Remote sensing satellite closed loop tracking verification system and method for supersonic weak and small target tracking

Abstract

The application discloses a kind of for hypersonic weak small target tracking remote sensing satellite closed loop tracking verification system and method, the system includes: image generator, for according to the real-time pointing simulation remote sensing satellite in orbit working scene of tracking turntable corresponding simulation view image and the processing result generated by receiving main control platform;View simulator, for receiving simulation view image, and view image is projected onto screen;Payload simulator, obtain the simulation image consistent with the real scene corresponding to the remote sensing satellite in orbit working scene;Image framing and transmission module, the image data generated after splicing frame is transmitted to information processor according to transmission protocol;Main control platform, from the image framing and transmission module acquire the image generated after splicing frame and the auxiliary information, processing result is sent to image generator, payload simulator.The system of the application, simulation has higher detail richness, confidence is high, as far as possible realizes consistency with in-orbit state.

Description

Technical Field

[0001] This invention relates to the field of semi-physical simulation of remote sensing satellites, specifically to a closed-loop tracking verification system and method for tracking supersonic weak targets using remote sensing satellites. Background Technology

[0002] As the application scenarios and modes of remote sensing satellites become increasingly complex, in order to maximize the utilization of the satellite's field of view and imaging capabilities, close cooperation between the onboard rotating mechanism and the camera is required to meet the diverse payload operating mode requirements. Currently, a high-confidence physical simulation system for joint acquisition and tracking of high-speed, weak targets in space using a spaceborne camera and turntable is still lacking.

[0003] Therefore, verifying the high-speed, small-target closed-loop tracking process achieved through the combined imaging of the remote sensing satellite's rotating mechanism and camera is an essential step. However, for large remote sensing satellites, the rotating mechanism and camera are too large and heavy to be tested in conventional tests, and can only be analyzed through numerical simulation. The limitation of theoretical analysis is that the simulation of various errors is flawed, resulting in significant differences from the actual closed-loop process.

[0004] In summary, it is necessary to build a closed-loop tracking system for remote sensing satellites oriented towards high-speed target tracking in the semi-physical simulation of remote sensing satellites. This system can more realistically reflect the closed-loop tracking effect of remote sensing satellite payloads on targets under various working modes, and provide an effective means for the design verification of remote sensing satellites. Summary of the Invention

[0005] In view of this, the present invention provides a closed-loop tracking verification system and method for tracking supersonic weak targets using remote sensing satellites, which can solve the problem of functional performance verification under various working modes of remote sensing satellite payloads.

[0006] To address the aforementioned technical problems, this invention is implemented as follows: This invention provides a semi-physical simulation scheme for verifying the operating modes of a remote sensing satellite payload in a closed-loop tracking system for high-speed target tracking. This system combines a rotating mechanical mechanism with an optical system in a collaborative design to achieve a semi-physical simulation system for automatic target tracking and aiming. Digital images are resampled using an optical camera, and target position information is obtained through image information processing. Then, a control system controls the turntable mechanism to achieve automatic target tracking and aiming. This completes the closed-loop verification of the functional performance of the remote sensing satellite payload under various operating modes. This invention verifies the functional performance of the closed-loop tracking effect of the remote sensing satellite payload under various operating modes.

[0007] A remote sensing satellite closed-loop tracking verification system for supersonic, weak target tracking, the system comprising:

[0008] The image generator is used to simulate the visual scene image corresponding to the on-orbit operation scenario of the remote sensing satellite based on the real-time pointing of the tracking turntable, and to receive the processing results generated by the main control platform; the simulated visual scene image content includes the ground background, the air background, and the supersonic weak target;

[0009] A visual simulator is used to receive the simulated visual image and project the visual image onto a screen.

[0010] The payload simulator includes a turntable and a camera fixed to the turntable; the camera acquires images displayed on the screen, and the images are preprocessed to obtain a simulated image that corresponds to the real scene of the remote sensing satellite's on-orbit operation; the tracking turntable is used to track the supersonic weak target;

[0011] The image framing and transmission module is used to receive the simulated image, frame the simulated image and the auxiliary information corresponding to the simulated image according to the satellite format, and transmit the image data generated after framing to the main control platform according to the transmission protocol.

