Method, device and equipment for simulating optical imaging of space target by satellite-borne sensor and medium

Abstract

The invention discloses an optical imaging simulation method, device and equipment for space targets by a satellite-borne sensor and a medium. The method comprises the following steps: constructing a field-of-view model, performing visibility screening on fixed stars and all space targets detected in the field-of-view model, establishing a reference plane along the center field-of-view direction of an observation satellite, and transferring the field-of-view model to the reference plane; all visible fixed star and space target J2000 positions are converted to a reference plane; and calculating the size and the brightness of equivalent pixel points according to the space target and the star equivalence of the fixed star, and drawing a simulation image. According to the method, view field model construction and visibility analysis are adopted, visibility judgment of the super-large-scale fixed star and the space target is processed, the calculation speed is increased, the calculation efficiency is improved, and the real-time requirement of a large-scale space situation simulation system is effectively met.

Description

Technical Field

[0001] The present invention relates to the technical field of optical imaging of space targets by spaceborne sensors, and particularly to an optical imaging simulation method, device, equipment and medium for spaceborne sensors to space targets. Background Technique

[0002] The optical imaging simulation of space targets is a common business function in the field of aerospace simulation. The common simulation method is based on three-dimensional digital earth engines such as OSGEarth or Cesium. Using the viewing angle function in the platform, the position data of the target and the observer are set, and the image of the viewing angle screen is intercepted. The disadvantage of this method is that the imaging algorithm needs to rely on a heavyweight three-dimensional engine, resulting in the imaging algorithm occupying a high amount of computer resources. On the other hand, if hundreds of thousands of star data need to be loaded to simulate the real star background, the efficiency for large-scale star data is low, which will greatly reduce the display efficiency.

[0003] For example, the invention application with the application number 202410127537.8 discloses a space target optical imaging simulation method and system. This application scheme can establish the position and attitude relationship between the space target and the observation equipment by simulating the optical imaging simulation scene. Combining the parameters of the observation equipment, under the support of OpenGL, the geometric simulation of the optical imaging of the aerial target is realized by adjusting the position and direction of the viewpoint, so as to assist in analyzing the situation of the aerial target, and has good application prospects. However, its scheme also has the problems that it cannot process the simulation imaging of hundreds of thousands of star data, and the imaging algorithm occupies a high amount of computer resources.

[0004] Therefore, for systems with higher real-time requirements in reality, a new method is needed to improve the simulation calculation efficiency while reducing the occupation of computing resources, and to realize the processing of simulation imaging data of large-scale space targets. Summary of the Invention

[0005] Aiming at the above existing problems, the purpose of the present invention is to provide an optical imaging simulation method, device, equipment and medium for spaceborne sensors to space targets, to realize the optical imaging simulation of hundreds of thousands of stars and space targets, and reduce the occupation of computing resources.

[0006] The embodiments of the present invention provide an optical imaging simulation method, device, equipment and medium for spaceborne sensors to space targets.

[0007] First aspect: An optical imaging simulation method for spaceborne sensors to space targets, including:

[0008] S1. Obtain the field of view parameters of the satellite payload, construct a field of view model, and calculate the J2000 coordinate positions of the vertices A, B, C, and D of the field of view model.

[0009] S2. Perform visibility screening on the detected stars and all space targets within the field-of-view model, and record the J2000 positions and star numbers of the visible stars and space targets within the field-of-view model;

[0010] S3. The observation satellite establishes a reference plane along the central field-of-view direction, and rotates the vertices ABCD of the field-of-view model to the reference plane to obtain vertices A'B'C'D';

[0011] S4. Convert the J2000 positions of all visible stars and space targets to the reference plane;

[0012] S5. Calculate the equivalent pixel sizes and brightnesses according to the stellar magnitudes of the space targets and stars, and draw a simulation image.

[0013] Optionally, when performing visibility screening on the detected stars within the field-of-view model, the influence of lighting conditions is considered.

[0014] Optionally, the origin of coordinates of the reference plane is located at the vertex, so that the coordinate values displayed on the reference plane are positive.

[0015] Optionally, the formula for obtaining the stellar magnitude is:

[0016] m obj = m sun -2.5log(ρ·σ0 / R 2 )

[0017]

[0018] where, m sun = -26.73 is the solar apparent magnitude; R is the target distance; ρ is the reflectivity; σ0 is the target cross-sectional area; d is the target diameter; is the phase angle.

[0019] Optionally, when drawing the simulation image in S5, the coordinates of the reference plane are scaled and transformed according to the resolution of the generated image.

