation cannot meet the requirements of refined design. Instead, it is necessary to evaluate the cumulative solar radiation capacity at all locations for each orbit. The traditional approach is based on a given... The average illumination is calculated by successively simulating and averaging the cosine values ​​of the solar illumination angle (the angle between the solar direction vector and the solar panel normal vector) at all non-shadow positions of the satellite in its orbit. However, this method has two drawbacks: first, it requires extensive calls to the above-mentioned average illumination calculation process when designing the solar panel rotation / swing angle, resulting in a long design process; second, the trade-off between the accuracy of the average illumination calculation and the computation time is difficult to avoid. Therefore, in traditional methods, a compromise is generally adopted, which is to set a solar panel rotation / swing angle according to a simple rule, for example, setting it to equal... ( (The opposite of the angle). Therefore, traditional methods, due to insufficient design capabilities, cannot maximize the utilization of platform capabilities. Summary of the Invention

[0003] In view of this, the purpose of the present invention is to provide a method, device and equipment for determining the swing angle of a solar panel based on the amount of sunlight emitted by the solar panel, which has the characteristics of high accuracy, small amount of calculation and fast calculation speed.

[0004] In a first aspect, the present invention provides a method for determining the swing angle of a solar panel based on the amount of sunlight emitted by the solar panel, comprising: Obtain the track Angular sequence and the range of solar panel swing angles corresponding to the satellite's solar panels; For orbit Any target orbit in the angular sequence Angle, determine the target trajectory The initial solar panel yaw angle value is used as the starting point. The optimizer calls an objective function to maximize the solar radiation output for each yaw angle value. The yaw angle value is iteratively adjusted within the given range of yaw angles to obtain the target trajectory. The optimal windshield swing angle value under the angle; Among them, solar panel illumination is the average effective amount of sunlight acting on the satellite's solar panels during one orbital period.

[0005] In one implementation, an objective function is called in the optimizer, with the goal of maximizing the solar irradiance output by the objective function for the solar panel yaw angle value. The yaw angle value is iteratively adjusted using the range of the solar panel yaw angle as a constraint to obtain the target trajectory. The optimal windshield angle values ​​under the angle include: Perform the following operations in the optimizer: Call the target function; Based on the objective function and the target trajectory The solar panel illumination corresponding to the solar panel irradiance is determined by the angle, the solar panel swing angle value, and the corresponding semi-major axis of the satellite orbit. If the solar panel irradiance does not meet the preset conditions, the solar panel swing angle value is adjusted based on the swing angle range, and the objective function is called again until the solar panel irradiance meets the preset conditions. The solar panel yaw angle corresponding to the minimum solar panel illumination is taken as the target orbit. The optimal windshield swing angle value under the angle.

[0006] In one implementation, the objective function is used, based on the target trajectory. The solar panel illumination corresponding to the solar panel irradiance is determined by the angle, the solar panel sway angle, and the semi-major axis of the satellite's orbit, including: Based on the target orbit The effective illumination duration is determined by the angle, the solar panel swing angle, and the corresponding semi-major axis of the satellite's orbit. Based on the target orbit The evaluation value is determined by the angle, solar panel swing angle, effective illumination duration, and the corresponding orbital period of the satellite. The negative of the evaluation value is taken as the solar panel illumination corresponding to the solar panel swing angle.

[0007] In one implementation, based on the target orbit The effective illumination duration is determined by the angle, the solar panel swing angle, and the semi-major axis of the satellite's corresponding preset orbit, including: Based on the target orbit The angle and the preset orbital semi-major axis determine the first type of illumination duration, which is: the total time that the satellite can receive sunlight within one orbital period, taking into account the Earth's shading factor; Based on the target orbit The angle and the solar panel swing angle determine the second type of illumination duration. The second type of illumination duration is: the total time that the solar panel's light-receiving surface can receive sunlight within one orbital period, ignoring the Earth's shading factor and considering the solar panel's own attitude factor. The minimum of the first type of illumination duration and the second type of illumination duration is taken as the effective illumination duration.

[0008] In one implementation, based on the target orbit The evaluation values ​​are determined by the angle, solar panel swing angle, effective illumination duration, and the satellite's corresponding orbital period, including: The assessment value is determined using the following formula: ; in, For evaluation purposes, This is the windsurfing angle value. For the target orbit horn, For effective illumination duration, For orbital period.

