Space target observation right ascension and declination data three-dimensional simulation method and system

Abstract

The invention discloses a space target observation right ascension and declination data three-dimensional simulation method and system, and the method comprises the steps: adding observation equipment and an observed target, and marking a J2000 position; calculating the J2000 position of the observation equipment and the observed target in the visible time period; converting the J2000 position of the observed target in the visible time period into a required J2000 position; the converted J2000 position data is right ascension and declination; and setting the same height according to the calculated right ascension and declination, and displaying in a three-dimensional situation. Through the three-dimensional visualization technology, the defects of two-dimensional projection are effectively avoided, the motion trail and the space relation of the space observed target can be accurately presented, and reliable support is provided for related research, task planning and the like.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of right ascension and declination data simulation of space targets, and particularly relates to a three-dimensional simulation method and system for right ascension and declination data of space target observation. BACKGROUND

[0002] In the field of space target observation, accurately presenting and analyzing the motion trajectories and spatial relationships of celestial bodies and various space observed targets such as spacecrafts is an important basis for carrying out related research, task planning and situation assessment.

[0003] Traditionally, the observation data display of space observed targets mostly adopts a two-dimensional equatorial coordinate system display method. However, this method has essential limitations. For example, when using the Mercator or other two-dimensional projection methods, the area of the high-declination region will be significantly inflated, resulting in a serious distortion of the spatial relationship between celestial bodies near the north celestial pole, and the actual distribution and relative position relationship of celestial bodies in three-dimensional space cannot be accurately and truly reflected. The defects of this two-dimensional display method bring many inconveniences to the interpretation of space observed target observation data, the analysis of motion rules, and the formulation of related tasks.

[0004] Three-dimensional model display can completely avoid the above problems caused by two-dimensional projection, and can real-time render the three-dimensional spatial relationship between celestial bodies, intuitively reflect the spatial motion trajectory of celestial bodies, and provide more reliable and effective visual support for space observed target observation research.

[0005] However, at present, there is no solution for how to combine three-dimensional models to efficiently and accurately simulate the right ascension and declination data of space observed target observation to better serve the business of space observed target motion trajectory display and running path inference.

[0006] For example, the invention application with application number 202210611996.4 discloses a right ascension and declination calculation method, device, equipment and medium based on Euler angles, which can quickly and accurately solve the celestial equatorial right ascension and declination from the initial pointing of the camera. However, the scheme lacks three-dimensional model display of right ascension and declination. SUMMARY

[0007] In view of the above problems, the present application aims to provide a three-dimensional simulation method and system for right ascension and declination data of space target observation, which solves the problem in the prior art that there is a lack of effective combination of right ascension and declination data of space observed target observation and three-dimensional models to achieve efficient and accurate simulation, thereby better serving the business of space observed target motion trajectory display and running path inference.

[0008] The present application provides a three-dimensional simulation method and system for right ascension and declination data of space target observation.

[0009] The first aspect is a three-dimensional simulation method for space target observation right ascension and declination data, comprising:

[0010] S1, adding observation equipment, marking the J2000 position of the observation equipment, and setting the load parameters of the observation equipment;

[0011] S2, adding at least one observed target, marking the J2000 position of the observed target;

[0012] S3, calculating the J2000 position of the observation equipment and the observed target in the visible time period;

[0013] S4, converting the J2000 position of the observed target in the visible time period into the required J2000 position;

[0014] S5, calculating the right ascension and declination of the converted J2000 position data;

[0015] S6, according to the calculated right ascension and declination, setting the same height, and displaying in a three-dimensional situation.

[0016] In an embodiment of the present application, the S3 visible time period acquisition comprises:

[0017] determining whether the observed target is observed by the load of the observation equipment from the scene start time to the end time, and the observable time period is the visible time period.

