Method and device for calculating the mean solar irradiance cosine of a satellite solar wing in orbit

Abstract

The present application relates to the field of satellite energy analysis, and more particularly to a satellite solar wing on-orbit average illumination cosine calculation method and device, comprising: S1: obtaining a circular orbit altitude, an orbit beta angle range and a solar wing outer normal direction range; S2: determining an orbit shadow area range according to an orbit radius and an orbit beta angle; S3: generating an initial sun vector, obtaining a sun vector sequence by traversing an orbit phase angle, and generating a solar wing outer normal unit vector; S4: calculating an illumination cosine value and a sun elevation angle of each phase angle; S5: filtering invalid illumination data based on the shadow area range and the sun elevation angle threshold; S6: performing average processing on the valid illumination cosine value to obtain an entire-orbit average illumination cosine; and S7: batch traversing the parameter range to determine an optimal direction of the solar wing outer normal that maximizes the entire-orbit average illumination cosine. The present application has few input parameters and a standardized calculation process, and can realize automatic optimization of the solar wing installation angle.

Description

Technical Field

[0001] This invention relates to the field of satellite energy analysis technology, and in particular to a method and device for calculating the on-orbit average illumination cosine of a satellite solar array. Background Technology

[0002] With the rapid development of aerospace technology, low-Earth orbit satellite constellations are showing a significant trend towards large-scale, low-cost, and batch deployment. Against this backdrop, to improve the design efficiency and evaluation accuracy of satellite energy systems, traditional technologies typically employ illumination analysis methods based on orbital parameters, mainly including transient angle analysis, orbital element integration, and general orbital illumination model methods.

[0003] The transient angle analysis method calculates the solar incidence angle only for specific moments or discrete orbital positions during operation, failing to reflect the average light received by the satellite over a complete orbital period. Its calculation results deviate significantly from the actual long-term energy output characteristics of the solar array, limiting the accuracy of energy system design margin assessments to some extent. The orbital element integration method requires inputting numerous complex parameters such as the complete six orbital elements, orbital period, right ascension of the ascending node, and seasonal parameters. The numerous input conditions and cumbersome calculation process require engineers with strong orbital mechanics backgrounds to complete the analysis, hindering rapid iteration and multi-scheme comparison during the design phase. While the general orbital illumination model method can adapt to various orbital types, the complexity of the calculation model increases significantly due to the need to consider factors such as eccentricity and orbital perturbations. It is not specifically optimized for the most widely used low-Earth orbit circular orbit, making it difficult to achieve a good balance between computational efficiency and engineering accuracy.

[0004] Furthermore, none of the aforementioned analytical methods simultaneously consider multiple practical constraints, such as Earth's shadow occlusion, the engineering threshold of the solar altitude angle, and the actual installation attitude of the solar array. While some methods can calculate the duration of shadows, they do not integrate this calculation with the calculation of the cosine of illumination; other methods assume that the solar array is always directly facing the sun, ignoring the actual pointing limitations of a fixedly installed solar array. This makes the calculation results idealized and difficult to directly guide engineering practice.

[0005] In practical applications, the layout design of satellite solar arrays presents significant differences in reliability and energy output requirements. Under different orbital β-angle conditions, the solar array's illumination level varies considerably; furthermore, the average illumination level across the entire orbit fluctuates considerably depending on the solar array's installation angle. However, traditional analysis methods lack standardized calculation processes and automated frameworks capable of batch processing, making it difficult to systematically optimize solar array installation angles. They still rely on manual calculations and experience-based judgments. When orbital parameters or mission requirements change, a large amount of repetitive calculation work must be performed again, resulting in significant shortcomings in analysis efficiency and design optimization capabilities.