[0009] In one implementation, the windshield yaw angle range is divided into a left windshield yaw angle range and a right windshield yaw angle range, and the windshield yaw angle value is divided into a left windshield yaw angle value and a right windshield yaw angle value.

[0010] In one implementation, the method further includes: For orbit Any target orbit in the angular sequence Angle, determine the target trajectory The sum of the solar panel irradiance corresponding to the optimal left and right solar panel sway angles at each angle. Based on track Each orbital in the angular sequence The total illuminance value corresponding to the angle, the total illuminance value generated varies with the orbit. Distribution diagram of angular variation.

[0011] Secondly, the present invention also provides a device for determining the swing angle of a solar panel based on the amount of sunlight emitted by the solar panel, comprising: The data acquisition module is used to acquire the track. Angular sequence and the range of solar panel swing angles corresponding to the satellite's solar panels; The swing angle iterative optimization module is used for the orbit... Any target orbit in the angular sequence Angle, determine the target trajectory The initial solar panel yaw angle value is used as the starting point. The optimizer calls an objective function to maximize the solar radiation output for each yaw angle value. The yaw angle value is iteratively adjusted within the given range of yaw angles to obtain the target trajectory. The optimal windshield swing angle value under the angle; Among them, solar panel illumination is the average effective amount of sunlight acting on the satellite's solar panels during one orbital period.

[0012] Thirdly, the present invention also provides an electronic device including a processor and a memory, the memory storing computer-executable instructions executable by the processor, the processor executing the computer-executable instructions to implement any of the methods provided in the first aspect.

[0013] Fourthly, the present invention also provides a computer-readable storage medium storing computer-executable instructions, which, when invoked and executed by a processor, cause the processor to implement any of the methods provided in the first aspect.

[0014] This invention provides a method, apparatus, and device for determining the swing angle of a solar panel based on solar panel illumination, and for acquiring track information. The angle sequence and the range of solar panel swing angles corresponding to the satellite's solar panels, for the orbit. Any target orbit in the angular sequence Angle, determine the target trajectory The initial solar panel yaw angle value is used as the starting point. The optimizer calls an objective function to maximize the solar radiation output for each yaw angle value. The yaw angle value is iteratively adjusted within the given range of yaw angles to obtain the target trajectory. The optimal solar panel tilt angle is determined at the specified angle; where solar panel illumination is the average effective irradiance received by the sun on the satellite's solar panels during one orbital period. This method introduces the novel concept of solar panel illumination and provides the optimal solar panel illumination for any orbit. The method of iteratively optimizing the angle of the solar panel under the angle of the angle has higher calculation accuracy than traditional techniques, enabling the optimal solar panel angle to achieve better charging capability. It also has advantages such as low computational load and fast calculation speed, making it well applicable to the spaceborne operating environment and having engineering practical value.

[0015] Other features and advantages of the present invention will be described in the following description, and in part will become apparent from the description, or understood by practicing the present invention. The purposes and other advantages of the present invention are realized and obtained by the structures particularly pointed out in the description, claims and drawings.

[0016] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings. Attached Figure Description

[0017] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0018] Figure 1 A flowchart illustrating a method for determining the swing angle of a solar panel based on solar panel illumination, provided in an embodiment of the present invention; Figure 2 This is a technical framework diagram of a method for determining the swing angle of a solar panel based on solar panel illumination, provided in an embodiment of the present invention. Figure 3 An embodiment of the present invention provides a total illuminance value that varies with the orbit. Example of a distribution diagram for angular variation; Figure 4 This is a schematic diagram of a device for determining the swing angle of a solar panel based on the amount of sunlight emitted by the solar panel, provided in an embodiment of the present invention. Figure 5 A schematic structural diagram of an electronic device provided by an embodiment of the present invention. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0020] Currently, existing technologies have the following drawbacks: First, the design of solar panel rotation / swing angle requires extensive use of the aforementioned average illuminance calculation process, resulting in a long design time; second, the trade-off between the accuracy of average illuminance calculation and the computation time is difficult to avoid. Based on this, the present invention implements a problem model based on a one-dimensional SADA (Solar Panel Drive Device) satellite model (the solar panel only swings around the ±X axis of the orbital system), and provides a method, device, and equipment for determining the solar panel swing angle based on solar panel illuminance, which has the characteristics of high accuracy, small computational load, and fast calculation speed.

