Spectral measurement method for luminosity of low-orbit satellite and satellite constellation in near space

Abstract

The invention relates to a near space low earth orbit satellite and satellite constellation luminosity spectral measurement method, which comprises the following steps: acquiring a low earth orbit satellite and satellite constellation model, and carrying out two-dimensional surface element grid division on the low earth orbit satellite and satellite constellation model; reconstructing a low earth orbit satellite and a satellite constellation model by using the divided surface element data, establishing different satellite and satellite constellation model scenes, and obtaining vector data of the satellite and the satellite constellation changing along with the solar altitude angle and the solar azimuth angle; and calculating the luminosity spectrums of satellites and satellite constellations in different observation scenes according to the vector data in combination with a bidirectional reflection distribution function model and an atmospheric radiation transmission model. The invention aims to improve the precision and stability of observation data, and compared with a space-based observation platform, the deployment and recovery cost of the near space observation platform is lower, and the observation position and angle are easier to adjust. The limitation of foundation observation and space-based observation is overcome, the observation precision and flexibility are improved, and an important means of diversified research is supported.

Description

Technical Field

[0001] The present invention relates to the fields of aerospace technology, satellite and satellite constellation communications and remote sensing, optical observation and numerical simulation calculation modeling technology, and in particular to a near-space photometric spectrum measurement method for low-orbit satellites and satellite constellations. Background Art

[0002] The importance of near-space to the photometric and spectral measurements of low-orbit satellites and satellite constellations: it not only provides superior atmospheric conditions and observation distance advantages, but also provides strong environmental support for optical observation methods. By making full use of these advantages of near-space, we can conduct more in-depth research on the optical spectral characteristics of low-orbit satellites and satellite constellations, and promote the further development of aerospace technology.

[0003] Limitations of traditional observation methods: The biggest limitation of ground-based observations is the impact of the Earth's atmosphere on observation results. When the reflected light from low-orbit satellites and satellite constellations is transmitted to the surface, it passes through the atmosphere. During this process, the light signal will be absorbed and scattered by the atmosphere, resulting in a weakening of the observed signal intensity, and may introduce additional noise and errors. Although space-based observations are not affected by the Earth's atmosphere, due to the long distance between the observation equipment and low-orbit satellites and satellite constellations, the irradiance of the reflected light received from satellites and satellite constellations is relatively low. This increases the difficulty of signal detection and may affect the signal-to-noise ratio of the observation data. Summary of the invention

[0004] In order to solve the problems existing in the above-mentioned prior art, the purpose of the present invention is to provide a near-space photometric spectrum measurement method for low-orbit satellites and satellite constellations, aiming to improve the accuracy and stability of observation data, and compared with space-based observation platforms, the deployment and recovery costs of near-space observation platforms are lower, and it is easier to adjust the observation position and angle. It is an important means to overcome the limitations of ground-based and space-based observations, improve observation accuracy and flexibility, and support diversified research.

[0005] To achieve the above object, the present invention provides the following solutions:

[0006] A near-space photometric spectrum measurement method for low-orbit satellites and satellite constellations, comprising:

[0007] Acquire a low-orbit satellite and satellite constellation model, and perform two-dimensional facet meshing on the low-orbit satellite and satellite constellation model;

[0008] Reconstruct the low-orbit satellite and satellite constellation model using the divided face metadata, establish different satellite and satellite constellation model scenarios, simulate different scenarios on the aerospace analysis platform, and obtain vector data of satellites and satellite constellations that change with solar altitude angles and azimuth angles;

[0009] According to the vector data, in combination with a bidirectional reflectance distribution function model and an atmospheric radiation transfer model, the photometric spectra of satellites and satellite constellations under different observation scenarios are calculated.

[0010] Optionally, establishing the different satellite and satellite constellation model scenarios includes:

[0011] Reconstruct the low-orbit satellite and satellite constellation model using the divided face data to obtain the rotation of the solar panels of the satellite and the satellite constellation following the sun vector and the shadow area of ​​the satellite and the satellite constellation body;

[0012] Based on the rotation and the shadow area, the satellite and satellite constellation model scene is established.