[0006] Therefore, there is an urgent need in engineering for a method to calculate the average illumination cosine of the entire orbit with clear input parameters, specifically adapted to circular orbits, with standardized calculation procedures, and calculation results that closely reflect engineering realities, in order to support the rapid design and optimization evaluation of solar arrays for low Earth orbit circular orbit satellites. Summary of the Invention

[0007] The purpose of this invention is to overcome the shortcomings of existing technologies and provide a method for calculating the on-orbit average illumination cosine of satellite solar panels, comprising the following steps: S1: Obtain the circular orbit height, orbit β angle range, and solar array outer normal direction range; S2: Calculate the orbit radius based on the circular orbit height, and determine the orbital shadow area range within one complete orbital cycle of the satellite based on the orbit radius and the orbital angle β; S3: For each orbital β angle within the orbital β angle range, generate an initial solar vector, and generate the solar vector corresponding to each orbital phase angle position by traversing the orbital phase angles. At the same time, generate a solar wing outer normal unit vector based on the range of the solar wing outer normal direction. S4: Calculate the illumination cosine value and solar altitude angle corresponding to each orbital phase angle based on the solar vector corresponding to the position of each orbital phase angle and the unit vector of the outer normal of the solar wing; S5: Based on the orbital shadow area and the preset solar altitude angle threshold, the illumination cosine value is filtered to remove invalid illumination data that are in the shadow area or whose solar altitude angle is lower than the threshold. S6: Average the effective illumination cosine value over the entire orbital period after filtering to obtain the whole orbital average illumination cosine under the combination of the orbital β angle and the outer normal direction of the solar array. S7: Based on the batch traversal results of the orbit β angle range and the solar wing outer normal direction range, determine the optimal solar wing outer normal direction that maximizes the average illumination cosine of the entire orbit.

[0008] Preferably, in step S2, based on the orbital radius and the orbital angle β, the range of the orbital shadow area within one complete orbital period of the satellite is determined, including: Based on Earth's radius The formula for calculating the track radius r from the height H of the circular track is as follows: ; According to Earth's radius Calculate the Earth's apparent half-angle using the orbital radius r. The calculation formula is: ; According to the Earth's apparent half-angle The shadow judgment ratio calculated with the orbital β angle The calculation formula is: ; When the shadow judgment ratio satisfies |ratio|≥1, it is determined that the satellite is in full illumination throughout the entire course under the corresponding orbital angle β, and the shadow arc length is 0. When the shadow judgment ratio |ratio| < 1, calculate the shadow arc length. And based on the shadow arc length, determine the orbital phase angle range corresponding to the shadow area, the shadow arc length The calculation formula is as follows: .

[0009] Preferably, in step S3, an initial solar vector is generated, and the solar vector corresponding to each orbital phase angle position is generated by traversing the orbital phase angles, including: Generate the initial solar vector in the orbital coordinate system based on the current orbital angle β. The initial solar vector The expression is: ; The orbital phase angle θ is traversed within the range of 0° to 360° with a preset step size, and the rotation matrix around the Y-axis is used. For the initial solar vector Perform a rotation transformation to obtain the solar vector corresponding to the orbital phase angle position. The calculation formula is: .

[0010] Preferably, in step S3, generating the unit vector of the outer normal of the solar wing based on the range of the outer normal direction of the solar wing includes: Define the initial reference direction vector ; According to the angle within the range of the outer normal direction of the solar wing Using a rotation matrix around the X-axis For the initial reference direction vector Perform a rotation transformation to obtain the outer normal direction vector of the solar array. The calculation formula is: ; For the outer normal direction vector of the solar array After normalization, the unit vector of the solar array's outer normal is obtained. The normalization process satisfies: .

[0011] Preferably, in step S4, the calculation of the illumination cosine value and solar altitude angle corresponding to each orbital phase angle includes: Solar vector corresponding to each orbital phase angle position unit vector of the outer normal of the solar wing Perform a dot product operation to obtain the illumination cosine value of the corresponding orbital phase angle. The calculation formula is: ; Based on the light cosine value The corresponding solar altitude angle h is calculated using the following formula: .

[0012] Preferably, in step S5, invalid illumination data located in the shadow area is removed, including: Determine whether the phase angle of the currently traversed orbit is within the orbital shadow area; If the phase angle of the currently traversed orbit is within the orbit shadow area, then the illumination cosine value corresponding to the orbit phase angle is set to zero or removed.