[0021] To facilitate understanding of this embodiment, a method for determining the swing angle of a solar panel based on solar panel illumination, as disclosed in this embodiment of the invention, will first be described in detail. (See [link to relevant documentation]). Figure 1 The diagram shows a method for determining the swing angle of a solar panel based on solar panel illumination. This method mainly includes the following steps S102 to S104: Step S102, Obtain the track The angle sequence and the range of solar panel swing angles corresponding to the satellite's solar panels.

[0022] Among them, the orbit Angular sequences include multiple orbitals Angle, track The angle is the complementary angle between the solar vector and the orbital plane normal vector; the satellite is equipped with a left solar panel and a right solar panel, and based on this, the swing angle range of the panels is divided into the left panel half-angle range and the right panel swing angle range.

[0023] Step S104, for the track Any target orbit in the angular sequence Angle, determine the target trajectory The initial solar panel yaw angle value is used as the starting point. The optimizer calls an objective function to maximize the solar radiation output for each yaw angle value. The yaw angle value is iteratively adjusted within the given range of yaw angles to obtain the target trajectory. The optimal windshield swing angle value under the angle.

[0024] The solar panel yaw angle is divided into the left solar panel yaw angle and the right solar panel yaw angle. Solar panel illumination is the average effective amount of sunlight acting on the satellite's solar panels during one orbital period. Specifically, the definition of solar panel illumination is as follows:

[0025] In the formula, The angle of illumination, representing the angle between the solar vector and the solar panel normal vector, is a time-dependent angle. A function of . P is the orbital period, a constant. The orbital angular velocity is expressed in rad / sec. This represents the angle of the solar panel in the orbital frame, in rad. For orbit Angle, measured in rad; The effective illumination duration for each track is , The function.

[0026] In one implementation, the tracks can be sequentially arranged. orbits in angular sequence Angle, as the target orbit Angle, the target trajectory is determined in the optimizer. The initial left and right windshield angles are set at the target angle, and the objective function is applied to the target trajectory. The objective is to maximize the solar panel illumination output by the left side solar panel swing angle value. This objective trajectory is obtained iteratively, with the left side solar panel swing angle range as a constraint. The optimal left sail swing angle value under the angle; similarly, the objective function for this target trajectory. The objective is to maximize the solar panel illumination output by the right-side solar panel swing angle value. This objective trajectory is obtained iteratively, with the right-side solar panel swing angle range as a constraint. Find the optimal right-side sail swing angle under the angle. Repeat the above process until the track is obtained. All orbits within the angular sequence The optimal left and right windshield angles are determined by the angle.

[0027] The method for determining the swing angle of a solar panel based on solar panel irradiance provided in this invention proposes a new concept of solar panel irradiance and provides a method for determining the swing angle of an arbitrary orbit based on solar panel irradiance. The method of iteratively optimizing the angle of the solar panel under the angle of the angle has higher calculation accuracy than traditional techniques, enabling the optimal solar panel angle to achieve better charging capability. It also has advantages such as low computational load and fast calculation speed, making it well applicable to the spaceborne operating environment and having engineering practical value.

[0028] In one implementation, see Figure 2 The diagram shows a technical framework for a method to determine the swing angle of a solar panel based on solar panel illumination, including: for any orbit Angle, set the corresponding swing angle within the optimizer. The initial value (i.e., the initial solar panel angle) is used to call the objective function to output the solar panel illumination based on the solar panel angle value. Determine the assessment value In the evaluation value Update the swing angle without convergence In the evaluation value Output the minimum evaluation value if convergence is achieved. Corresponding swing angle .

[0029] To facilitate understanding, this invention provides a specific implementation of a method for determining the swing angle of a solar panel based on solar panel illumination, including: Step 1: Parameter Settings: Set the upper and lower limits of the left windsurfing angle range, and set the upper and lower limits of the right windsurfing angle. These are denoted as follows: , .

[0030] Step 2: For the track Any target orbit in the angular sequence Angle, determine the target trajectory The initial solar panel yaw angle value is used as the starting point. The optimizer calls an objective function to maximize the solar radiation output for each yaw angle value. The yaw angle value is iteratively adjusted within the given range of yaw angles to obtain the target trajectory. The optimal windshield angle under the current angle. For example, the track. In the angular sequence sequentially all orbitals within the sequence The optimal left and right windshield angles are designed.