[0013] Optionally, the method further comprises:

[0014] Adjust the coefficients of the bidirectional reflectance distribution function model, so as to adjust the surface materials of the satellite and the satellite constellation to the materials of the satellite and the satellite constellation in the photoelectric sensor, observe the photometric curve of the bidirectional reflectance distribution function model, change the specular reflectance and the diffuse reflectance, analyze the photometric characteristics of the bidirectional reflectance distribution function model, and obtain the simulation calculation results;

[0015] Use photoelectric sensors to collect irradiance data and calculate photometric data for satellites and satellite constellations, and use electro-optical infrared sensor system modules on aerospace analysis platforms to extract detection time and satellite photometric characteristics to obtain photoelectric detection results;

[0016] The simulation calculation results and the photoelectric detection results are used to verify the calculated photometric spectra of the satellite and satellite constellation under different observation scenarios.

[0017] Optionally, analyzing the photometric characteristics of the bidirectional reflectance distribution function model includes:

[0018] When analyzing the photometric characteristics of the Starlink satellite solar panels, contributing factors are identified, and based on the contributing factors, the total solar flux and final brightness of the spacecraft are calculated.

[0019] Optionally, the contributing factors include: diffuse reflection from the front surface of the solar panel, diffuse reflection from the rear surface of the solar panel, diffuse reflection from the bottom of the solar panel, and specular reflection from the bottom of the solar panel.

[0020] Optionally, the diffuse reflection on the rear surface of the solar panel includes: diffuse reflection of the exposed antenna and diffuse reflection outside the sunshade.

[0021] Optionally, the formula for calculating the total solar flux of the spacecraft is:

[0022] F=a×cos(PVA)×cos(PSA)×BF+b×cos(180-PVA)+(c×sin(SDA)×VE+d×((cosSOA) e )×cos(OBA)

[0023] Among them, PVA is the panel observation angle, PSA is the solar phase angle, a is the diffuse reflectance parameter of the front of the solar panel, BF is the blocking factor, b is the reflectance of the back of the panel, c is the diffuse reflectance of the bottom of the body, VE is the sunshade efficiency, d is the specular reflectance of the bottom of the body, SOA is the specular beam deviation angle, OBA is the deviation from the baseline observation angle, the angle between the zenith line of the spacecraft and the observer direction, and SDA is the solar depression angle.

[0024] Optionally, calculating the final brightness of the spacecraft includes:

[0025] m visorsat = -2.5 × log 10 (F)+f

[0026] Where F is the total solar flux and f is a constant used to calculate apparent magnitude.

[0027] The beneficial effects of the present invention are:

[0028] The signal transmission delay of the low-orbit satellite and satellite constellation of the present invention is smaller, and it is more suitable for providing real-time communication and data transmission services; and compared with ground-based observation and space-based observation, near-space has a lower atmospheric density and a closer detection distance to low-orbit satellites and satellite constellations, so it has more superior optical observation conditions, which is conducive to the photometric and spectral measurement research of low-orbit satellites and satellite constellations. In addition, by adjusting the surface material of the satellite and satellite constellation in the bidirectional reflectance distribution function model to the material of the satellite and satellite constellation calculated by photoelectric sensing, the photometric and spectral curves of the satellite and satellite constellation similar to the detection results of photoelectric sensing are obtained, and the average error rate is only 1.6%. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0030] Figure 1 This is a flow chart of a method for measuring photometric spectra of low-orbit satellites and satellite constellations in near space according to an embodiment of the present invention;

[0031] Figure 2A schematic diagram comparing a numerical simulation calculation method and a photoelectric sensing calculation method according to an embodiment of the present invention;

[0032] Figure 3 A schematic diagram of relative errors of a numerical simulation calculation method and a photoelectric sensor calculation according to an embodiment of the present invention;