[0013] Preferably, invalid illumination data with a solar altitude angle lower than a preset solar altitude angle threshold are removed, including: Determine whether the solar altitude angle corresponding to the current orbital phase angle is lower than the preset solar altitude angle threshold. ; If the solar altitude angle corresponding to the current orbital phase angle is lower than the solar altitude angle threshold If so, the corresponding illumination cosine value will be set to zero or removed. in, This indicates the preset solar altitude angle threshold.

[0014] Preferably, in step S6, the effective illumination cosine value over the entire orbital period after filtering is averaged, including: The effective illumination cosine values ​​over the entire orbital period are discretely integrated and accumulated to obtain the total effective accumulated value. Dividing the total effective accumulated value by the total number of traversal points throughout the entire orbital period yields the average illumination cosine of the entire orbit. The calculation formula is: , in, Let represent the effective illumination cosine value corresponding to the i-th traversal point, and N represent the total number of traversal points for the entire orbital period.

[0015] Preferably, in step S7, based on the batch traversal results, the optimal direction of the solar array's outer normal that maximizes the average illumination cosine of the entire orbit is determined, including: The range of the outer normal direction of the solar wing is traversed with a preset angle step size, and the range of the orbit β angle is traversed with a preset β angle step size, to construct a whole-track average illumination cosine result matrix with the outer normal direction of the solar wing as the row and the orbit β angle as the column. The results matrix is ​​used to statistically compare the total orbit average illumination cosine results corresponding to each solar wing outer normal direction. The solar wing outer normal direction with the maximum value of the total orbit average illumination cosine is selected as the optimal solar wing outer normal direction.

[0016] Based on the same concept, the present invention also provides a computer device, including a memory and one or more processors, wherein the memory stores computer code, and when the computer code is executed by the one or more processors, the one or more processors cause the one or more processors to perform the steps of a method for calculating the on-orbit average illumination cosine of a satellite solar array as described in any one of the embodiments.

[0017] Compared with the prior art, the beneficial effects of the present invention are: (1) This invention uses the height of the circular orbit, the range of the orbit β angle, and the range of the outer normal direction of the solar wing as core input parameters. Only three types of explicit parameters are needed to complete all analysis and calculation. There is no need to input complex orbital parameters such as the number of orbital elements, orbital period, and right ascension of the ascending node. This greatly simplifies the input conditions and calculation process, significantly reduces the threshold for engineering use, and greatly improves the ability to iterate quickly in the scheme stage.

[0018] (2) This invention determines the range of the orbital shadow area of ​​a satellite within a complete orbital cycle based on the orbital radius and orbital β angle, and performs dual filtering on the illumination data by combining a preset solar altitude angle threshold, thereby achieving integrated invalid data removal under the conditions of Earth shadow occlusion and low solar altitude angle, so that the calculation results effectively reflect the real on-orbit light constraint and ensure the engineering closeness and reliability of the energy assessment results.

[0019] (3) This invention generates a full-cycle solar vector sequence by traversing the orbital β angle range and generating a corresponding normal unit vector based on the range of the outer normal direction of the solar wing, thereby realizing the discretized illumination traversal calculation of the entire orbital period and multiple parameter combinations, providing a complete and continuous data foundation for the analysis of the average characteristics of the entire orbit.

[0020] (4) This invention calculates the illumination cosine value and solar altitude angle corresponding to each orbit phase angle, and performs full-cycle averaging on the filtered effective illumination cosine value, so as to replace the traditional transient value with the average illumination cosine of the whole orbit as the evaluation index, which truly reflects the long-term light reception level and energy output characteristics of the satellite in orbit, and provides a more accurate quantitative basis for solar array layout design and energy system margin assessment.

[0021] (5) This invention constructs a matrix of the average illumination cosine of the entire track under multiple parameter combinations by batch traversing the range of the orbit β angle and the range of the outer normal direction of the solar wing, and filters the optimal direction of the outer normal of the solar wing that maximizes the average illumination cosine of the entire track based on the traversal results, thereby realizing the automated optimization of the solar wing installation angle, effectively reducing the workload of manual trial calculation, and improving design efficiency and scheme optimization capabilities.