[0031] The optimizer is implemented using the `fmincon` function provided by the Matrix Labs platform. In one implementation: The optimizer is used to optimize the swing angle of the left solar panel until the objective function outputs the desired value. The minimum. The optimal windshield angle is denoted as... The following information is required to use the optimizer: Table 1. Information required by the optimizer for optimizing the solar panel's swing angle value on the left side.

[0032] The optimizer is used to optimize the swing angle of the right solar panel until the objective function outputs the desired value. The minimum. The optimal windshield angle is denoted as... The following information is required to use the optimizer: Table 2. Information required by the optimizer for optimizing the right-side solar panel's swing angle.

[0033] For each The angle values ​​are obtained in the same way as described above, with the optimal left and right windshield angles recorded as follows: , .

[0034] To facilitate understanding of the process by which the optimizer outputs the optimal solar panel swing angle value, this embodiment of the invention provides a specific implementation method. Taking any solar panel as an example, the following operations can be performed in the optimizer to obtain the optimal solar panel swing angle value for that side: Step 1: Call the target function. The expression for the target function is as follows: Among them, the output For the evaluation value, enter This is the windsurfing angle value. For orbit horn, It is the semi-major axis of the track.

[0035] Step 2, using the objective function, based on the target trajectory Using the angle, solar panel oscillation angle, and the corresponding semi-major axis of the satellite's orbit, determine the solar panel illumination corresponding to the solar panel oscillation angle. Objective function Includes the following sub-steps: Step 2.1, based on the target orbit The effective illumination duration is determined by the angle, the solar panel swing angle, and the corresponding semi-major axis of the satellite's orbit. Specifically, this includes: Based on the target orbit The duration of the first type of illumination is determined by the angle and the semi-major axis of the preset orbit. First type of illumination duration This refers to the total amount of time a satellite can receive sunlight within one orbital period, taking into account Earth's eclipse. In practice, this can be achieved using industry-standard algorithms based on the orbit. Angle and orbital semi-major axis Calculate the shadow duration and illumination duration for each track; this illumination duration is the first type of illumination duration. The embodiments of the present invention will not be described in detail here.

[0036] Based on the target orbit The angle and the swing angle of the sail determine the duration of the second type of illumination. Second type of illumination duration This refers to the total time a satellite's solar panels can receive sunlight over one orbital period, ignoring Earth's eclipse and considering the solar panel's own attitude. Specifically, the duration of this second type of illumination can be determined using the following formula. : ;in, The orbital period can be calculated according to industry standard algorithms, which will not be elaborated further in this embodiment of the invention.

[0037] The minimum value between the first type of illumination duration and the second type of illumination duration is taken as the effective illumination duration. , that is .

[0038] Step 2.2, based on the target orbit The evaluation value is determined by the angle, solar panel swing angle, effective illumination duration, and the corresponding orbital period of the satellite. The negative of the evaluation value is taken as the solar panel illumination corresponding to the solar panel swing angle.

[0039] The assessed value is determined using the following formula. : ; in, For evaluation purposes, This is the windsurfing angle value. For the target orbit horn, For effective illumination duration, For orbital period.

[0040] Determine the solar panel illumination using the following formula. : .

[0041] Step 3: If the solar panel irradiance does not meet the preset conditions, adjust the solar panel swing angle value based on the swing angle range, and continue calling the objective function until the solar panel irradiance meets the preset conditions. The preset conditions can be the evaluation values. Convergence, or near convergence to the optimum, or reaching a specified number of iterations. In one example, the evaluation value is based on preset conditions. For example, if the evaluation value If convergence fails, the current windshield angle value will be constrained by the range of windshield angles. After making adjustments, return to step 1; if the evaluation value If convergence is achieved, proceed to step 4.

[0042] Step 4: Take the solar panel swing angle value corresponding to the minimum solar panel illumination as the target orbit. The optimal windshield swing angle value under the angle.

[0043] Repeat steps 1 through 4 above until the aforementioned trajectory is determined. angle sequence[ All orbits in The optimal left windshield angle value And the optimal right-side windshield angle value .