[0012] The main control platform is used to collect and distribute information from each simulator and generate control signals to each simulator; it obtains the image generated after frame stitching and the auxiliary information from the image framing and transmission module, sends the processing results to the image generator, and provides the image generator with the data required for the next frame simulation; it generates control information to control the rotation of the camera turntable.

[0013] Preferably, the image generator includes a target data calculation submodule and a background data calculation submodule;

[0014] The target data calculation submodule is used to determine the expected specific position, resolution, and radiation characteristics of the supersonic weak target in the simulated visual image based on the real-time pointing of the tracking turntable and the real-time position of the supersonic weak target, and to superimpose the supersonic weak target on the background of the simulated visual image.

[0015] The background data calculation submodule performs inversion based on real images acquired under the existing remote sensing satellite in-orbit working scenarios to generate the Earth background and edge background of the simulated visual image; it selects observed stars based on the star catalog to generate the air background of the simulated visual image.

[0016] Preferably, the step of inverting real images acquired under existing remote sensing satellite on-orbit operating scenarios to generate the Earth background and edge background of the simulated visual image includes:

[0017] The original background base map is selected from the visual images corresponding to several on-orbit working scenarios. The imaging band of each original background image is determined. If the imaging band is consistent, the radiance inversion is performed to obtain the radiance distribution at the camera entrance pupil. Otherwise, the temperature field distribution of the corresponding background is inverted according to each original background base map. Based on the different emissivity of different land cover types in different spectral bands, the radiance distribution at the camera entrance pupil is obtained.

[0018] The radiance distribution, atmospheric transmittance, and background radiance at the camera's entrance pupil are dynamically superimposed to obtain the scene radiance distribution within the payload's field of view. The grayscale image within the payload's field of view is then determined. The simulation inversion result of the remote sensing image of the ground scene is used as the ground background of the visual image, and the simulation inversion result of the remote sensing image containing the edge background is used as the edge background of the visual image.

[0019] Preferably, the step of selecting observed stars based on a star catalog to generate the aerial background of the visual image includes:

[0020] Based on the star catalog, a number of observed stars are selected, and each observed star is used as a candidate star point. The magnitude of each candidate star point is transformed into the gray value on the corresponding image plane.

[0021] The process of transforming the magnitude values ​​of candidate stars into corresponding grayscale values ​​on the image plane includes:

[0022] The gray-level distribution of the light spot of the candidate star point is approximated by a two-dimensional Gaussian distribution function, as shown in the following expression:

[0023]

[0024] In the formula, B represents the maximum gray value of the star point, (x0,y0) are the coordinates of the center point of the Gaussian distribution, (x,y) are the coordinates of the pixels adjacent to the center point of the Gaussian distribution in the image, and σ is the standard deviation.

[0025]

[0026] Where m is the magnitude value of the candidate star point.

[0027] Preferably, the visual simulator includes a projection blending control module, multiple projection devices, and a spherical projection screen;

[0028] The projection device is used to form a projected image and, based on the signal sent by the projection fusion control module, performs geometric correction and adjusts color difference.

[0029] The projection fusion control module is used to set a grid on the spherical projection screen, eliminate various projection fusion bands, perform edge feathering and geometric correction on the projection fusion bands, and perform multi-point joint fine-tuning on the points on the grid using geometric alignment calibration test images to generate a large-view projection image corresponding to the simulated visual image.

[0030] The present invention provides a remote sensing satellite closed-loop tracking verification method for supersonic weak target tracking. The method is based on the aforementioned remote sensing satellite closed-loop tracking verification system for supersonic weak target tracking, and includes the following steps:

[0031] Step S1: The image generator generates a simulated visual image based on the turntable pointing information and target position information sent by the main control platform;

[0032] Step S2: Project the simulated visual image through the visual generator;

[0033] Step S3: Reacquire the projected image using a camera mounted on the turntable;

[0034] Step S4: Input the re-acquired image from the camera into the image framing and transmission module, and send the framed image to the main control platform for processing;

[0035] Step S5: The main control platform distributes the processing results to the image generator and controls the turntable through commands to verify the remote sensing satellite closed-loop tracking system for supersonic weak target tracking.