[0022] (6) The overall technical solution of this invention is specifically adapted to low-Earth orbit circular orbit satellites. It is specifically simplified for the characteristic that the orbit radius of a circular orbit is constant, without having to consider the complex calculations caused by the change in eccentricity, thus achieving a good balance between computational efficiency and engineering accuracy. At the same time, the method is compatible with the illumination characteristic analysis of fixed solar arrays and single-axis SADA solar arrays, and has the practical advantages of strong versatility and easy embedding into the overall satellite design process. Attached Figure Description

[0023] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention.

[0024] Figure 1 This is a flowchart of a method for calculating the on-orbit average illumination cosine of a satellite solar array according to the present invention; Figure 2 This is a three-dimensional view of a method for calculating the on-orbit average illumination cosine of a satellite solar array according to the present invention; Figure 3 This is a two-dimensional view of a method for calculating the on-orbit average illumination cosine of a satellite solar array according to the present invention. Detailed Implementation

[0025] 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 of the invention and are not intended to limit the invention. Obviously, the described embodiments are only some, not all, of the embodiments described in this application. All other embodiments obtained by those skilled in the art based on the embodiments in this application without creative effort are within the scope of protection of this application.

[0026] Those skilled in the art will understand that, unless otherwise stated, the singular forms “a” and “an” used herein, and “the”, may also include the plural forms. It should be further understood that the term “comprising” as used in this specification means the presence of the stated features, integers, steps, operations, elements, and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof.

[0027] First Embodiment Please see Figure 1 As shown, this embodiment provides a method for calculating the on-orbit average illumination cosine of a satellite solar array. This method is used to calculate the average illumination level of the satellite solar array across its entire orbit under different orbital β angles and solar array outer normal directions, and to determine the optimal installation direction from candidate directions that maximizes the average illumination cosine of the entire orbit. This method is applicable to scenarios such as solar array layout design, on-orbit attitude analysis, power assessment, and configuration optimization for low-Earth orbit satellites in circular orbits, and includes the following steps: S1: Obtain the circular orbit altitude, orbital β angle range, and solar array outer normal direction range. Specifically, in this embodiment, the circular orbit altitude H = 500 km, the Earth radius Re = 6378.137 km, and the orbital radius r = Re + H is a constant, consistent with the characteristics of a circular orbit; the orbital β angle range is determined to be 17° to 27° based on the satellite orbital parameters and the change in the sun's position during the mission cycle, with a traversal step size of 1°; the solar array outer normal direction range is the reversal angle around the satellite's roll axis (X-axis). The value ranges from 90° to 180°, with a step size of 1°.

[0028] In this embodiment, an orbital coordinate system is used for calculation, and two basic rotation matrices are defined to realize the attitude transformation of the solar array normal vector and the on-orbit traversal of the solar vector.

[0029] Where the rotation matrix around the X-axis The expression for deflection in the direction of the outer normal of the solar array is: .

[0030] Rotation matrix around the Y-axis The phase angle θ used to traverse one cycle of the satellite in orbit, with a value ranging from 0° to 360°, is expressed as: .

[0031] Figure 2 It can be used to illustrate the three-dimensional geometric relationship between the outer normal direction of the solar array, the solar incidence direction, and the orbital coordinate system; Figure 3 It can be used to illustrate the orbital phase angle, the extent of the shadow region, and the two-dimensional projection relationship of the solar vector in the orbital plane. Figure 2 and Figure 3 The geometric relationships shown provide a geometric foundation for subsequent shadow area determination, solar vector generation, and illumination cosine calculation. S2: Calculate the orbit radius based on the circular orbit height, and determine the orbit shadow area range within one complete cycle (0°~360°) of the satellite in orbit based on the orbit radius and the orbit β angle. Specifically, in this embodiment, a fast calculation method of apparent half angle + β angle is adopted, which only depends on the input parameters (orbit height H, β angle).