[0018] In an embodiment of the present application, the S4 conversion process is expressed by the formula:

[0019]

[0020]

[0021]

[0022]

[0023]

[0024] Wherein, A(x1, y1, z1) is the J2000 position of the observation equipment, B(x2, y2, z2) is the J2000 position of the observed target, is a direction vector, is a direction vector, is a normalization process, C(x3, y3, z3) is the required J2000 position after conversion distance, is the conversion distance.

[0025] In one embodiment of the present application, in S5,

[0026] The right ascension is expressed as:

[0027]

[0028] The declination is expressed as:

[0029]

[0030] Wherein, C(x3, y3, z3) is the observed target converted distance to the desired J2000 position, and r is the radius of the celestial sphere.

[0031] In one embodiment of the present application, in S6, when displayed in a three-dimensional situation, a preset celestial sphere model is loaded, and the celestial equator, ecliptic, and vernal equinox reference grid are superimposed.

[0032] In one embodiment of the present application, in S6, when displayed in a three-dimensional situation, the observation equipment position is taken as the perspective center, interactive operations such as rotation, scaling, and panning are supported, special perspectives such as the north celestial pole and the celestial equator are switched to, and the trajectory details of the high-declination region are observed.

[0033] In one embodiment of the present application, in S6, when displayed in a three-dimensional situation, the observed targets are distinguished by different colors, icons, or labels.

[0034] Second aspect: a three-dimensional simulation system for space target observation right ascension and declination data, comprising:

[0035] A parameter setting module is configured to add the load parameters of the observation equipment and the observed targets, and mark the J2000 positions of the observation equipment and the observed targets.

[0036] A visible time period screening module is configured to screen the visible time period of the observed targets and the load observation of the observation equipment from the scene start time to the end time.

[0037] A coordinate conversion module is configured to convert the J2000 positions of the observed targets in the visible time period to the desired J2000 positions, and convert the converted J2000 position data to right ascension and declination.

[0038] A projection display module is configured to display the right ascension and declination in a three-dimensional situation.

[0039] Third aspect: an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor implements the steps of the method provided in the first aspect when executing the program.

[0040] The fourth aspect: a non-transitory computer readable storage medium, having stored thereon a computer program, which, when executed by a processor, implements the steps of the method provided in the first aspect.

[0041] Advantages of the present application:

[0042] 1、The present application displays the right ascension and declination data at the same height in the three-dimensional situation by three-dimensional visualization technology, combines with the celestial sphere model and reference grid, can accurately restore the motion track and real space layout of the observed target in space, effectively avoids the inherent defects of two-dimensional projection, breaks through the limitation of two-dimensional projection, accurately presents the spatial relationship, and improves the reliability and practicality of data simulation.

[0043] 2、The present application ensures that only the target data observed by the observation equipment is processed by strict visible time period screening, uses the standardized coordinate conversion formula to ensure the accuracy and consistency of data conversion, and provides high-precision track reference and reliable data support for spatial target research and task planning.

[0044] 3、The present application method supports rotation, scaling, translation and other operations in the three-dimensional situation display with the observation equipment as the visual center, can be switched to the special visual angle of the north celestial pole and the celestial equator, is convenient for observing the track details of the high declination area, distinguishes multiple targets through color and icon, supports track point data linkage query, improves the analysis efficiency and intuitiveness of the motion law of the spatial target, and enhances the interactivity and detail observation ability. BRIEF DESCRIPTION OF DRAWINGS

[0045] Figure 1 The flowchart of the method of the present application is shown in the figure;

[0046] Figure 2 The application schematic diagram of the system of the present application is shown in the figure;

[0047] Figures 3 to 6 The application schematic diagram of the system of the present application is shown in the figure;

[0048] Figure 7 The structure schematic diagram of the electronic equipment of the present application is shown in the figure. DETAILED DESCRIPTION

[0049] The embodiments of the present application are described in detail below, and examples of the embodiments are shown in the drawings, wherein the same or similar symbols represent the same or similar elements or elements with the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary, only for explaining the present application, and cannot be understood as limiting the present application.