[0036] The present invention provides a computer-readable storage medium storing a plurality of instructions; the plurality of instructions are used by a processor to load and execute the method as described above.

[0037] The present invention provides an electronic device, characterized in that the electronic device comprises:

[0038] A processor is used to execute multiple instructions;

[0039] Memory, used to store multiple instructions;

[0040] The plurality of instructions are to be stored in the memory and loaded and executed by the processor as described above.

[0041] Beneficial effects:

[0042] (1) The simulation process of this invention has high detail richness and the confidence level of the whole system is high, achieving consistency with the on-orbit state as much as possible. The simulated image source used in this invention is generated by inverting the measured images of the camera on orbit, and the simulation considers the degradation of optical system, degradation of detector and electronic circuit and platform flutter degradation, etc., and has a high degree of consistency with the on-orbit image source.

[0043] (2) This invention has an interface consistent with that of a real satellite. The system's input and output interfaces are consistent with those of a real satellite in terms of interface type and data format, and can be connected to upper and lower level modules for equivalent verification.

[0044] (3) The visual simulator of the present invention adopts spherical projection technology. The spherical screen can effectively reduce imaging distortion and improve the imaging orientation of the turntable. The simulation of the field of view and image size is strongly correlated with the actual load index parameters, and can reflect the working state of different loads more realistically.

[0045] (4) The visual effect of the system of the present invention is intuitive. The present invention can output and display the working results of the load in a set scenario in real time, and the display effect of the results is very intuitive. Attached Figure Description

[0046] Figure 1 This is a schematic diagram of the architecture of the remote sensing satellite closed-loop tracking verification system for supersonic weak target tracking provided by the present invention.

[0047] Figure 2 This is a simulation diagram of the imaging link provided by the present invention;

[0048] Figure 3 This is a schematic diagram of the measured ground feature inversion process provided by the present invention;

[0049] Figure 4 This is a schematic diagram of the stellar target simulation process provided by the present invention;

[0050] Figure 5 This is a schematic diagram of visual correction and fusion provided by the present invention;

[0051] Figure 6 A schematic diagram of the latitude and longitude angles of the simulated dome screen overlap area provided by the present invention;

[0052] Figure 7 This is a schematic diagram of the simulated camera, visual scene, and ideal observation area provided by the present invention;

[0053] Figure 8 This is a schematic diagram of the image data structure provided by the present invention. Detailed Implementation

[0054] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0055] like Figure 1 As shown, this invention proposes a remote sensing satellite closed-loop tracking verification system for supersonic weak target tracking. The system includes an image generator, a visual simulator, a payload simulator, an image framing and transmission module, and a main control platform.

[0056] The image generator is used to simulate the visual scene image corresponding to the on-orbit operation scenario of the remote sensing satellite based on the real-time pointing of the tracking turntable, and to receive the processing results generated by the main control platform; the simulated visual scene image content includes the ground background, the air background, and the supersonic weak target.

[0057] The visual simulator is used to receive the simulated visual image and project the visual image onto the screen;

[0058] The payload simulator includes a turntable and a camera fixed to the turntable; the camera acquires images displayed on the screen, and the images are preprocessed to obtain a simulated image that corresponds to the real scene of the remote sensing satellite's on-orbit operation; the tracking turntable is used to track the supersonic weak target;

[0059] The image framing and transmission module is used to receive the simulated image, assemble the simulated image and the auxiliary information corresponding to the simulated image into frames according to the satellite format, and transmit the image data generated after framing to the main control platform according to the transmission protocol.

[0060] The main control platform is used to collect and distribute information from each simulator and generate control signals to each simulator; it obtains the image generated after frame stitching and the auxiliary information from the image framing and transmission module, sends the processing results to the image generator, and provides the image generator with the data required for the next frame simulation; it generates control information to control the rotation of the camera turntable.