[0044] Furthermore, regarding the orbit Any target orbit in the angular sequence Angle, determine the target trajectory The sum of the solar panel illumination corresponding to the optimal left and right solar panel yaw angles at each angle, based on the orbit. Each orbital in the angular sequence The total illuminance value corresponding to the angle, the total illuminance value generated varies with the orbit. Distribution diagrams of angular variations, such as Figure 3 The total illuminance value shown varies with the orbit. Example of a distribution chart for angular variation. Figure 3 The "fixed value" shown This is a traditional method for designing the windshield angle of a windsurfing system. It can be seen that, compared to the traditional method of directly determining the windshield angle based on certain principles, the method proposed in this embodiment is based on… The method of using the angle (the complementary angle between the solar vector and the orbital plane normal vector) to perform high-precision optimization design of the solar panel swing angle value maximizes the charging capability of the satellite platform.

[0045] Based on the foregoing embodiments, this invention provides a device for determining the swing angle of a solar panel based on solar panel illumination. (See attached image.) Figure 4 The diagram shows a structural schematic of a device for determining the swing angle of a solar panel based on solar panel illumination. This device mainly includes the following components: Data acquisition module 402 is used to acquire track. Angular sequence and the range of solar panel swing angles corresponding to the satellite's solar panels; The swing angle iterative optimization module 404 is used for the orbit... Any target orbit in the angular sequence Angle, determine the target trajectory The initial solar panel yaw angle value is used as the starting point. The optimizer calls an objective function to maximize the solar radiation output for each yaw angle value. The yaw angle value is iteratively adjusted within the given range of yaw angles to obtain the target trajectory. The optimal windshield swing angle value under the angle; Among them, solar panel illumination is the average effective amount of sunlight acting on the satellite's solar panels during one orbital period.

[0046] The solar panel illuminance determination device provided in this invention proposes a new concept of solar panel illuminance and provides a method for determining the sway angle of an arbitrary orbit based on solar panel illuminance. The method of iteratively optimizing the angle of the solar panel under the angle of the angle has higher calculation accuracy than traditional techniques, enabling the optimal solar panel angle to achieve better charging capability. It also has advantages such as low computational load and fast calculation speed, making it well applicable to the spaceborne operating environment and having engineering practical value.

[0047] In one implementation, the swing angle iteration optimization module 404 is specifically used for: Perform the following operations in the optimizer: Call the target function; Based on the objective function and the target trajectory The solar panel illumination corresponding to the solar panel irradiance is determined by the angle, the solar panel swing angle value, and the corresponding semi-major axis of the satellite orbit. Solar panel illumination not evaluated If convergence fails, adjust the solar panel swing angle value based on the range of the solar panel swing angle, and continue to call the objective function until the solar panel irradiance assessment value is reached. Non-convergence and cessation; The solar panel yaw angle corresponding to the minimum solar panel illumination is taken as the target orbit. The optimal windshield swing angle value under the angle.

[0048] In one implementation, the swing angle iteration optimization module 404 is specifically used for: Based on the target orbit The effective illumination duration is determined by the angle, the solar panel swing angle, and the corresponding semi-major axis of the satellite's orbit. Based on the target orbit The evaluation value is determined by the angle, solar panel swing angle, effective illumination duration, and the corresponding orbital period of the satellite. The negative of the evaluation value is taken as the solar panel illumination corresponding to the solar panel swing angle.

[0049] In one implementation, the swing angle iteration optimization module 404 is specifically used for: Based on the target orbit The angle and the preset orbital semi-major axis determine the first type of illumination duration, which is: the total time that the satellite can receive sunlight within one orbital period, taking into account the Earth's shading factor; Based on the target orbit The angle and the solar panel swing angle determine the second type of illumination duration. The second type of illumination duration is: the total time that the solar panel's light-receiving surface can receive sunlight within one orbital period, ignoring the Earth's shading factor and considering the solar panel's own attitude factor. The minimum of the first type of illumination duration and the second type of illumination duration is taken as the effective illumination duration.

[0050] In one implementation, the swing angle iteration optimization module 404 is specifically used for: The assessment value is determined using the following formula: ; in, For evaluation purposes, This is the windsurfing angle value. For the target orbit horn, For effective illumination duration, For orbital period.

[0051] In one implementation, the windshield yaw angle range is divided into a left windshield yaw angle range and a right windshield yaw angle range, and the windshield yaw angle value is divided into a left windshield yaw angle value and a right windshield yaw angle value.

[0052] In one implementation, a distribution map generation module is further included, for: For orbit Any target orbit in the angular sequence Angle, determine the target trajectory The sum of the solar panel irradiance corresponding to the optimal left and right solar panel sway angles at each angle. Based on track Each orbital in the angular sequence The total illuminance value corresponding to the angle, the total illuminance value generated varies with the orbit. Distribution diagram of angular variation.