[0033] Figure 4 It is a front view schematic diagram of the flying position of the detector relative to the satellite and the satellite constellation when the motion direction of the detector in the embodiment of the present invention is consistent with that of the satellite and the satellite constellation;

[0034] Figure 5 A data model for meshing calculation of finite element simulation according to an embodiment of the present invention;

[0035] Figure 6 A front view of the flying position of the detector according to an embodiment of the present invention;

[0036] Figure 7 The diagram is a schematic diagram of light reflection between a satellite solar panel and a satellite body according to an embodiment of the present invention. DETAILED DESCRIPTION

[0037] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0038] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0039] like Figure 1 As shown, this embodiment discloses a near-space photometric spectrum measurement method for low-orbit satellites and satellite constellations, including: obtaining low-orbit satellite and satellite constellation models, and dividing the low-orbit satellite and satellite constellation models into two-dimensional facet grids; reconstructing the low-orbit satellite and satellite constellation models using the facet data after division, establishing different satellite and satellite constellation model scenes, simulating different scenes on a space analysis platform, and obtaining vector data of satellites and satellite constellations that change with solar altitude and azimuth angles; and calculating the photometric spectra of satellites and satellite constellations under different observation scenes based on the vector data in combination with a bidirectional reflectance distribution function (BRDF) model and an atmospheric radiation transmission model.

[0040] BRDF is the light source direction unit vector and the observer direction unit vector The function is defined as follows:

[0041]

[0042] Where the incident radiation brightness is L i , the outgoing radiance is L o ,φ i Defined as the surface normal and the light source vector The angle between o Defined as the surface normal and the observer vector The angle between.

[0043] Specifically, a method for measuring the photometric spectrum of a low-orbit satellite and a satellite constellation in near space includes the following steps:

[0044] 1. System construction and preparation:

[0045] Determine the research objectives and models: The research objectives are clearly defined as photometric and spectral measurements of low-orbit satellites and satellite constellations from near space, and the theoretical models and tools to be used are selected, including the bidirectional reflectance distribution function model and the atmospheric radiation transfer model.

[0046] Satellite structure and meshing: Related modeling software constructs three-dimensional models of low-orbit satellites and satellite constellations, and finite element processing software is used to perform two-dimensional meshing on the three-dimensional model surfaces of satellites and satellite constellations.

[0047] Model building and scene setting: Import the face data obtained after meshing into numerical calculation software to reconstruct the satellite and satellite constellation model. Use satellite and satellite constellation simulation calculation to set different satellite and satellite constellation observation scenes.

[0048] 2. System operation and parameter adjustment:

[0049] Application of the bidirectional reflectance distribution function model: The bidirectional reflectance distribution function model is combined with the atmospheric radiation transfer model, and the photometric spectra of satellites and satellite constellations under different observation scenarios are calculated and analyzed through numerical calculation software.

[0050] Bidirectional reflectance distribution function model coefficients and reflectivity adjustment: Adjust the bidirectional reflectance distribution function model coefficients of the satellite and satellite constellation surface materials to observe their impact on the photometric curve. The different materials of the satellite represent the changes in the reflection parameters, changing the specular reflectivity and diffuse reflectivity, and analyzing the impact of the material on the satellite's photometric characteristics, especially whether flickering occurs and its duration.

[0051] 3. Error analysis and summary:

[0052] Photoelectric sensor data acquisition: Use photoelectric sensors in satellite and satellite constellation simulation calculations to collect irradiance data and perform photometric calculations on satellites and satellite constellations.

[0053] Model comparison and verification: The surface materials of satellites and satellite constellations in the bidirectional reflectance distribution function model are adjusted to the materials of satellites and satellite constellations in the optoelectronic sensing, and the simulation calculation results are compared with the optoelectronic detection results.

[0054] Error analysis: simulate the error rate between the calculation results and the photoelectric detection results, analyze the source of the error, and ensure the accuracy and reliability of the measurement method.