[0050] Existing technologies, particularly traditional two-dimensional equatorial coordinate system display methods, have inherent limitations. Using two-dimensional projection methods such as Mercator projection leads to area expansion in high-declination regions, failing to accurately reflect the actual size and distribution of celestial bodies in these areas. Furthermore, the spatial relationships of celestial bodies near the celestial north pole are severely distorted, failing to accurately represent their true layout and interrelationships in three-dimensional space. Two-dimensional models struggle to render the three-dimensional spatial relationships between celestial bodies in real time and cannot intuitively reflect their spatial trajectories, hindering the observation and analysis of celestial motion patterns.

[0051] To address the above problems, this invention provides a three-dimensional simulation method for right ascension and declination data of space target observation.

[0052] Example 1:

[0053] This embodiment discloses a three-dimensional simulation method for right ascension and declination data of space target observation, such as... Figure 1 As shown, the steps include:

[0054] S1. Add observation equipment, mark the J2000 position of the observation equipment, and set the load parameters of the observation equipment.

[0055] Select appropriate observation equipment, such as satellites or ground observation stations, based on actual observation needs.

[0056] Using professional astronomical coordinate calculation tools or relevant data, the precise position of the observation equipment in the J2000 coordinate system was determined and marked as A(x1, y1, z1).

[0057] The J2000 coordinate system is a celestial inertial coordinate system that provides a stable position reference.

[0058] Based on the type of observation equipment and the requirements of the observation mission, set its payload parameters, including but not limited to observation range, observation accuracy, and operating frequency band, to ensure that the visibility of the observed target can be accurately determined subsequently.

[0059] S2. Add at least one observed target and mark the J2000 position of the observed target.

[0060] Based on the requirements of the observation mission, select at least one spatial target to be observed, such as a satellite or spacecraft debris (see reference). Figure 4 Satellites or debris such as “FENGYUN IC DEB-297461” were observed as targets.

[0061] Calculate the precise three-dimensional position coordinates of the observed target in the J2000 inertial coordinate system using astronomical observation databases, orbit calculation tools, or historical orbit parameters of the observed target.

[0062] The calculated coordinates are marked as the J2000 position of the observed target. A single observed target is denoted as B(x2, y2, z2); if there are multiple observed targets, they are marked as B1(x2, y2, z2) respectively. 21 y 21 , z 21 B2(x) 22 y 22 , z 22 These data, along with others, form a set of observed target locations, providing fundamental data for subsequent visibility assessment and trajectory calculation.

[0063] S3. Calculate the position of the observation equipment and the observed target at J2000 within the visible time period.

[0064] The method for obtaining the visible time period is as follows: determine whether the observed target is observed by the payload of the observation equipment from the start time to the end time of the scene. The observable time period is the visible time period.

[0065] Define the start time (e.g., T1) and end time (e.g., T2) of the scene, and use this as the time interval for visibility judgment.

[0066] Based on the load parameters of the observation equipment (such as observation range, field of view, etc.), within the time range T1 to T2, it is calculated segment by segment or in real time whether the observed target is within the observable range of the observation equipment. Specifically, spatial geometric calculations can be used to determine whether the line connecting the position of the observed target J2000 and the position of the observation equipment J2000 is within the load observation field of view, and the time period that meets the conditions is the visible time period (such as [t1, t2], [t3, t4], etc.).

[0067] For each visible time period, the J2000 position data of the observation equipment and the observed target are extracted separately within that time period. The position of the observation equipment can be determined based on its orbital parameters or fixed coordinates (such as ground stations), denoted as A(x1, y1, z1); the position of the observed target is calculated in real time based on its orbital model, denoted as B(x2, y2, z2), forming a position sequence within the visible time period, providing a basis for subsequent data conversion.

[0068] S4. Convert the J2000 position of the observed target within the visible time period to the required J2000 position.