[0053] The device provided in this embodiment of the invention has the same implementation principle and technical effect as the aforementioned method embodiment. For the sake of brevity, any parts not mentioned in the device embodiment can be referred to the corresponding content in the aforementioned method embodiment.

[0054] This invention provides an electronic device, specifically, the electronic device includes a processor and a storage device; the storage device stores a computer program, and the computer program, when run by the processor, executes the method described in any of the above embodiments.

[0055] Figure 5 The present invention provides a schematic diagram of the structure of an electronic device 100, which includes a processor 50, a memory 51, a bus 52 and a communication interface 53. The processor 50, the communication interface 53 and the memory 51 are connected through the bus 52. The processor 50 is used to execute executable modules, such as computer programs, stored in the memory 51.

[0056] The memory 51 may include high-speed random access memory (RAM) or non-volatile memory, such as at least one disk storage device. Communication between this system network element and at least one other network element is achieved through at least one communication interface 53 (which can be wired or wireless), such as the Internet, wide area network, local area network, metropolitan area network, etc.

[0057] Bus 52 can be an ISA bus, PCI bus, or EISA bus, etc. The bus can be divided into address bus, data bus, control bus, etc. For ease of representation, Figure 5 The symbol is represented by a single double-headed arrow, but this does not mean that there is only one bus or one type of bus.

[0058] The memory 51 is used to store programs. After receiving an execution instruction, the processor 50 executes the programs. The method executed by the device for defining the flow process disclosed in any of the foregoing embodiments of the present invention can be applied to the processor 50 or implemented by the processor 50.

[0059] Processor 50 may be an integrated circuit chip with signal processing capabilities. In implementation, each step of the above method can be completed by the integrated logic circuitry in the hardware of processor 50 or by instructions in software form. Processor 50 can be a general-purpose processor, including a Central Processing Unit (CPU), a Network Processor (NP), etc.; it can also be a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field-Programmable Gate Array (FPGA), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components. It can implement or execute the methods, steps, and logic block diagrams disclosed in the embodiments of this invention. The general-purpose processor can be a microprocessor or any conventional processor. The steps of the methods disclosed in the embodiments of this invention can be directly embodied in the execution of a hardware decoding processor, or executed by a combination of hardware and software modules in the decoding processor. The software modules can reside in random access memory, flash memory, read-only memory, programmable read-only memory, electrically erasable programmable memory, registers, or other mature storage media in the art. The storage medium is located in memory 51. The processor 50 reads the information in memory 51 and, in conjunction with its hardware, completes the steps of the above method.

[0060] The computer program product of the readable storage medium provided in the embodiments of the present invention includes a computer-readable storage medium storing program code. The instructions included in the program code can be used to execute the methods described in the foregoing method embodiments. For specific implementation, please refer to the foregoing method embodiments, which will not be repeated here.

[0061] If the aforementioned functions are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this invention, essentially, or the part that contributes to the prior art, or a portion of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0062] Finally, it should be noted that the above-described embodiments are merely specific implementations of the present invention, used to illustrate the technical solutions of the present invention, and not to limit it. The scope of protection of the present invention is not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that any person skilled in the art can still modify or easily conceive of changes to the technical solutions described in the foregoing embodiments within the technical scope disclosed in the present invention, or make equivalent substitutions for some of the technical features; and these modifications, changes, or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention, and should all be covered 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 determining the swing angle of a solar panel based on solar panel illumination, characterized in that, include: Obtain the track Angular sequence and the range of solar panel swing angles corresponding to the satellite's solar panels; For the orbit Any target orbit in the angular sequence Angle, determine the target orbit The initial solar panel sway angle value is used as the initial value. In the optimizer, an objective function is called to maximize the solar radiation output by the objective function for the given solar panel sway angle value. The sway angle value is iteratively adjusted within the given range of sway angles to obtain the target trajectory. The optimal windshield swing angle value under the angle; The solar panel illumination is the average effective irradiance of the solar panel on the satellite during one orbital period.

