A method, device, equipment and medium for simulating optical imaging of a space target by a space-borne sensor

Abstract

The application discloses a kind of spaceborne sensor optical imaging simulation method, device, equipment and medium to space target, method includes: constructing field of view model, the visibility screening is carried out to the star and all space targets detected in field of view model, along with the direction of observation satellite central field of view, establish reference plane, field of view model is transferred to reference plane;All visible stars and space target J2000 position is converted to reference plane;According to the star value of space target and star, the equivalent pixel point size and brightness are calculated, and simulation image is drawn.The application is processed by adopting field of view model construction and visibility analysis, the visibility judgment of super large scale star and space target is handled, and the calculation speed is improved, the calculation efficiency is greatly improved, effectively supports the real-time demand of large-scale space situation simulation system.

Description

Technical Field

[0001] This invention relates to the field of optical imaging technology for space targets by spaceborne sensors, and in particular to a method, apparatus, equipment and medium for simulating optical imaging of space targets by spaceborne sensors. Background Technology

[0002] Optical imaging simulation of space targets is a common operational function in the aerospace simulation field. Common simulation methods are based on 3D digital earth engines such as OSGEarth or Cesium, utilizing the platform's viewpoint function to set the position data of the target and observer, and capturing images from the viewpoint. The drawbacks of this method are that the imaging algorithm relies on a heavyweight 3D engine, resulting in high computational resource consumption. Furthermore, if hundreds of thousands of star data points are needed to simulate a realistic stellar background, the method becomes inefficient with large-scale stellar data, significantly reducing display efficiency.

[0003] For example, invention application No. 202410127537.8 discloses a method and system for simulating optical imaging of space targets. This application's solution, by simulating optical imaging scenarios, can establish the position and attitude relationship between space targets and observation equipment. Combined with the parameters of the observation equipment, and with the support of OpenGL, it achieves geometric simulation of optical imaging of aerial targets by adjusting the viewpoint position and direction, thus assisting in the analysis of aerial target situations and showing good application prospects. However, this solution also has the problems of being unable to handle the simulation imaging of hundreds of thousands of star data points, and the imaging algorithm consuming high computer resources.

[0004] Therefore, real-world systems with higher real-time requirements need a new approach to improve simulation efficiency while reducing computational resource consumption, enabling the processing of large-scale space target simulation imaging data. Summary of the Invention

[0005] To address the aforementioned problems, the present invention aims to provide a method, apparatus, device, and medium for optical imaging simulation of space targets by a spaceborne sensor, enabling optical imaging simulation of hundreds of thousands of stars and space targets while reducing the consumption of computing resources.

[0006] This invention provides a method, apparatus, device, and medium for simulating optical imaging of space targets by a spaceborne sensor.

[0007] First aspect: A method for simulating optical imaging of space targets by a spaceborne sensor, comprising:

[0008] S1. Obtain the field of view parameters of the satellite payload, construct the field of view model, and calculate the J2000 coordinate position of the vertex ABCD of the field of view model.

[0009] S2. Perform visibility screening on the stars and all space targets detected 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, and rotates the field of view model vertices ABCD to the reference plane to obtain vertices A'B'C'D'.

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

[0012] S5. Based on the magnitude values ​​of the space target and the star, calculate the equivalent pixel size and brightness, and draw the simulation image.

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

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

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

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

[0017]

[0018] 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; This 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 simulated image in S5, the equivalent pixel size and brightness of the star and the space target are calculated based on the magnitude of the space target and the star and the resolution of the generated image.

[0021] The second aspect: an optical imaging simulation device for space targets by a spaceborne sensor, comprising:

[0022] The field of view construction module is used to construct a field of view model based on the satellite payload field of view parameters and calculate the J2000 coordinate position of the vertex ABCD of the field of view model.

[0023] The filtering and generation module is used to filter the visibility of stars and all space targets within the field of view model, and record the J2000 positions and star numbers of visible stars and space targets.

[0024] The reference plane module is used to establish a reference plane along the direction of the center field of view of the observed satellite, and to rotate the vertices ABCD of the field of view model to the reference plane to obtain vertices A'B'C'D'.

[0025] The projection conversion module is used to convert the positions of all visible stars and space targets J2000 to the reference plane;

[0026] The rendering and generation module is used to obtain the magnitude values ​​of space targets and stars, calculate the equivalent pixel size and brightness, and render the simulation image.

[0027] Third aspect: An electronic device including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor, when executing the program, performs the steps of the method provided in the first aspect.