[0069] Obtain the position of the J2000 observation equipment during the visible time period. and the J2000 position of the observed target And determine the normalized transformation distance parameter, such as 1e13.

[0070] First, calculate the direction vector using the formula:

[0071]

[0072] Calculate the direction vector from the position of the observation equipment to the position of the observed target, and then calculate the direction vector. The modulus, the formula is:

[0073]

[0074] Next, the normalized direction vector is calculated, and the direction vector is normalized using the following formula:

[0075]

[0076] Then, using the formula:

[0077]

[0078]

[0079] The calculated distance is the required J2000 position. Expanded as:

[0080]

[0081]

[0082]

[0083] Complete the transformation of the observed target's location within the visible time period.

[0084] S5. The converted J2000 position data is right ascension and declination.

[0085] Right ascension (RA) and declination (Dec) are two angular coordinates in the celestial coordinate system, which can be obtained by converting from rectangular coordinates to spherical coordinates.

[0086] Calculate right ascension (RA):

[0087]

[0088] Here, arctan2() is the arctangent function in the four quadrants, and the result is in the range of [-π, π], which is usually converted to [0, 2π) or [0°, 360°).

[0089] Calculate declination (Dec):

[0090]

[0091] Where r is the radius of the celestial sphere, which is the distance from point C to the origin:

[0092]

[0093] Since C is obtained by multiplying the normalized direction vector by 1e13, theoretically r≈1e13, but for accurate calculation, the actual distance is still used.

[0094] S6. Based on the calculated right ascension and declination, set them to the same altitude and display them in the three-dimensional situation.

[0095] The calculated right ascension and declination data are processed to a uniform height and then mapped onto a three-dimensional celestial sphere model to achieve an intuitive display of the observed target's trajectory.

[0096] The radius of the preset three-dimensional celestial sphere, i.e. the value at the same height, is denoted as H. It can be set according to visualization needs. For example, H=1 unit celestial sphere radius. The center of the celestial sphere is associated with the J2000 position (point A) of the observation equipment to ensure a unified observation perspective.

[0097] Right ascension and declination are converted into coordinates (X, Y, Z) on the three-dimensional celestial surface to achieve spatial positioning at the same altitude. The calculation formula is based on the transformation relationship between the celestial coordinate system and the rectangular coordinate system, and the formula is as follows:

[0098]

[0099]

[0100]

[0101] According to the above formula, for continuous right ascension and declination data points (α1, δ1), (α2, δ2)...(α...) within the visible time period... n δ n ), and convert them one by one into three-dimensional coordinate points (X1, Y1, Z1), (X2, Y2, Z2)...(X n Y n Z n ).

[0102] By using linear interpolation or spline curve fitting, the coordinates of adjacent time points are connected to generate a smooth trajectory line of the observed target, reflecting the dynamic changes of the observed target on the celestial sphere.

[0103] Load a pre-defined celestial sphere model into a 3D engine (such as Unity or Cesium), and overlay reference grids such as the celestial equator, ecliptic, and vernal equinox to enhance spatial orientation. Mark the current 3D coordinate position using specific icons (such as satellite icons). For the trajectory line, set color gradients or thickness variations according to the time series to highlight the temporal characteristics of the trajectory.

[0104] Preferably, with the location of the observation equipment (point A) as the center of view, the simulation supports interactive operations (such as rotation, zoom, and translation), and can also switch to special perspectives such as the celestial north pole and celestial equator to observe trajectory details in high declination regions (avoiding the distortion problem of two-dimensional projection).

[0105] Preferably, the position of the observed target on the three-dimensional celestial sphere is dynamically updated according to the timeline, and the display status of the trajectory line is refreshed synchronously (such as highlighting the trajectory before the current moment).

[0106] Preferably, for multiple observed targets, different colors, icons, or labels (e.g.) are used. Figure 4 To distinguish the target (shown as satellite number "FENGYUN IC DEB-297461") and avoid trajectory confusion.