2. The method for determining the swing angle of a solar panel based on solar panel illumination according to claim 1, characterized in that, The optimizer calls an objective function, aiming to maximize the solar irradiance output by the objective function for the given solar panel yaw angle value. Using the range of the solar panel yaw angle as a constraint, the optimizer iteratively adjusts the solar panel yaw angle value to obtain the optimal solar panel yaw angle value under the target orbital angle, including: Perform the following operations in the optimizer: Call the target function; Based on the target orbit, through the target function. The solar panel illumination corresponding to the solar panel irradiance is determined by the angle, the solar panel sway angle value, and the semi-major axis of the satellite's orbit. If the solar panel irradiance does not meet the preset conditions, the solar panel swing angle value is adjusted based on the solar panel swing angle range, and the target function is called again until the solar panel irradiance meets the preset conditions. The solar panel yaw angle value corresponding to the minimum solar panel illumination is taken as the target orbit. The optimal windshield swing angle value under the angle.

3. The method for determining the swing angle of a solar panel based on solar panel illumination according to claim 2, characterized in that, Using the objective function, based on the target orbital angle, the solar panel oscillation angle, and the semi-major axis of the satellite's orbit, the solar panel irradiance corresponding to the oscillation angle value is determined, including: Based on the target orbit The effective illumination duration is determined by the angle, the swing angle of the solar panel, and the semi-major axis of the satellite's orbit. Based on the target orbit The evaluation value is determined by the angle, the solar panel swing angle value, the effective illumination duration, and the orbital period corresponding to the satellite, and the negative number of the evaluation value is used as the solar panel illumination corresponding to the solar panel swing angle value.

4. The method for determining the swing angle of a solar panel based on solar panel illumination according to claim 3, characterized in that, Based on the target orbital angle, the solar panel swing angle, and the pre-defined semi-major axis of the satellite's orbit, the effective illumination duration is determined, including: Based on the target orbit The angle and the preset orbital semi-major axis determine the first type of illumination duration, which is: the total time that the satellite can receive sunlight in one orbital period, taking into account the Earth's shading factor; Based on the target orbit The angle and the swing angle of the solar panel determine the second type of illumination duration, which is: the total time that the solar panel of the satellite can receive sunlight on its light-receiving surface within one orbital period, ignoring the Earth's shading factor and considering the attitude factor of the solar panel itself. The minimum value between the first type of illumination duration and the second type of illumination duration is taken as the effective illumination duration.

5. The method for determining the swing angle of a solar panel based on solar panel illumination according to claim 3, characterized in that, The evaluation value is determined based on the target orbital angle, the solar panel swing angle, the effective illumination duration, and the satellite's corresponding orbital period, including: The assessment value is determined using the following formula: ； in, For evaluation purposes, This is the windsurfing angle value. For the target orbit horn, For effective illumination duration, For orbital period.

6. The method for determining the solar panel swing angle based on solar panel illumination according to any one of claims 1-5, characterized in that, The range of the windshield angle is divided into the range of the left windshield angle and the range of the right windshield angle, and the windshield angle value is divided into the value of the left windshield angle and the value of the right windshield angle.

7. The method for determining the swing angle of a solar panel based on solar panel illumination according to claim 6, characterized in that, The method further includes: For the orbit Any of the target orbits in the angular sequence Angle, determine the target orbit The sum of the irradiance values ​​of the solar panels corresponding to the optimal left and right solar panel angle values ​​at each angle. Based on the orbit Each of the orbits in the angular sequence The total illuminance value corresponding to the angle is used to generate the total illuminance value along the orbit. Distribution diagram of angular variation.

8. A device for determining the swing angle of a solar panel based on solar panel illumination, characterized in that, include: The data acquisition module is used to acquire the track. Angular sequence and the range of solar panel swing angles corresponding to the satellite's solar panels; The swing angle iterative optimization module is used for the orbit. Any target orbit in the angular sequence Angle, determine the target orbit The initial solar panel sway angle value is used as the initial value. In the optimizer, an objective function is called to maximize the solar radiation output by the objective function for the given solar panel sway angle value. The sway angle value is iteratively adjusted within the given range of sway angles to obtain the target trajectory. The optimal windshield swing angle value under the angle; The solar panel illumination is the average effective irradiance of the solar panel on the satellite during one orbital period.

9. An electronic device, characterized in that, The method includes a processor and a memory, the memory storing computer-executable instructions executable by the processor, the processor executing the computer-executable instructions to implement the method of any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer-executable instructions that, when invoked and executed by a processor, cause the processor to perform the method according to any one of claims 1 to 7.

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