[0020] Optionally, when drawing the simulation image in S5, the equivalent pixel sizes and brightnesses of the stars and space targets are calculated according to the stellar magnitudes of the space targets and stars and the resolution of the generated image.

[0021] Second aspect: An optical imaging simulation device for a space target by a spaceborne sensor, comprising:

[0022] A field-of-view construction module, configured to construct a field-of-view model according to the field-of-view parameters of the satellite payload, and calculate the J2000 coordinate positions of the vertices ABCD of the field-of-view model;

[0023] A screening and generation module for performing visibility screening on stars and all space targets within the field of view model, and recording the J2000 positions and star numbers of the visible stars and space targets;

[0024] A reference plane module for establishing a reference plane along the direction of the central field of view of the observation satellite, and transferring the vertices ABCD of the field of view model to the reference plane to obtain the vertices A'B'C'D';

[0025] A projection conversion module for converting the J2000 positions of all visible stars and space targets to the reference plane;

[0026] A drawing and generation module for obtaining the magnitude values of space targets and stars, calculating the equivalent pixel point sizes and brightnesses, and drawing a simulation image.

[0027] In a third aspect: An electronic device includes a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the program, the steps of the method provided in the first aspect are implemented.

[0028] In a fourth aspect: A non-transitory computer-readable storage medium stores a computer program thereon. When the computer program is executed by a processor, the steps of the method provided in the first aspect are implemented.

[0029] Advantages of the present invention:

[0030] 1. By adopting a parallel computing architecture for field of view model construction and visibility analysis, the present invention processes the visibility judgment of stars and space targets. Compared with the serial computing mode of traditional 3D engines, the computing speed is improved (especially for star data scenarios of more than 100,000 levels), the computing efficiency is greatly improved, and the real-time requirements of large-scale space situation simulation systems are effectively supported.

[0031] 2. By replacing 3D engine rendering with a coordinate system conversion chain (J2000 → reference plane → image coordinate system), the present invention reduces the computing levels of the graphics pipeline, reduces the CPU occupancy rate and memory consumption, and significantly reduces the resource occupancy rate, enabling space-level optical simulation on ordinary computing terminals.

[0032] 3. The innovative star screening mechanism (dynamic elimination algorithm based on magnitude) of the present invention, combined with the space target visibility pre-judgment module, can support the second-level loading and processing of a million-level star database while ensuring imaging accuracy, breaking through the data carrying bottleneck of traditional 3D engines and having ultra-large-scale data throughput capabilities.

[0033] 4. The magnitude timely formula of the present invention introduces the phase angle The dynamic compensation algorithm accurately calculates the light scattering effect of space targets, constructs a quadratic attenuation model of the target reflectivity ρ and the target distance R, and improves the accuracy of magnitude acquisition through the σ0 target cross-sectional area dynamic correction mechanism, achieving high-fidelity imaging accuracy.

[0034] 5. The present invention supports dynamic configuration of the reference plane field-of-view height parameter (e.g., the 100-meter reference plane is adjustable). The resolution-magnitude mapping algorithm can adapt to optical sensors of different specifications. The projection plane coordinate system conversion module is compatible with multiple types of spaceborne platforms, meeting the multi-scenario application requirements from low-Earth orbit to deep space exploration, and having strong adaptive imaging scalability.

[0035] 6. The present invention decomposes complex optical imaging problems into standardized calculation units (field-of-view modeling → visibility analysis → coordinate projection → magnitude mapping), forms a lightweight simulation module that can be embedded in the space mission planning system and space situation awareness system, and has high system integration efficiency using engineering applications. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 is a schematic flow chart of the optical imaging simulation method of the spaceborne sensor of the present invention for space targets;

[0037] Figure 2 is a schematic structural diagram of the optical imaging simulation device of the spaceborne sensor of the present invention for space targets;

[0038] Figure 3 is a construction diagram of the field-of-view model of the spaceborne sensor of the present invention for space targets;

[0039] Figure 4 is a schematic diagram of projecting the field-of-view model coordinates of the spaceborne sensor of the present invention onto the reference plane;

[0040] Figure 5 is a diagram of setting the magnitude of a constant star in the simulation interface of the present invention;

[0041] Figure 6 is a diagram of setting parameters of a space target (satellite) in the simulation interface of the present invention;

[0042] Figure 7 is the real-time simulation imaging interface of the present invention;

[0043] Figure 8 is a schematic diagram after storing the generated simulation picture of the present invention;

[0044] Figure 9 is a schematic structural diagram of the electronic device of the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0045] Embodiments of the present invention will be described in detail below. Examples of the embodiments are shown in the accompanying drawings, where the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention and should not be construed as a limitation of the present invention.