[0061] This invention relates to a high-speed target tracking closed-loop tracking verification system for remote sensing satellites, applied in a semi-physical simulation system for remote sensing satellites to demonstrate the process of a turntable mechanism and camera jointly capturing a target. Functionally, this invention can be divided into an image generator, a scene simulator, a payload simulator, and an image framing and transmission module. The specific working process is as follows: The scene simulator receives the scene image generated by the image generator and displays it through a projection device. Subsequently, the payload simulator acquires a portion of the scene image, and after certain preprocessing, obtains a simulated image consistent with the scene captured by the onboard camera in orbit, where the target position, radiation characteristics, etc., are consistent with the real scene. The result is transmitted to the image framing and transmission module. Finally, the image transmission module frames the image data and auxiliary data according to the onboard protocol. The resulting image data is then transmitted to the main control platform via a 2711 board according to the actual satellite transmission protocol.

[0062] Furthermore, the image generator includes a target data calculation submodule and a background data calculation submodule. Each submodule can directly call the target radiation characteristic data and background radiation characteristic data in the database to synthesize infrared image data within each detector scene in real time. The link simulation process for generating the infrared image data is as follows: Figure 2 As shown.

[0063] The target data calculation submodule is used to determine the expected specific position, resolution, and radiation characteristics of the supersonic weak target in the simulated visual image based on the real-time pointing of the tracking turntable and the real-time position of the supersonic weak target, and to superimpose the supersonic weak target on the background of the simulated visual image.

[0064] The background data calculation submodule performs inversion based on real images acquired under the existing remote sensing satellite in-orbit working scenarios to generate the Earth background and edge background of the simulated visual image; it selects observed stars based on the star catalog to generate the air background of the simulated visual image.

[0065] Furthermore, such as Figure 3 As shown, the process of inverting real images acquired under existing remote sensing satellite on-orbit operating scenarios to generate the Earth background and edge background of the simulated visual image includes:

[0066] The original background base map is selected from the visual images corresponding to several on-orbit working scenarios. The imaging band of each original background image is determined. If the imaging band is consistent, the radiance inversion is performed to obtain the radiance distribution at the camera entrance pupil. Otherwise, the temperature field distribution of the corresponding background is inverted according to each original background base map. Based on the different emissivity of different land cover types in different spectral bands, the radiance distribution at the camera entrance pupil is obtained.

[0067] The radiance distribution, atmospheric transmittance, and background radiance at the camera's entrance pupil are dynamically superimposed to obtain the scene radiance distribution within the payload's field of view. The grayscale image within the payload's field of view is then determined. The simulation inversion result of the remote sensing image of the ground scene is used as the ground background of the visual image, and the simulation inversion result of the remote sensing image containing the edge background is used as the edge background of the visual image.

[0068] Furthermore, the selection of observed stars based on the star catalog, and the generation of the aerial background for the visual image, includes:

[0069] Based on the star catalog, a number of observed stars are selected, and each observed star is used as a candidate star point. The magnitude of each candidate star point is transformed into the gray value on the corresponding image plane.

[0070] Furthermore, the magnitude values ​​of the candidate stars are transformed into grayscale values ​​on the corresponding image plane, including:

[0071] The gray-level distribution of the light spot of the candidate star point is approximated by a two-dimensional Gaussian distribution function, as shown in the following expression:

[0072]

[0073] In the formula, B represents the maximum gray value of the star point, (x0,y0) are the coordinates of the center point of the Gaussian distribution, (x,y) are the coordinates of the pixels adjacent to the center point of the Gaussian distribution in the image, and σ is the standard deviation.

[0074]

[0075] Where m is the magnitude value of the candidate star. This embodiment achieves a higher brightness and grayscale value when the magnitude value is smaller.