[0055] Simulation calculation results: Organize the data and results obtained by the simulation calculation method, and summarize the photometric spectral characteristics of low-orbit satellites and satellite constellations at near-space observation altitudes.

[0056] Generate summary report: Based on the simulation calculations and analysis, write a detailed summary report, including research background, methods, results, discussion and conclusions.

[0057] 4. System maintenance and management:

[0058] Regular inspection and maintenance: Ensure that you take advantage of the latest features and performance optimizations. Regularly check and fix errors and vulnerabilities in the software to ensure that the system runs safely and stably.

[0059] Data management and backup: Organize, classify and archive the data generated by simulation calculations to facilitate subsequent data analysis and reuse. Establish a regular data backup mechanism, including system data, simulation calculation data and results, etc.

[0060] Model update and optimization: With the development of low-orbit satellite and satellite constellation technology and the accumulation of observation data, simulation calculation methods are regularly updated to improve simulation calculation accuracy. Simulation calculation models are optimized to reduce calculation time and improve simulation calculation efficiency.

[0061] Furthermore, establishing different satellite and satellite constellation model scenes includes: reconstructing low-orbit satellite and satellite constellation models using the divided face metadata, obtaining the rotation of the satellite and satellite constellation's solar panels following the sun vector and the shadow area of ​​the satellite and satellite constellation body; and establishing satellite and satellite constellation model scenes based on the rotation and shadow area.

[0062] Furthermore, the method also includes: adjusting the coefficients of the bidirectional reflection distribution function model, thereby adjusting the surface material of the satellite and satellite constellation to the material of the satellite and satellite constellation in the photoelectric sensor, observing the photometric curve of the bidirectional reflection distribution function model, and changing the mirror reflectivity and diffuse reflectivity, analyzing the photometric characteristics of the bidirectional reflection distribution function model, and obtaining simulation calculation results; using photoelectric sensors to collect irradiance data and perform photometric calculations on the satellite and satellite constellation, using the electro-optical infrared sensor system module on the aerospace analysis platform to extract the detection time and satellite photometric characteristics, and obtain photoelectric detection results; comparing the simulation calculation results with the photoelectric detection results, verifying the calculated photometric spectra of the satellite and satellite constellation under different observation scenarios.

[0063] Furthermore, analyzing the photometric characteristics of the bidirectional reflectance distribution function model includes: identifying contributing factors when analyzing the photometric characteristics of the Starlink satellite solar panels, and calculating the total solar flux and final brightness of the spacecraft based on the contributing factors.

[0064] Furthermore, the contributing factors include: diffuse reflection from the front surface of the solar panel, diffuse reflection from the rear surface of the solar panel, diffuse reflection from the bottom of the solar panel, and specular reflection from the bottom of the solar panel.

[0065] Furthermore, the diffuse reflection on the rear surface of the solar panel includes diffuse reflection of the exposed antenna and diffuse reflection outside the sunshade.

[0066] Specifically:

[0067] When analyzing the photometric characteristics of the Starlink satellite solar panels, this embodiment can identify four main contributing factors:

[0068] Diffuse reflection from the front surface of the solar panel: At least part of the reflection from the solar panel is diffuse, and this diffuse reflection component is modeled as Lambertian reflection. Therefore, the power of the solar panel is proportional to the cosine of the viewing angle of the solar panel, multiplied by the cosine of the solar angle of the solar panel (solar flux).

[0069] Diffuse reflection from the rear surface of the solar panel: Similar to contribution 1, this element is proportional to the negative value of the cosine of the viewing angle (PVA) of the solar panel (in this case the PVA is greater than 90°).

[0070] The diffuse reflection from the bottom of the solar panel consists of two parts: one is the reflection from the exposed antenna, which is considered as a Lambertian diffuse reflection, and its intensity is determined by the cosine of the bottom observation angle and the sine of the sun's altitude angle; the other is the area outside the sunshade, whose reflection intensity is proportional to the sine of the sun's angle. The model adds these two parts to obtain the total diffuse reflection flux from the bottom, and adjusts it according to the relative angle between the observer and the bottom.