[0046] Generally, the above-mentioned optical simulation methods for space targets require high computing resources and are inefficient for large-scale star data. For systems with higher real-time requirements, new methods are needed to improve the simulation computing efficiency and reduce the occupation of computing resources.

[0047] Existing methods for optical simulation of space targets generally require high computing resources and are inefficient for large-scale star data. For systems with higher real-time requirements, new methods are needed to improve the simulation computing efficiency and reduce the occupation of computing resources.

[0048] To address the above problems, the present invention provides an optical imaging simulation device for a space target by an on-board sensor. Figure 2 FIG. is a schematic structural diagram of the optical imaging simulation device for a space target by an on-board sensor provided in an embodiment of the present invention. The device includes: a field of view construction module, a screening and generation module, a reference plane module, a projection conversion module, a rendering and generation module, etc.

[0049] The field of view construction module is used to construct a field of view model based on the field of view parameters of the satellite payload and calculate the J2000 coordinate positions of the vertices ABCD of the field of view model.

[0050] The screening and generation module is used to perform visibility screening on the stars and all space targets within the field of view model and record the J2000 positions and star numbers of the visible stars and space targets.

[0051] The screening and generation module obtains the current position and attitude data of the satellite and the parameters of the payload field of view, constructs a field of view model, as Figure 3 shown, and calculates the J2000 coordinate positions of the vertices ABCD of the field of view according to geometric relationships.

[0052] Then, the detectable stars are screened according to the star magnitudes of the stars, and the visibility of all stars to the observation satellite is calculated by traversing. The J2000 positions and star numbers of the visible stars are recorded within the field of view model. Among them, the influence of lighting conditions needs to be considered when calculating the visibility.

[0053] The reference plane module is used to establish a reference plane along the central field of view direction of the observation satellite and transfer the vertices ABCD of the field of view model to the reference plane to obtain the vertices A'B'C'D'.

[0054] Starting from the observation satellite, along the direction of the central field of view, a reference plane (e.g., at an altitude of 100 meters) is established. This altitude can be arbitrarily specified. A rotation matrix from the J2000 coordinate system to the reference plane is constructed to transfer the vertices of the observation field of view of ABCD to the reference plane, as Figure 4 shown by the vertices A'B'C'D' of the reference plane.

[0055] A projection conversion module for converting the J2000 positions of all visible stars and space targets to the reference plane.

[0056] Convert the current J2000 positions of all visible stars and space targets to the reference plane. At this time, the coordinate origin is at the center of the image. For the convenience of drawing, convert the coordinates projected on the reference plane to positive values. By subtracting the coordinates of point C' on the reference plane from all projected coordinate points, move the coordinate origin to the lower left corner.

[0057] A drawing generation module for obtaining the star magnitudes of space targets and stars, calculating the equivalent pixel point sizes and brightnesses, and drawing a simulation image.

[0058] At this time, the projected point positions on the reference plane are the relative positions of the target points in the simulation image, but the sizes and brightnesses of the target points in the image still need to be further determined. Star magnitude is one of the important indicators for describing the light brightness of space targets. For optical imaging simulation, the sizes and brightnesses of target points can be calculated according to the visible star magnitudes, and the visible star magnitudes of each space target point are calculated respectively.

[0059] Then, scale and convert the coordinates of the reference plane according to the resolution of the generated image. According to the visible star magnitudes of space targets and the star magnitudes of star targets, combined with the image resolution, calculate the equivalent pixel point sizes and brightnesses, and draw a simulation image.

[0060] Using the device of the present invention, the formed simulation interface is as shown in Figure 5 、 6 、7 and 8. Figure 5 is the star magnitude setting diagram of the simulation interface of the present invention for stars; Figure 6 is the parameter setting diagram of the space target (satellite) of the simulation interface of the present invention; Figure 7 is the real-time simulation imaging interface of the present invention; Figure 8 is the schematic diagram after storing the generated simulation picture of the present invention.

[0061] Through the setting of star parameters in the simulation interface, the star magnitude range for star screening and the update period can be set; through the parameter setting of space targets (taking satellites as an example), satellite image options can be selected, the number of satellites and the selected number can be displayed; and the image can be displayed in real time and captured and saved for convenient later call.

[0062] Based on the above optical imaging simulation device of space targets by spaceborne sensors, the present invention also discloses an optical imaging simulation method of space targets by spaceborne sensors, as follows Figure 1 shown, the method includes:

[0063] S1. Obtain the field of view parameters of the satellite payload, construct a field of view model, and calculate the J2000 coordinate positions of the vertices ABCD of the field of view model.