[0028] Fourth aspect: A non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the steps of the method provided in the first aspect.

[0029] The beneficial effects of this invention are:

[0030] 1. This invention employs a parallel computing architecture for field-of-view model construction and visibility analysis to process 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 scenarios with more than 100,000 star data), and the computing efficiency is greatly improved, effectively supporting the real-time requirements of large-scale space situation simulation systems.

[0031] 2. This invention replaces 3D engine rendering with a coordinate system transformation chain (J2000 → reference plane → image coordinate system), reducing the number of graphics pipeline calculation layers, lowering CPU usage and memory consumption, significantly reducing resource usage, and enabling spatial-level optical simulation on ordinary computing terminals.

[0032] 3. The innovative star screening mechanism of this invention (dynamic elimination algorithm based on magnitude) combined with the space target visibility prediction module can support the loading and processing of a million-level star database in seconds while ensuring imaging accuracy. It breaks through the data carrying capacity bottleneck of traditional 3D engines and has ultra-large-scale data throughput capability.

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

[0034] 5. This invention supports dynamic configuration of the reference plane field of view height parameter (e.g., adjustable 100-meter reference plane), the resolution-magnitude mapping algorithm can be adapted to optical sensors of different specifications, and the projection plane coordinate system transformation module is compatible with multiple types of spaceborne platforms, meeting the application needs of multiple scenarios from near-Earth orbit to deep space exploration, and has strong adaptive imaging scalability.

[0035] 6. This invention decomposes complex optical imaging problems into standardized computational units (field of view modeling → visibility analysis → coordinate projection → magnitude mapping), forming a lightweight simulation module that can be embedded in aerospace mission planning systems and space situational awareness systems. With the help of engineering applications, the system integration efficiency is high. Attached Figure Description

[0036] Figure 1 This is a flowchart illustrating the optical imaging simulation method for space targets using a spaceborne sensor according to the present invention.

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

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

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

[0040] Figure 5 This is a diagram showing the star magnitude settings in the simulation interface of this invention;

[0041] Figure 6 This is a diagram showing the parameter settings for the space target (satellite) in the simulation interface of this invention;

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

[0043] Figure 8 This is a schematic diagram of the simulated image generated and stored according to the present invention;

[0044] Figure 9 This is a schematic diagram of the structure of the electronic device of the present invention. Detailed Implementation

[0045] Embodiments of the present invention are described in detail below. Examples of these embodiments are illustrated in the accompanying drawings, wherein the same or similar symbols denote the same or similar elements or elements having 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 limiting the present invention.

[0046] The aforementioned optical simulation methods for space targets generally require significant computational resources and are inefficient with large-scale stellar data. For systems with higher real-time requirements, new methods are needed to improve simulation efficiency while reducing computational resource consumption.

[0047] Existing methods for optical simulation of space targets generally require high computational resources and are inefficient with large-scale stellar data. For systems with higher real-time requirements, new methods are needed to improve simulation efficiency while reducing computational resource consumption.

[0048] To address the aforementioned problems, this invention provides an optical imaging simulation device for space targets using a spaceborne sensor. Figure 2 This is a schematic diagram of the structure of the optical imaging simulation device for space targets provided by the spaceborne sensor 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, and a drawing 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 to calculate the J2000 coordinate position of the vertex ABCD of the field of view model.

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

[0051] After the filtering and generation module passes, it obtains the satellite's current position and attitude data, the parameters of the payload's field of view, and constructs a field of view model, such as... Figure 3 As shown, the J2000 coordinate position of the field vertex ABCD is calculated based on geometric relationships.

[0052] Then, the detectable stars are filtered according to their magnitude values, and the visibility of all stars by the observation satellite is calculated. The J2000 position and star number of the visible stars are recorded in the field of view model. The effect of lighting conditions must be considered when calculating visibility.

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

[0054] Starting from the observation satellite, establish a reference plane (e.g., at a height of 100 meters) along the central field of view. This height can be arbitrarily specified. Construct a rotation matrix from the J2000 coordinate system to the reference plane, rotating the field vertices of the observation values ​​ABCD to the reference plane, as follows: Figure 4 The reference plane vertices A'B'C'D' are shown.

[0055] The projection conversion module is used to convert the positions of all visible stars and space targets J2000 to the reference plane.

[0056] Transform the current J2000 positions of all visible stars and space targets to the reference plane. At this point, the origin of the coordinate system is at the center of the image. To facilitate drawing, the coordinates projected onto the reference plane are converted to positive values. By subtracting the coordinates of the reference plane C' from all projected coordinate points, the origin of the coordinate system is moved to the lower left corner.