[0107] Preferably, clicking on any point on the trajectory displays the original data of right ascension and declination at the corresponding time point, the name of the observed target, and other information, enabling linked querying of visualization and original data.

[0108] By mapping right ascension and declination onto a three-dimensional celestial sphere with a fixed radius, the spatial orientation of the observed target is preserved, while the interference of distance on visualization is eliminated by maintaining the same altitude. Finally, a dynamic display of the trajectory is achieved using a three-dimensional engine. This process solves the problem of distortion in high-declination regions in traditional two-dimensional projection, providing an intuitive and accurate spatial reference for analyzing the trajectory of the observed target.

[0109] Example 2:

[0110] Based on Example 1, this example discloses a three-dimensional simulation system for right ascension and declination data of space target observation, such as... Figure 2 As shown, this system uses a modular design to simulate, transform, and visualize observation data of observed targets in space. It includes: a parameter setting module, a visible time period filtering module, a coordinate transformation module, and a projection display module, among others.

[0111] like Figure 3 and Figure 4 As shown, the parameter setting module is used to add the load parameters of the observation equipment and the observed target, mark the J2000 position of the observation equipment and the observed target, and provide initial data support for subsequent system calculations.

[0112] The parameter setting module allows users to add observation equipment such as satellites and ground observation stations according to the needs of the observation mission. By calling the astronomical coordinate database or inputting orbital parameters, it automatically calculates and marks the three-dimensional position A(x1,y1,z1) of the observation equipment in the J2000 coordinate system. At the same time, it receives the payload parameters input by the user, including the observation range, observation accuracy, and operating frequency band, and stores them as constraints for subsequent visibility judgment.

[0113] It also allows the addition of single or multiple space targets to be observed (such as the satellite "FENGYUN IC DEB-297461", spacecraft debris, etc.). By inputting the target number or orbital elements (such as semi-major axis, eccentricity), the orbit calculation tool is invoked to generate the real-time position B(x2,y2,z2) of the target in the J2000 coordinate system, and the target position set is formed in list form. Dynamic addition and deletion of targets to be observed are supported.

[0114] like Figure 5 As shown, the visible time period filtering module is used to filter the visible time period from the start time to the end time of the scene, and to filter out the effective time period in which the observed target is within the observable range of the observation equipment's load.

[0115] As can be seen, the time period filtering module receives the user-defined scenario start time T1 (e.g., 2023-01-01 00:00:00) and end time T2 (e.g., 2023-01-01 23:59:59) to determine the time boundaries of the analysis.

[0116] Based on parameters such as the load field of view provided by the parameter setting module, spatial geometric calculations are used to determine whether the observed target is visible. The system iterates through time points T1 to T2, outputting consecutive visible time periods. The selected visible time periods are then associated with and stored along with the location data of the observation equipment and the observed target at the corresponding time points, forming a time-stamped location sequence.

[0117] The coordinate transformation module is used to convert the J2000 position of the observed target within the visible time period to the required J2000 position; and the transformed J2000 position data is converted to right ascension and declination;

[0118] The coordinate transformation module calls the position A of the observation equipment and the position B of the observed target within the visible time period, calculates the direction vector (BA), normalizes it using the normalVec() function, and then applies the formula...

[0119]

[0120] Generate the transformed target position C(x3,y3,z3) to ensure the orientation consistency of all observed targets on a uniform distance scale.

[0121] Then, based on the rectangular coordinates of position C, the right ascension (RA) and declination (Dec) are calculated using the spherical coordinate transformation formula, where,

[0122] Right ascension is:

[0123] Declination is:

[0124] Output the right ascension and declination sequence with timestamps.

[0125] like Figure 6 As shown, the projection display module is used to display right ascension and declination in a three-dimensional situation, mapping the right ascension and declination data onto a three-dimensional celestial sphere model to achieve a visual display of the trajectory of the observed target.