[0032] Preferably, in step S2, based on the orbital radius and orbital angle β, the range of the orbital shadow area during one complete orbital period of the satellite is determined, including: Based on Earth's radius The formula for calculating the track radius r from the height H of the circular track is as follows: ; According to Earth's radius Calculate the Earth's apparent half-angle with orbital radius r The calculation formula is: , Specifically, in this embodiment, the Earth's apparent half-angle γ represents the angle subtended by the Earth as seen from the satellite's position, and is used to reflect the relative geometric relationship between the satellite and the Earth; According to the Earth's apparent half-angle The ratio of shadow judgment calculated with orbital β angle The calculation formula is: , Specifically, in this embodiment, taking β=20° as an example, γ≈68.0° and ratio≈0.3986 are calculated; When the shadow judgment ratio satisfies |ratio|≥1, it is determined that the satellite is in full illumination throughout the entire course under the corresponding orbital angle β, and the shadow arc length is 0. When the shadow judgment ratio |ratio| < 1, calculate the shadow arc length. And based on the shadow arc length, determine the orbital phase angle range corresponding to the shadow area, shadow arc length The calculation formula is as follows: , Specifically, in this embodiment, when β = 20°, the shadow arc length can be obtained. ≈133.0°. Furthermore, after converting the shadow arc length into an angle range, the range of the shadowed area for the on-orbit phase angle can be determined as follows: That is, the shadow area is located within a symmetrical interval with the center of the orbital phase angle at 180°. This shadow area is used for subsequent filtering of invalid lighting data.

[0033] S3: For each orbital β angle within the orbital β angle range, generate an initial solar vector, and generate the solar vector corresponding to each orbital phase angle position by traversing the orbital phase angles. At the same time, generate the solar wing outer normal unit vector based on the range of the solar wing outer normal direction.

[0034] Preferably, in step S3, an initial solar vector is generated, and the solar vector corresponding to each orbital phase angle position is generated by traversing the orbital phase angles, including: Generate the initial solar vector in the orbital coordinate system based on the current orbital angle β. Initial solar vector The expression is: , Specifically, in this embodiment, β is the input orbital angle β. During the calculation process, if the program uses the standard trigonometric function library, the angle β must first be converted to radians, i.e.: ; The orbital phase angle θ is traversed within the range of 0° to 360° with a preset step size, and the rotation matrix around the Y-axis is used. For the initial solar vector Perform a rotation transformation to obtain the solar vector corresponding to the orbital phase angle position. The calculation formula is: , The orbital phase angle also needs to be converted to radians before being substituted into the trigonometric functions: .

[0035] Preferably, in step S3, generating the unit vector of the outer normal of the solar wing based on the range of the outer normal direction of the solar wing includes: Define the initial reference direction vector ; Based on the angle within the range of the outer normal direction of the solar wing Using a rotation matrix around the X-axis For the initial reference direction vector Perform a rotation transformation to obtain the outer normal direction vector of the solar array. The calculation formula is: ; For the outer normal direction vector of the solar array After normalization, the unit vector of the solar array's outer normal is obtained. The unitization process satisfies: , in, Representing vectors The length of the module.

[0036] S4: Calculate the illumination cosine and solar altitude angle corresponding to each orbital phase angle based on the solar vector and the unit vector of the outer normal of the solar wing.

[0037] Preferably, in step S4, the calculation of the illumination cosine value and solar altitude angle corresponding to each orbital phase angle includes: Solar vector corresponding to each orbital phase angle position unit vector of the outer normal of the solar wing Perform a dot product operation to obtain the illumination cosine value of the corresponding orbital phase angle. The calculation formula is: , in, It is used to characterize the angle between the direction of solar incidence and the direction of the outer normal of the solar array. The larger the value, the more fully the solar array receives sunlight. Based on the cosine value of illumination The corresponding solar altitude angle h is calculated using the following formula: , Numerically, the above formula is also equivalent to .

[0038] S5: Based on the orbital shadow area and the preset solar altitude angle threshold (5°), the cosine value of illumination is filtered to remove invalid illumination data that are in the shadow area or whose solar altitude angle is below the threshold.