[0071] Mirror reflection from the bottom of the solar panels: A large part of the bottom of the spacecraft has a mirror-like surface, which reflects a portion of the incident solar flux.

[0072] Based on the above information, the total solar flux (F) of the spacecraft and its final brightness (m visorsat ), by analyzing F, we can calculate the brightness of the satellite at different times and different positions of the sun and observer, convert F into apparent magnitude, and obtain a standardized brightness metric to compare the visibility of the satellite under different conditions. Modeled by formula 1 and formula 2:

[0073] F=a×cos(PVA)×cos(PSA)×BF

[0074] +b×cos(180-PVA)+(c×sin(SDA)×VE+d×((cosSOA) e )×cos(OBA)(1)

[0075] m visorsat = -2.5×log 10 (F) +f (2)

[0076] Among them, PVA is the panel observation angle, PSA is the solar phase angle, a is the diffuse reflectance parameter of the front of the solar panel, BF is the blocking factor, b is the reflectance of the back of the panel, c is the diffuse reflectance of the bottom of the body, VE is the sunshade efficiency, d is the mirror reflectance of the bottom of the body, SOA is the mirror beam deviation angle, OBA is the deviation from the baseline observation angle, the angle between the zenith line of the spacecraft and the observer direction, SDA is the solar depression angle, F is the total solar flux, and f is the constant used to calculate the apparent magnitude, where f is 7.2 m .

[0077] Where PVA (Panel Viewing Angle) and PSA (Solar Phase Angle) take into account PM (Panel Normal), POA (Sun Normal) and FA (Flight Path Angle), as well as the geometry of the spacecraft relative to the Sun and the observer.

[0078] The present embodiment discloses a near-space photometric and spectral measurement method for low-orbit satellites and satellite constellations, characterized in that the method includes: using the finite element method to perform two-dimensional facet meshing on the three-dimensional model of the satellite and the satellite constellation; reconstructing the satellite and satellite constellation model using the obtained facet data through numerical calculation software, and realizing the rotation of the satellite and satellite constellation solar panels following the sun vector and the calculation of the shadow area of ​​the satellite and satellite constellation body through an algorithm; using satellite and satellite constellation numerical simulation calculation method software to establish a satellite and satellite constellation model scene, and obtain vector data of the satellite and satellite constellation that changes with the sun's altitude angle and azimuth angle.

[0079] The finite element method provides a variety of mesh generation tools that can automatically generate structural meshes, shell meshes, and various types of volume meshes. When performing mesh division, users can choose different division methods, such as quadrilateral, triangle, or mixed division, to adapt to different geometric shapes and measurement accuracy requirements.

[0080] The numerical simulation calculation method software has efficient data processing capabilities, can process large amounts of data and perform complex mathematical operations. The numerical simulation calculation method software can generate and display the calculated satellite and satellite constellation model images, and can intuitively display the processing results.

[0081] Space vehicle dynamics calculation methods play an important role in the aerospace field with features such as vehicle orbit design and analysis, optoelectronic sensor calculation, three-dimensional visualization and vector analysis, observation of solar altitude and azimuth angle determination, data reporting and export, and coordinate system support.

[0082] Finite element calculation method: Geometric modeling and calculation model method: Supports geometric modeling of imported satellite structures and satellite constellation configurations, including automatic detection, as well as manual more detailed modeling. Meshing: Provides automatic and manual meshing functions, supporting multiple mesh classes to meet the needs of different complexity and accuracy.

[0083] Numerical simulation calculation methods: Data processing: import, analyze and visualize data. Support reading and writing different data formats, provide basic and complex statistical analysis functions, as well as data modeling, data conversion, etc. Graphics processing: process and analyze images, and provide tools to import, display, analyze and modify images. Functions include image reading, filtering, edge detection, image transformation, etc., which can be used for applications such as image analysis, feature extraction, and image enhancement.