[0057] The rendering and generation module is used to obtain the magnitude values ​​of space targets and stars, calculate the equivalent pixel size and brightness, and render the simulation image.

[0058] At this point, the projection point on the reference plane is the relative position of the target point in the simulated image. However, it is still necessary to further determine the size and brightness of the target point in the image. Magnitude is one of the important indicators describing the brightness of a spatial target. For optical imaging simulation, the size and brightness of the target point can be calculated based on the visible magnitude value, and the visible magnitude value of each spatial target point can be calculated separately.

[0059] Then, the coordinates of the reference plane are scaled and transformed according to the resolution of the generated image. Based on the visible magnitude of the space target and the magnitude of the stellar target, and combined with the image resolution, the equivalent pixel size and brightness are calculated, and the simulation image is drawn.

[0060] Using the device of this invention, a simulated interface is created, such as... Figure 5 , 6 As shown in 7 and 8, Figure 5 This is a diagram showing the star magnitude settings in the simulation interface of this invention; Figure 6 This is a diagram showing the parameter settings for the space target (satellite) in the simulation interface of this invention; Figure 7 This is the real-time simulation imaging interface of the present invention; Figure 8 This is a schematic diagram of the simulated image generated and stored according to the present invention.

[0061] By setting star parameters through the simulation interface, you can set the magnitude range for star filtering, set the update cycle, etc. By setting parameters for space targets (taking satellites as an example), you can select satellite image options, display the number of satellites and the number of selected satellites. You can also display images in real time and save screenshots for easy retrieval later.

[0062] Based on the aforementioned optical imaging simulation device for space targets using spaceborne sensors, this invention also discloses a method for simulating optical imaging of space targets using spaceborne sensors, such as... Figure 1 As shown, the method includes:

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

[0064] Acquire the satellite's current position and attitude data, the parameters of the payload's field of view, construct the field of view model, and calculate the J2000 coordinate position of the field of view vertex ABCD based on geometric relationships.

[0065] The detectable stars are filtered based on their magnitude values. The visibility of all stars by the observation satellite is calculated and recorded. The J2000 position and star number of the visible stars within the field of view are recorded. This step can be performed in parallel. The visibility calculation needs to take into account the influence of lighting conditions. When filtering the visibility of the stars detected within the field of view model, the influence of lighting conditions should be taken into account.

[0066] S2. Perform visibility screening on the stars and all space targets detected 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.

[0067] The detectable stars are filtered based on their magnitude values. The visibility of all stars by the observation satellite is calculated. The J2000 position and star number of the visible stars within the field of view are recorded. This step can be performed in parallel. The effect of lighting conditions needs to be considered when calculating visibility.

[0068] The process involves iterating through all observation satellites to determine whether they are visible to all space targets (e.g., satellites). The position and target number of the visible space target J2000 within the field of view are recorded. This step can be performed in parallel. The visibility calculation must take into account the influence of lighting conditions.

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

[0070] Starting from the observation satellite, establish a reference plane with a height of 100 meters along the central field of view. This height can be arbitrarily specified. Construct a rotation matrix from the J2000 coordinate system to the reference plane, and rotate the field of view vertices of the observation values ​​of ABCD to the reference plane to obtain the vertices A'B'C'D' of the reference plane.

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

[0072] Transform the current J2000 positions of all visible stars and space targets to the reference plane. At this point, the origin of the coordinate system is at the center of the image. To facilitate drawing, the coordinates projected onto the reference plane are converted to positive values. By subtracting the coordinates of the reference plane C' from all projected coordinate points, the origin of the coordinate system is moved to the lower left corner.

[0073] At this point, the projection point on the reference plane is the relative position of the target point in the simulation image. However, it is still necessary to further determine the size and brightness of the target point in the image. Magnitude is one of the important indicators describing the brightness of a space target. For optical imaging simulation, the size and brightness of the target point can be calculated based on the visible magnitude value. The visible magnitude value of each star and space target point is calculated separately. The relationship between the magnitude, diameter, and distance of a space target 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, typically 0.2; σ0 is the target cross-sectional area; d is the target diameter; This is the phase angle.

[0077] S5. Based on the magnitude values ​​of the space target and the star, calculate the equivalent pixel size and brightness, and draw the simulation image.