[0039] Preferably, in step S5, invalid illumination data located in the shadow area is removed, including: Determine whether the phase angle of the currently traversed orbit is within the orbital shadow area; If the current orbit phase angle is within the orbit shadow area, the corresponding illumination cosine value is set to zero or discarded. Specifically, in this embodiment, if the current orbit phase angle is within the shadow area, the corresponding illumination cosine value is set to zero. That is, when: At that time, the corresponding illumination cosine value is treated as invalid data.

[0040] Preferably, invalid illumination data with a solar altitude angle lower than a preset solar altitude angle threshold are removed, including: Determine whether the solar altitude angle corresponding to the current orbital phase angle is lower than the preset solar altitude angle threshold. ; If the solar altitude angle corresponding to the current orbital phase angle is lower than the solar altitude angle threshold If so, the corresponding illumination cosine value will be set to zero or removed. in, This represents a preset solar altitude angle threshold. Specifically, in this embodiment, when... If the angle of solar incidence at that location is too low, the corresponding illumination is invalid, and the cosine value of illumination at that point is also set to zero.

[0041] S6: Average the effective illumination cosine value over the entire orbital period after filtering to obtain the whole orbital average illumination cosine under the combination of the orbital β angle and the outer normal direction of the solar array.

[0042] Preferably, in step S6, the effective illumination cosine value over the entire orbital period after filtering is averaged, including: The effective illumination cosine values ​​over the entire orbital period are discretely integrated and accumulated to obtain the total effective accumulated value. Dividing the total effective accumulated value by the total number of traversal points throughout the entire orbital period yields the average illumination cosine of the entire orbit. The calculation formula is: , in, Let N represent the effective illumination cosine value corresponding to the i-th traversal point, and let N represent the total number of traversal points for the entire orbital period. Specifically, in this embodiment, the traversal step size of the orbital phase angle is 0.1°, the traversal range is 0° to 359.9°, and the total number of traversal points N = 360° / 0.1° = 3600. After accumulating the effective illumination cosine values ​​of each traversal point, the average illumination cosine of the entire orbit under the orbital β angle and the outer normal direction of the solar wing can be obtained.

[0043] It should be noted that this embodiment uses a method of setting invalid data to zero before participating in the averaging of the total points. Therefore, the denominator is the total number of points N traversed throughout the entire orbit. This method can comprehensively reflect the overall light reception level of the solar array within the entire orbital period. S7: Based on the batch traversal results of the orbit β angle range and the solar array outer normal direction range, determine the optimal solar array outer normal direction that maximizes the average illumination cosine of the entire orbit.

[0044] Preferably, in step S7, based on the batch traversal results, the optimal direction of the solar array's outer normal that maximizes the average illumination cosine of the entire orbit is determined, including: The range of the outer normal direction of the solar wing is traversed with a preset angle step size, and the range of the orbital β angle is traversed with a preset β angle step size. A matrix res representing the overall average illumination cosine of the entire orbit is constructed, with the outer normal direction of the solar wing as the row and the orbital β angle as the column. Specifically, in this embodiment, the range of the outer normal direction of the solar wing is traversed from 90° to 180° with a step size of 1° to obtain multiple outer normal directions of the solar wing; the range of the orbital β angle is traversed from 17° to 27° with a step size of 1° to obtain multiple orbital β angle values; and a matrix res is constructed with the outer normal direction of the solar wing as the row and the orbital β angle as the column, where res(i,j) represents the overall average illumination cosine value of the entire orbit under the combination of the i-th outer normal direction of the solar wing and the j-th orbital β angle. The results matrix is ​​used to statistically compare the total orbit average illumination cosine values ​​corresponding to each solar wing outer normal direction. The solar wing outer normal direction with the maximum total orbit average illumination cosine value is selected as the optimal solar wing outer normal direction. Specifically, in this embodiment, the maximum and minimum values ​​of the results matrix res are counted row by row, representing the optimal and worst average illumination cosine values ​​of the solar wing outer normal direction under different β angle conditions. ; Furthermore, select The direction of the outer normal of the solar array corresponding to the maximum value is taken as the optimal direction of the outer normal of the solar array, thereby realizing the quantitative optimization of the solar array installation angle.