[0064] Obtain the current position and attitude data of the satellite, the parameters of the payload field of view, construct a field of view model, and calculate the J2000 coordinate positions of the vertices ABCD of the field of view according to geometric relationships.

[0065] Screen the detectable stars according to the star magnitudes of the stars, traverse and calculate whether the observation satellite can see all the stars, record the J2000 positions and star numbers of the visible stars in the field of view; this step can be calculated in parallel, and the influence of lighting conditions needs to be considered when calculating visibility. When screening the visibility of the detected stars in the field of view model, the influence of lighting conditions is considered.

[0066] S2. Screen the visibility of the detected stars and all space targets in the field of view model, and record the J2000 positions and star numbers of the visible stars and space targets in the field of view model.

[0067] Screen the detectable stars according to the star magnitudes of the stars, traverse and calculate whether the observation satellite can see all the stars, record the J2000 positions and star numbers of the visible stars in the field of view, this step can be calculated in parallel, and the influence of lighting conditions needs to be considered when calculating visibility.

[0068] Traverse and calculate whether the observation satellite can see all space targets (such as satellites), record the J2000 positions and target numbers of the visible space targets in the field of view, this step can be calculated in parallel, and the influence of lighting conditions needs to be considered when calculating visibility.

[0069] S3. The observation satellite establishes a reference plane along the central field of view direction, and rotates the vertices ABCD of the field of view model to the reference plane to obtain the vertices A'B'C'D'.

[0070] Taking the observation satellite as the starting point, establish a reference plane with a height of 100 meters along the central field of view direction. This height can be specified arbitrarily, construct a rotation matrix from the J2000 coordinate system to the reference plane, and rotate the observed field of view vertices of ABCD to the reference plane to obtain the reference plane vertices A'B'C'D'.

[0071] S4. Convert the J2000 positions of all visible stars and space targets to the reference plane.

[0072] Convert the current J2000 positions of all visible stars and space targets to the reference plane. At this time, the coordinate origin is at the center of the image. For the convenience of drawing, convert the coordinates projected on the reference plane to positive values. Move the coordinate origin to the lower left corner by subtracting the coordinates of the reference plane C' from all projected coordinate points.

[0073] At this time, the projected point positions on the reference plane are the relative positions of the target points in the simulation image. However, the size and brightness of the target points in the image still need to be further determined. The magnitude is one of the important indicators for describing the light brightness of space targets. For optical imaging simulation, the size and brightness of the target points can be calculated according to the visible magnitude values. Calculate the visible magnitude values of each star and space target point respectively. The relationship between the magnitude, diameter, and distance of space targets is as follows:

[0074] m obj =m sun -2.5log(ρ·σ0 / R 2 )

[0075]

[0076] where, m sun =-26.73 is the apparent magnitude of the sun; R is the target distance; ρ is the reflectivity, generally 0.2; σ0 is the target cross-sectional area; d is the target diameter; is the phase angle.

[0077] S5. Calculate the equivalent pixel point size and brightness according to the magnitude values of space targets and stars, and draw the simulation image.

[0078] Then, perform scaling conversion on the coordinates of the reference plane according to the resolution of the generated image. Calculate the equivalent pixel point size and brightness according to the visible magnitude of space targets and the magnitude values of star targets, and combine with the image resolution to draw the simulation image.

[0079] The present invention also provides an electronic device, Figure 9 which is a schematic structural diagram of the electronic device provided by the embodiment of the present invention. As Figure 9 shown, the electronic device may include: a processor, a communication interface, a memory, and a communication bus. Among them, the processor, the communication interface, and the memory complete mutual communication through the communication bus. The processor can call the logical instructions in the memory, for example, to execute the following method:

[0080] S1. Obtain the satellite payload field of view parameters, construct a field of view model, and calculate the J2000 coordinate positions of the vertices ABCD of the field of view model.

[0081] S2. Perform visibility screening on the detected stars and all space targets within the field-of-view model, and record the J2000 positions and star numbers of the visible stars and space targets within the field-of-view model;

[0082] S3. The observation satellite establishes a reference plane along the central field-of-view direction, and rotates the vertices ABCD of the field-of-view model to the reference plane to obtain the vertices A'B'C'D';

[0083] S4. Convert the J2000 positions of all visible stars and space targets to the reference plane;

[0084] S5. Calculate the equivalent pixel sizes and brightnesses based on the magnitude values of the space targets and stars, and draw a simulation image.

[0085] In addition, when the logical instructions in the above-mentioned memory are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or a part of this 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 for causing a computer device (which can be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in various embodiments of the present invention. The foregoing storage medium includes: various media such as USB flash drives, mobile hard disks, read-only memories (ROMs), random access memories (RAMs), magnetic disks, or optical discs that can store program codes.