[0084] Satellite and satellite constellation space vehicle dynamics calculation methods: 3D display: Provides high-precision 3D visualization and high-precision integrated data, providing a leading 3D display environment for space vehicle dynamics calculation methods and other additional.

[0085] Advanced Analysis: Interactive orbital maneuvering and deep space exploration planning tools for spacecraft operation and mission analysis, providing orbital maneuver solutions and optimization plans by defining thrust models, target ephemeris, spacecraft attitude, etc.

[0086] Improved analysis method of joint analysis: model building and facet segmentation: This embodiment uses actual satellite and satellite constellation models and performs facet segmentation on them. Compared with the simple combination of polyhedral geometric models, this method is more accurate. Through facet segmentation, the optical properties of the satellite and satellite constellation surfaces can be simulated more finely.

[0087] Parameter adjustment of numerical simulation calculation method: The influence of different detection altitudes and detector flight speeds on the photometric spectrum of satellites and satellite constellations under different scenarios, such as daytime conditions, full moon night conditions, and half-moon night conditions, was simulated and calculated, further verifying the adaptability and accuracy of the measurement system. The influence of different satellite and satellite constellation materials on the photometric spectrum characteristics was considered, and the influence of material changes on the photometric spectrum of satellites and satellite constellations was analyzed through numerical simulation calculations.

[0088] Data analysis and error comparison: Use the optoelectronic sensing calculation in the numerical simulation calculation method of satellites and satellite constellations to collect irradiance data and calculate the photometric spectrum of satellites and satellite constellations, and perform error comparison analysis with the results of the two-way scattering model.

[0089] The observation altitude is 60km, the detector flight speed is 1km / s, the detector azimuth angle is -180°, the pitch angle is -70°, the horizontal and vertical field of view angles are both 20°, and the exposure time is set to 500ms. By comparing the calculated results with the data calculated by the photoelectric sensor, the accuracy and reliability of the measurement results are verified, and the error rate is only 1.2%.

[0090] The combination of the above and improved analysis methods provides valuable technical support and theoretical basis for the photometric and spectral research of low-orbit satellites and satellite constellations.

[0091] like Figure 2-3 As shown, Figure 2-3 The comparison between numerical simulation and photoelectric sensing calculation methods and the relative error diagram between numerical simulation and photoelectric sensing calculation methods are shown respectively. The finite element method is a professional finite element processing software. The figure depicts that the software meshes the surface of the three-dimensional model of the satellite and satellite constellation, and then extracts its facet data, including the spatial coordinates of the facet center, the area size of the facet, and the facet normal vector data, in preparation for subsequent model construction and calculation.

[0092] like Figure 4 As shown, Figure 4 The diagram shows the front view of the probe's relative position to the satellite and satellite constellation when the probe and the satellite and satellite constellation are moving in the same direction. The satellite and satellite constellation are flying in the same direction as the probe, both perpendicular to the paper and facing inward. The parallel orbit of the spacecraft is determined by changing θ. From this diagram, it can be clearly seen that by changing the angle θ between the satellite and satellite constellation and the probe, it can be determined which side of the probe relative to the satellite and satellite constellation has a higher apparent magnitude of the satellite and satellite constellation.

[0093] The photometric spectrum measurement system covers the entire process from the construction of the satellite and satellite constellation model based on the segmentation of the surface element to the photometric spectrum measurement method of the low-orbit satellite and satellite constellation, such as Figure 5-7 As shown, Figure 5 Compute meshing data models for finite element simulations, Figure 6 This is the front view of the probe's flight position. Figure 7 This is a schematic diagram of the light reflection between the satellite solar panel and the satellite body.

[0094] The embodiments described above are only descriptions of the preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Without departing from the design spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by ordinary technicians in this field should all fall within the protection scope determined by the claims of the present invention.