[0045] Second Embodiment In this embodiment, a computer device is provided, including a memory and one or more processors. The memory stores computer code. When the computer code is executed by one or more processors, it causes the one or more processors to perform the steps of the satellite solar array on-orbit average illumination cosine calculation method in the first embodiment.

[0046] In some embodiments of this application, a computer-readable storage medium is also provided, wherein when the computer-readable instructions are executed by one or more processors, the one or more processors perform the steps of a method for calculating the on-orbit average illumination cosine of a satellite solar array as described in any of the first embodiments.

[0047] It is understood that, regarding the aforementioned method for calculating the on-orbit average illumination cosine of a satellite solar array, if all of these methods are implemented as software functional modules 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, in essence, or the part that contributes to the prior art, or all or part 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 a network device, etc.) to execute all or part of the steps of the methods 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.

[0048] Computer-readable storage media may include data signals propagated in baseband or as part of a carrier wave, carrying readable program code. Such propagated data signals may take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A readable storage medium may also be any readable medium other than a readable storage medium that can transmit, propagate, or transfer a program for use by or in connection with an instruction execution system, apparatus, or device. The program code contained on the readable storage medium may be transmitted using any suitable medium, including but not limited to wireless, wired, optical fiber, RF, etc., or any suitable combination thereof.

[0049] The above description is merely a preferred embodiment of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions falling within the scope of the present invention's concept are within the scope of protection of the present invention. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principles of the present invention should also be considered within the scope of protection of the present invention.

Claims

1. A method for calculating the cosine of the on-orbit average illumination of a satellite solar array, characterized in that, Includes the following steps: S1: Obtain the circular orbit height, orbit β angle range, and solar array outer normal direction range; S2: Calculate the orbit radius based on the circular orbit height, and determine the orbital shadow area range within one complete orbital cycle of the satellite based on the orbit radius and the orbital angle β; S3: For each orbital β angle within the orbital β angle range, generate an initial solar vector, and generate the solar vector corresponding to each orbital phase angle position by traversing the orbital phase angles. At the same time, generate a solar wing outer normal unit vector based on the range of the solar wing outer normal direction. S4: Calculate the illumination cosine value and solar altitude angle corresponding to each orbital phase angle based on the solar vector corresponding to the position of each orbital phase angle and the unit vector of the outer normal of the solar wing; S5: Based on the orbital shadow area and the preset solar altitude angle threshold, the illumination cosine value is filtered to remove invalid illumination data that are in the shadow area or whose solar altitude angle is lower than the threshold. S6: Average the effective illumination cosine value over the entire orbital period after filtering to obtain the whole orbital average illumination cosine under the combination of the orbital β angle and the outer normal direction of the solar array. S7: Based on the batch traversal results of the orbit β angle range and the solar wing outer normal direction range, determine the optimal solar wing outer normal direction that maximizes the average illumination cosine of the entire orbit.