[0086] The embodiments of the present invention further provide a non-transitory computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, it is configured to execute the methods provided in the above-mentioned various embodiments, for example, including:

[0087] S1. Obtain the field-of-view parameters of the satellite payload, construct a field-of-view model, and calculate the J2000 coordinate positions of the vertices ABCD of the field-of-view model.

[0088] S2. Perform visibility screening on the detected stars and all space targets within the field-of-view model, and record the J2000 positions and star numbers of the visible stars and space targets within the field-of-view model;

[0089] S3. The observation satellite establishes a reference plane along the central field-of-view direction, and rotates the vertices ABCD of the field-of-view model to the reference plane to obtain the vertices A'B'C'D';

[0090] S4. Convert the J2000 positions of all visible stars and space targets to the reference plane;

[0091] S5. Calculate the equivalent pixel size and brightness based on the space target and the stellar magnitude of the stars, and draw a simulation image.

[0092] The device embodiments described above are merely illustrative. The units described as separate components may or may not be physically separated. The components shown as units may or may not be physical units, that is, they may be located in one place or distributed to multiple network units. Some or all of the modules can be selected according to actual needs to achieve the purpose of the solution of this embodiment. Those of ordinary skill in the art can understand and implement it without creative efforts.

[0093] Through the description of the above embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on this understanding, the essence of the above technical solution, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, magnetic disk, optical disk, etc., and includes several instructions to enable a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0094] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements for some of the technical features. And these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. An optical imaging simulation method for space targets by a spaceborne sensor, characterized in that Including: S1. Obtain the field-of-view parameters of the satellite payload, construct a field-of-view model, and calculate the J2000 coordinate positions of the vertices ABCD of the field-of-view model; S2. Perform visibility screening on the detected stars and all space targets within the field-of-view model, and record the J2000 positions and star numbers of the visible stars and space targets within the field-of-view model; S3. The observation satellite is along the central field-of-view direction, a reference plane is established, and the vertices ABCD of the field-of-view model are transferred to the reference plane to obtain the vertices A'B'C'D'; S4. Convert the J2000 positions of all visible stars and space targets to the reference plane; S5. According to the stellar magnitudes of the space targets and stars, calculate the equivalent pixel sizes and brightnesses, and draw a simulation image.

2. The optical imaging simulation method according to claim 1, wherein When performing visibility screening on the detected stars within the field-of-view model, the influence of lighting conditions is considered.

3. The optical imaging simulation method according to claim 1, wherein The coordinate origin of the reference plane is located at the vertex, so that the coordinate values displayed on the reference plane are positive.

4. The optical imaging simulation method according to claim 1, wherein The formula for obtaining the stellar magnitude is as follows: m obj = m sun -2.5 log(ρ·σ0 / R 2 ) where m sun = -26.73 is the apparent magnitude of the sun; R is the target distance; ρ is the reflectivity; σ0 is the target cross-sectional area; d is the target diameter; is the phase angle.

5. The optical imaging simulation method according to claim 1, wherein When drawing the simulation image in S5, the coordinates of the reference plane are scaled and converted according to the resolution of the generated image.

6. The optical imaging simulation method according to claim 1, wherein When drawing the simulation image in S5, according to the stellar magnitudes of the space targets and stars and the resolution of the generated image, calculate the equivalent pixel sizes and brightnesses of the stars and space targets.

7. An optical imaging simulation device for space targets by a spaceborne sensor applied to the method according to any one of claims 1 to 6, characterized in that, The device includes: A field-of-view construction module, which is used to construct a field-of-view model based on the field-of-view parameters of the satellite payload and calculate the J2000 coordinate positions of the vertices ABCD of the field-of-view model; A screening and generation module, which is used to perform visibility screening on the stars and all space targets within the field-of-view model and record the J2000 positions and star numbers of the visible stars and space targets; A reference plane module, which is used to establish a reference plane along the central field-of-view direction of the observation satellite and transfer the vertices ABCD of the field-of-view model to the reference plane to obtain the vertices A'B'C'D'; A projection conversion module, which is used to convert the J2000 positions of all visible stars and space targets to the reference plane; A drawing and generation module, which is used to obtain the stellar magnitudes of the space targets and stars, calculate the equivalent pixel sizes and brightnesses, and draw a simulation image.

8. An electronic device, comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, When the processor executes the program, it implements the steps of the optical imaging simulation method described in any one of claims 1 to 6.

9. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the steps of the optical imaging simulation method described in any one of claims 1 to 6.

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