[0076] In this invention, the azimuth and brightness of stars can be obtained from star catalogs. The SAO star catalog used contains 258,997 stars. Since the standard star catalog has a large amount of data, including much information not needed for image generation, when creating simulated starscapes, data is usually not directly read from the standard star catalog. Instead, a sub-star catalog is edited, and simulation is performed based on this sub-star catalog. Each star in the sub-star catalog is a star point. The right ascension and declination values ​​of the star points in the celestial coordinate system are converted to coordinate values ​​in the image plane coordinate system, completing the selection of the observed stars. Based on the transformation relationship between magnitude and grayscale, the magnitude values ​​of candidate star points in the star catalog are transformed into corresponding grayscale values ​​on the image plane. Since the image formed by the optical system of star points is centered on the star's position, and the energy distribution follows a point spread function model, it is necessary to defocus the star image points so that the energy of the image points is dispersed within 5×5 pixels. The process of stellar target simulation is as follows: Figure 4 As shown.

[0077] The pixel size occupied by a star point is related not only to the brightness of the star but also to the point spread function of the optical system. The grayscale distribution of the star point spot is determined by the point spread function, which can be approximated using a two-dimensional Gaussian distribution function.

[0078] The visual simulator includes a projection fusion control module, multiple projection devices, and a spherical projection screen.

[0079] The projection device is used to form a projected image and, based on the signal sent by the projection fusion control module, performs geometric correction and adjusts color difference.

[0080] The projection fusion control module is used to set a grid on the spherical projection screen, eliminate various projection fusion bands, perform edge feathering and geometric correction on the projection fusion bands, and perform multi-point joint fine-tuning on the points on the grid using geometric alignment calibration test images to generate a large-view projection image corresponding to the simulated visual image.

[0081] Geometric correction of the projection fusion band, including:

[0082] Based on the distribution of each projection device, the angle and area projected by each projection device are determined. Then, the spherical projection screen is divided into grids at preset angle intervals using latitude and longitude. The misaligned geometric images are corrected one by one according to the grid. Based on the geometric positional relationship between the mutual projection fusion zones, the splicing and alignment of the projection fusion zones are achieved.

[0083] The spherical projection screen is used to display the wide-view, high-resolution projected image.

[0084] In this embodiment, the geometric features of a graphic can be described by low-level features and high-level features. Low-level features include edges and corners, while high-level features can describe the relationship between object recognition and image features. When multiple projectors simultaneously project onto a dome screen, image overlap occurs. In ordinary planar projection, the image can be evenly distributed across the projection screen without geometric misalignment. However, due to the irregularity of dome projection compared to planar projection, the projection light rays cannot be evenly distributed on the projection screen, resulting in a certain degree of misalignment in the projected image and corresponding image distortion. Therefore, a "meshization" method is used to correct the misaligned geometric images, analyze the geometric positional relationship between mutually projected images, and achieve grid alignment of edge images.

[0085] According to the design requirements, the angle and area projected by each projector can be determined by the projector distribution. Therefore, the entire spherical screen is divided into a grid using latitude and longitude at certain angles. The grid division result is as follows: Figure 6 As shown, the entire projection screen is divided into several grids containing several intersection points. Using the fusion software installed on the projection fusion server, the points on the grid are finely adjusted in a multi-point manner, thereby generating a natural-looking wide-angle projection image on the dome screen.

[0086] In addition to geometric correction, the visual simulator needs to consider color correction and edge brightness correction during the projection process. Furthermore, the projection device adjusts color difference in the following way:

[0087] In this embodiment, in a multi-channel projection system composed of multiple projection devices, color inconsistencies between projectors can lead to noticeable tonal transitions between images projected by different projectors. The color response of pixels projected by the same projector differs only in brightness; their color gamut and gradation responses are relatively similar. Therefore, the output characteristics of each projector can be approximated using a signal response function of the RGB color gamut and three primary colors. A theoretical model is derived through mathematical reasoning, and after embedding this mathematical model into software, color correction can be easily performed using the software.

[0088] Since the coverage areas of multiple projection devices overlap, edge brightness transition processing is required to ensure that the brightness of the transition area does not change abruptly.