2. The method for calculating the on-orbit average illumination cosine of satellite solar arrays according to claim 1, characterized in that, In step S2, based on the orbital radius and the orbital angle β, the range of the orbital shadow area during one complete orbital period of the satellite is determined, including: Based on Earth's radius The formula for calculating the track radius r from the height H of the circular track is as follows: ； According to Earth's radius Calculate the Earth's apparent half-angle using the orbital radius r. The calculation formula is: ； According to the Earth's apparent half-angle The shadow judgment ratio calculated with the orbital β angle The calculation formula is: ； When the shadow judgment ratio satisfies |ratio|≥1, it is determined that the satellite is in full illumination throughout the entire course under the corresponding orbital angle β, and the shadow arc length is 0. When the shadow judgment ratio |ratio| < 1, calculate the shadow arc length. And based on the shadow arc length, determine the orbital phase angle range corresponding to the shadow area, the shadow arc length The calculation formula is as follows: 。 3. The method for calculating the on-orbit average illumination cosine of satellite solar arrays according to claim 1, characterized in that, In step S3, an initial solar vector is generated, and the solar vector corresponding to each orbital phase angle position is generated by traversing the orbital phase angles, including: Generate the initial solar vector in the orbital coordinate system based on the current orbital angle β. The initial solar vector The expression is: ； The orbital phase angle θ is traversed within the range of 0° to 360° with a preset step size, and the rotation matrix around the Y-axis is used. For the initial solar vector Perform a rotation transformation to obtain the solar vector corresponding to the orbital phase angle position. The calculation formula is: 。 4. The method for calculating the on-orbit average illumination cosine of satellite solar arrays according to claim 1, characterized in that, In step S3, the outer normal unit vector of the solar wing is generated based on the range of the outer normal direction of the solar wing, including: Define the initial reference direction vector ; According to the angle within the range of the outer normal direction of the solar wing Using a rotation matrix around the X-axis For the initial reference direction vector Perform a rotation transformation to obtain the outer normal direction vector of the solar array. The calculation formula is: ； For the outer normal direction vector of the solar array After normalization, the unit vector of the solar array's outer normal is obtained. The normalization process satisfies: 。 5. The method for calculating the on-orbit average illumination cosine of satellite solar arrays according to claim 1, characterized in that, In step S4, the illumination cosine value and solar altitude angle corresponding to each orbital phase angle are calculated, including: Solar vector corresponding to each orbital phase angle position unit vector of the outer normal of the solar wing Perform a dot product operation to obtain the illumination cosine value of the corresponding orbital phase angle. The calculation formula is: ； Based on the light cosine value The corresponding solar altitude angle h is calculated using the following formula: 。 6. The method for calculating the on-orbit average illumination cosine of satellite solar arrays according to claim 1, characterized in that, In step S5, invalid lighting data located in the shadow area is removed, including: Determine whether the phase angle of the currently traversed orbit is within the orbital shadow area; If the phase angle of the currently traversed orbit is within the orbit shadow area, then the illumination cosine value corresponding to the orbit phase angle is set to zero or removed.

7. The method for calculating the on-orbit average illumination cosine of satellite solar arrays according to claim 1, characterized in that, Invalid illumination data with a solar altitude angle lower than a preset solar altitude angle threshold are removed, including: Determine whether the solar altitude angle corresponding to the current orbital phase angle is lower than the preset solar altitude angle threshold. ; If the solar altitude angle corresponding to the current orbital phase angle is lower than the solar altitude angle threshold If so, the corresponding illumination cosine value will be set to zero or removed. in, This indicates the preset solar altitude angle threshold.

8. The method for calculating the on-orbit average illumination cosine of satellite solar arrays according to claim 1, characterized in that, In step S6, the effective illumination cosine value over the entire orbital period after filtering is averaged, including: The effective illumination cosine values ​​over the entire orbital period are discretely integrated and accumulated to obtain the total effective accumulated value. Dividing the total effective accumulated value by the total number of traversal points throughout the entire orbital period yields the average illumination cosine of the entire orbit. The calculation formula is: ， in, Let represent the effective illumination cosine value corresponding to the i-th traversal point, and N represent the total number of traversal points for the entire orbital period.

9. The method for calculating the on-orbit average illumination cosine of a satellite solar array according to claim 1, characterized in that, In step S7, based on the batch traversal results, the optimal direction of the solar array's outer normal that maximizes the average illumination cosine of the entire orbit is determined, including: The range of the outer normal direction of the solar wing is traversed with a preset angle step size, and the range of the orbit β angle is traversed with a preset β angle step size, to construct a whole-track average illumination cosine result matrix with the outer normal direction of the solar wing as the row and the orbit β angle as the column. The results matrix is ​​used to statistically compare the total orbit average illumination cosine results corresponding to each solar wing outer normal direction. The solar wing outer normal direction with the maximum value of the total orbit average illumination cosine is selected as the optimal solar wing outer normal direction.

10. A computer device comprising a memory and one or more processors, the memory storing computer code that, when executed by the one or more processors, causes the one or more processors to perform the steps of the method for calculating the on-orbit average illumination cosine of a satellite solar array as described in any one of claims 1-9.

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