[0078] Then, the coordinates of the reference plane are scaled and transformed according to the resolution of the generated image. Based on the visible magnitude of the space target and the magnitude of the stellar target, and combined with the image resolution, the equivalent pixel size and brightness are calculated, and the simulation image is drawn.

[0079] The present invention also provides an electronic device, Figure 9 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention, such as... Figure 9 As shown, the electronic device may include a processor, a communications interface, memory, and a communication bus, wherein the processor, communications interface, and memory communicate with each other via the communication bus. The processor can invoke logical instructions from the memory, for example, to execute the following method:

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

[0081] S2. Perform visibility screening on the stars and all space targets detected 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, and rotates the field of view model vertices ABCD to the reference plane to obtain vertices A'B'C'D'.

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

[0084] S5. Based on the magnitude values ​​of the space target and the star, calculate the equivalent pixel size and brightness, and draw the simulation image.

[0085] Furthermore, the logical instructions in the aforementioned memory can be implemented as software functional units and sold or used as independent products, and can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art, or a part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0086] This invention also provides a non-transitory computer-readable storage medium storing a computer program thereon, which, when executed by a processor, is implemented to perform the methods provided in the above embodiments, including, for example:

[0087] S1. Obtain the field of view parameters of the satellite payload, construct the field of view model, and calculate the J2000 coordinate position of the vertex ABCD of the field of view model.

[0088] S2. Perform visibility screening on the stars and all space targets detected 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, and rotates the field of view model vertices ABCD to the reference plane to obtain vertices A'B'C'D'.

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

[0091] S5. Based on the magnitude values ​​of the space target and the star, calculate the equivalent pixel size and brightness, and draw the simulation image.

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

[0093] Through the above description of the embodiments, those skilled in the art can clearly understand that each embodiment can be implemented by means of software plus necessary general-purpose hardware platforms, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solutions, in essence 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 cause a computer device (which may be a personal computer, server, or network device, etc.) to execute the methods described in the various embodiments 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 not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for simulating optical imaging of a space object by a space-borne sensor, characterized in that, The method comprises the following steps: S1, acquiring satellite payload field of view parameters, constructing a field of view model, and calculating J2000 coordinate positions of the field of view model vertex ABCD; S2, performing visibility screening on stars and all space targets detected in the field of view model, and recording J2000 positions and star numbers of visible stars and space targets in the field of view model; S3, establishing a reference plane along the central field of view direction of the observation satellite, and converting the field of view model vertex ABCD to the reference plane to obtain vertex A'B'C'D'; S4, converting J2000 positions of all visible stars and space targets to the reference plane; S5, calculating equivalent pixel point sizes and brightnesses according to star magnitude values of the space targets and stars, and drawing a simulation image. The star magnitude value is obtained according to the following formula: m obj = m sun -2.5 log(p-σ0 / R 2 ) where m sun = -26.73 is the apparent solar magnitude; R is the target distance; p is the reflectivity; σ0is the target cross-sectional area; d is the target diameter; is the phase angle.

2. The optical imaging simulation method of claim 1, wherein, When performing visibility screening on the stars detected in the field of view model, the influence of illumination conditions is considered.

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

4. The optical imaging simulation method of 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.

5. The optical imaging simulation method of claim 1, wherein, When drawing the simulation image in S5, the equivalent pixel point sizes and brightnesses of the stars and space targets are calculated according to the star magnitude values of the stars and space targets and the resolution of the generated image.

6. An optical imaging simulation device for space objects applied to the space-borne sensor of any one of claims 1 to 5, characterized in that, The device comprises: a field of view construction module configured to construct a field of view model according to satellite payload field of view parameters, and calculate J2000 coordinate positions of the field of view model vertex ABCD; a screening generation module configured to perform visibility screening on stars and all space targets in the field of view model, and record J2000 positions and star numbers of visible stars and space targets; a reference plane module configured to establish a reference plane along the central field of view direction of the observation satellite, and convert the field of view model vertex ABCD to the reference plane to obtain vertex A'B'C'D'; a projection conversion module configured to convert J2000 positions of all visible stars and space targets to the reference plane; a drawing generation module configured to obtain star magnitude values of the space targets and stars, calculate equivalent pixel point sizes and brightnesses, and draw a simulation image.

7. An electronic device comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, The processor implements the steps of the optical imaging simulation method according to any one of claims 1 to 5 when executing the program.

8. A non-transitory computer-readable storage medium having stored thereon a computer program, characterized in that, The computer program, when executed by the processor, implements the steps of the optical imaging simulation method according to any one of claims 1 to 5.

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