[0089] In this embodiment, when a multi-channel projection system composed of multiple projection devices performs multi-channel projection fusion, a certain range of fusion area is specified. The area where the projection of each projection device overlaps with the multi-channel projection system is defined as the fusion area. In this embodiment, 20% of the projection area of ​​each projection device is defined as the fusion area. Each fusion area corresponds to two projection devices. Within the fusion area, as the projection area of ​​the first projection device corresponding to the fusion area moves towards the projection area of ​​the second projection device corresponding to the fusion area, the brightness output by the first projection device gradually dims, and the brightness output by the second projection device gradually brightens. Furthermore, the sum of the brightness of the first projection device and the second projection device is always equal to 1.

[0090] The payload simulator includes a camera and a fixed turntable. The camera is used to simulate imaging by a real onboard camera. The turntable is used to receive rotation commands from the main control platform and rotate to a specific angle so that the camera can image a specific area.

[0091] The image framing and transmission module includes an image preprocessing submodule and an image framing and transmission submodule. The image preprocessing submodule is used to segment and crop, correct distortion, and process deviations in the images sampled by the camera.

[0092] The image framing and transmission module is used to receive the simulated images generated by the payload simulator, and to frame the simulated images and the auxiliary information corresponding to the simulated images according to the satellite format; and to transmit the image data generated after framing to the main control platform according to the transmission protocol.

[0093] The image data includes auxiliary data, valid image data, and pointing angle data. The auxiliary data is obtained from the main control platform, and the valid image data is obtained from the load simulator. The auxiliary data and valid image data are then processed according to... Figure 8 The methods are combined to form a transmitted binary code stream. For example... Figure 8As shown in the figure, x, y, and k represent the number of rows, columns, and rows occupied by the pointing angle data in a single frame of the image, respectively.

[0094] In this embodiment, the image format of each channel is described according to the state of the camera channel of each subsystem of the camera subsystem, including the detector coordinate definition, detector size, the relationship between the arrangement order of the stitched detectors and the data arrangement method, etc.

[0095] A remote sensing satellite closed-loop tracking verification method for supersonic weak target tracking, the method being based on the aforementioned remote sensing satellite closed-loop tracking verification system for supersonic weak target tracking, the method comprising the following steps:

[0096] Step S1: The image generator generates a simulated visual image based on the turntable pointing information and target position information sent by the main control platform;

[0097] Step S2: Project the simulated visual image through the visual generator;

[0098] Step S3: Reacquire the projected image using a camera mounted on the turntable;

[0099] Step S4: Input the re-acquired image from the camera into the image framing and transmission module, and send the framed image to the main control platform for processing;

[0100] Step S5: The main control platform distributes the processing results to the image generator and controls the turntable through commands to verify the remote sensing satellite closed-loop tracking system for supersonic weak target tracking.

[0101] The specific embodiments described above only illustrate the design principles of the present invention. The shapes and names of the components in this description may differ and are not limited. Therefore, those skilled in the art can modify or make equivalent substitutions to the technical solutions described in the foregoing embodiments; and these modifications and substitutions do not depart from the inventive spirit and technical solutions of the present invention, and should all fall within the protection scope of the present invention.