Claims

1. A near-space photometric spectrum measurement method for low-orbit satellites and satellite constellations, characterized in that: include: Acquire a low-orbit satellite and satellite constellation model, and perform two-dimensional facet meshing on the low-orbit satellite and satellite constellation model; Reconstruct the low-orbit satellite and satellite constellation model using the divided face metadata, establish different satellite and satellite constellation model scenarios, simulate different scenarios on the aerospace analysis platform, and obtain vector data of satellites and satellite constellations that change with solar altitude angles and azimuth angles; According to the vector data, in combination with a bidirectional reflectance distribution function model and an atmospheric radiation transfer model, the photometric spectra of satellites and satellite constellations under different observation scenarios are calculated.

2. The near-space photometric spectrum measurement method for low-orbit satellites and satellite constellations according to claim 1 is characterized in that: The establishment of the different satellite and satellite constellation model scenarios includes: Reconstruct the low-orbit satellite and satellite constellation model using the divided face data to obtain the rotation of the solar panels of the satellite and the satellite constellation following the sun vector and the shadow area of ​​the satellite and the satellite constellation body; Based on the rotation and the shadow area, the satellite and satellite constellation model scene is established.

3. The near-space photometric spectrum measurement method for low-orbit satellites and satellite constellations according to claim 1 is characterized in that: The method further comprises: Adjust the bidirectional reflectance distribution function model coefficients, so as to adjust the surface materials of the satellite and the satellite constellation to the materials of the satellite and the satellite constellation in the photoelectric sensor, observe the photometric curve of the bidirectional reflectance distribution function model, change the specular reflectance and the diffuse reflectance, analyze the photometric characteristics of the bidirectional reflectance distribution function model, and obtain the simulation calculation results; Use photoelectric sensors to collect irradiance data and calculate photometric data for satellites and satellite constellations, and use electro-optical infrared sensor system modules on aerospace analysis platforms to extract detection time and satellite photometric characteristics to obtain photoelectric detection results; The simulation calculation results and the photoelectric detection results are used to verify the calculated photometric spectra of the satellite and satellite constellation under different observation scenarios.

4. The near-space photometric spectrum measurement method for low-orbit satellites and satellite constellations according to claim 3 is characterized in that: Analyzing the photometric characteristics of the bidirectional reflectance distribution function model includes: When analyzing the photometric characteristics of the Starlink satellite solar panels, contributing factors are identified, and based on the contributing factors, the total solar flux and final brightness of the spacecraft are calculated.

5. The near-space photometric spectrum measurement method for low-orbit satellites and satellite constellations according to claim 4 is characterized in that: The contributing factors include diffuse reflection from the front surface of the solar panel, diffuse reflection from the rear surface of the solar panel, diffuse reflection from the bottom of the solar panel, and specular reflection from the bottom of the solar panel.

6. The near-space photometric spectrum measurement method for low-orbit satellites and satellite constellations according to claim 5 is characterized in that: The diffuse reflection on the rear surface of the solar panel includes diffuse reflection of the exposed antenna and diffuse reflection outside the sunshade.

7. The near-space photometric spectrum measurement method for low-orbit satellites and satellite constellations according to claim 4 is characterized in that: The formula for calculating the total solar flux for the spacecraft is: F=a×cos(PVA)×cos(PSA)×BF+b×cos(180-PVA)+(c×sin(SDA)×VE+d×((cosSOA)°)×cos(OBA) Among them, PVA is the panel observation angle, PSA is the solar phase angle, a is the diffuse reflectance parameter of the front of the solar panel, BF is the blocking factor, b is the reflectance of the back of the panel, c is the diffuse reflectance of the bottom of the body, VE is the sunshade efficiency, d is the specular reflectance of the bottom of the body, SOA is the specular beam deviation angle, OBA is the deviation from the baseline observation angle, the angle between the zenith line of the spacecraft and the observer direction, and SDA is the solar depression angle.

8. The near-space photometric spectrum measurement method for low-orbit satellites and satellite constellations according to claim 4 is characterized in that: Calculating the final brightness of the spacecraft involves: mvisorsa t =-2.5×log 10 (F)+f Among them, F is the total solar flux and f is a constant used to calculate the apparent star.

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