Claims

1. A remote sensing satellite closed-loop tracking verification system for supersonic tracking of weak targets, characterized in that, The system includes: The image generator is used to simulate the visual scene image corresponding to the on-orbit operation scenario of the remote sensing satellite based on the real-time pointing of the tracking turntable, and to receive the processing results generated by the main control platform; the simulated visual scene image content includes the ground background, the air background, and the supersonic weak target; A visual simulator is used to receive the simulated visual image and project the visual image onto a screen. The payload simulator includes a turntable and a camera fixed to the turntable; the camera acquires images displayed on the screen, and the images are preprocessed to obtain a simulated image that corresponds to the real scene of the remote sensing satellite's on-orbit operation; the tracking turntable is used to track the supersonic weak target; The image framing and transmission module is used to receive the simulated image, frame the simulated image and the auxiliary information corresponding to the simulated image according to the satellite format, and transmit the image data generated after framing to the main control platform according to the transmission protocol. The main control platform is used to collect and distribute information from each simulator and generate control signals to each simulator; it obtains the image generated after frame stitching and the auxiliary information from the image framing and transmission module, sends the processing results to the image generator, and provides the image generator with the data required for the next frame simulation; it generates control information to control the rotation of the camera turntable. The image generator includes a target data calculation submodule and a background data calculation submodule; The target data calculation submodule is used to determine the expected specific position, resolution, and radiation characteristics of the supersonic weak target in the simulated visual image based on the real-time pointing of the tracking turntable and the real-time position of the supersonic weak target, and to superimpose the supersonic weak target on the background of the simulated visual image. The background data calculation submodule performs inversion based on real images acquired under the existing remote sensing satellite in-orbit working scenarios to generate the Earth background and edge background of the simulated visual image; it selects observed stars based on the star catalog to generate the air background of the simulated visual image. The process involves inverting real images acquired from existing remote sensing satellites in orbit to generate the simulated visual image's Earth background and edge background, including: The original background base map is selected from the visual images corresponding to several on-orbit working scenarios. The imaging band of each original background image is determined. If the imaging band is consistent, the radiance inversion is performed to obtain the radiance distribution at the camera entrance pupil. Otherwise, the temperature field distribution of the corresponding background is inverted according to each original background base map. Based on the different emissivity of different land cover types in different spectral bands, the radiance distribution at the camera entrance pupil is obtained. The radiance distribution, atmospheric transmittance, and background radiance at the camera entrance pupil are dynamically superimposed to obtain the scene radiance distribution within the payload's field of view, and the grayscale image within the payload's field of view is determined. The simulation inversion result of the remote sensing image of the ground scene is used as the ground background of the scene image, and the simulation inversion result of the remote sensing image containing the edge background is used as the edge background of the scene image. The process of selecting observed stars based on a star catalog to generate the spatial background of the visual image includes: Based on the star catalog, a number of observed stars are selected, and each observed star is used as a candidate star point. The magnitude of each candidate star point is transformed into the gray value on the corresponding image plane. The process of transforming the magnitude values ​​of candidate stars into corresponding grayscale values ​​on the image plane includes: The gray-level distribution of the light spot of the candidate star point is approximated by a two-dimensional Gaussian distribution function, as shown in the following expression: In the formula, B represents the maximum gray value of the star point. The coordinates of the center point of the Gaussian distribution are: Let be the coordinates of the pixels near the center point of the Gaussian distribution in the image. Standard deviation; Where m is the magnitude value of the candidate star point.

2. The system as described in claim 1, characterized in that, The visual simulator includes a projection fusion control module, multiple projection devices, and a spherical projection screen. The projection device is used to form a projected image and, based on the signal sent by the projection fusion control module, performs geometric correction and adjusts color difference. The projection fusion control module is used to set a grid on the spherical projection screen, eliminate various projection fusion bands, perform edge feathering and geometric correction on the projection fusion bands, and perform multi-point joint fine-tuning on the points on the grid using geometric alignment calibration test images to generate a large-view projection image corresponding to the simulated visual image.

3. A method for verifying closed-loop tracking of a remote sensing satellite for tracking supersonic weak targets, the method being based on the remote sensing satellite closed-loop tracking verification system for tracking supersonic weak targets as described in claim 1 or 2, the method comprising the following steps: Step S1: The image generator generates a simulated visual image based on the turntable pointing information and target position information sent by the main control platform; Step S2: Project the simulated visual image through the visual generator; Step S3: Reacquire the projected image using a camera mounted on the turntable; Step S4: Input the re-acquired image from the camera into the image framing and transmission module, and send the framed image to the main control platform for processing; Step S5: The main control platform distributes the processing results to the image generator and controls the turntable through commands to verify the remote sensing satellite closed-loop tracking system for supersonic weak target tracking.

4. A computer-readable storage medium storing a plurality of instructions; the plurality of instructions being loaded by a processor and executing the method of claim 3.

5. An electronic device, characterized in that, The electronic device includes: A processor is used to execute multiple instructions; Memory, used to store multiple instructions; The plurality of instructions are to be stored in the memory and loaded and executed by the processor as described in claim 3.

Images