[0126] Preset the celestial radius H, and use the right ascension and declination data through the formula

[0127]

[0128]

[0129]

[0130] Convert to celestial surface coordinates to ensure that all observed target trajectories are at the same height.

[0131] Then, load the celestial sphere model in the Unity or Cesium engine and overlay reference grids such as the celestial equator and ecliptic; mark the observed targets with different colors and icons, generate smooth trajectory lines by connecting time point coordinates through linear interpolation, and support the trajectory color to change gradually over time.

[0132] Furthermore, the system supports rotation and zoom operations with the observation equipment position A as the center of view, and can switch to the celestial north pole perspective to observe the trajectory in the high declination region; clicking on the trajectory point can display the right ascension and declination values ​​of the corresponding time, the name of the observed target, and other information; the trajectory can be dynamically played by dragging the time axis, and the position of the observed target at the current moment can be highlighted.

[0133] This system automates the entire process from data input to 3D display through modular division of labor, solving the problem of distortion in high declination regions in traditional 2D projection and providing intuitive and accurate tool support for the observation and analysis of spatial targets.

[0134] The present invention also provides an electronic device, Figure 7 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention, such as... Figure 7 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:

[0135] S1. Add observation equipment, mark the J2000 position of the observation equipment, and set the load parameters of the observation equipment.

[0136] S2. Add at least one observed target and mark the J2000 position of the observed target;

[0137] S3. Calculate the J2000 position of the observation equipment and the observed target during the visible time period;

[0138] S4. Convert the J2000 position of the observed target within the visible time period to the required J2000 position;

[0139] S5. Calculate the right ascension and declination of the converted J2000 position data;

[0140] S6. Based on the calculated right ascension and declination, set them to the same altitude and display them in the three-dimensional situation.

[0141] 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.

[0142] 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:

[0143] S1. Add observation equipment, mark the J2000 position of the observation equipment, and set the load parameters of the observation equipment.

[0144] S2. Add at least one observed target and mark the J2000 position of the observed target;

[0145] S3. Calculate the J2000 position of the observation equipment and the observed target during the visible time period;

[0146] S4. Convert the J2000 position of the observed target within the visible time period to the required J2000 position;

[0147] S5. Calculate the right ascension and declination of the converted J2000 position data;

[0148] S6. Based on the calculated right ascension and declination, set them to the same altitude and display them in the three-dimensional situation.

[0149] The system 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.

[0150] 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.

[0151] 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 three-dimensional simulation method for right ascension and declination data of space target observation, characterized in that, include: S1. Add observation equipment, mark the J2000 position of the observation equipment, and set the load parameters of the observation equipment. S2. Add at least one observed target and mark the J2000 position of the observed target; S3. Calculate the J2000 position of the observation equipment and the observed target during the visible time period; S4. Convert the J2000 position of the observed target within the visible time period to the required J2000 position; S5. Calculate the right ascension and declination of the converted J2000 position data; S6. Based on the calculated right ascension and declination, set them to the same altitude and display them in the three-dimensional situation.

2. The method according to claim 1, characterized in that, The acquisition of the visible time period in S3 includes: Determine whether the observed target was observed by the payload of the observation equipment from the start time to the end time of the scene. The time period that can be observed is the visible time period.

3. The method according to claim 1, characterized in that, The S4 conversion process is expressed by the following formula: Where A(x1, y1, z1) is the J2000 position of the observation equipment, and B(x2, y2, z2) is the J2000 position of the observed target. It is a direction vector. Let the magnitude of the direction vector be . For normalization, C(x3, y3, z3) is the J2000 position required after the distance transformation. This is for distance conversion.

4. The method according to claim 3, characterized in that, In S5: Right ascension is represented as: Declination is represented as: Where C(x3, y3, z3) is the J2000 position of the observed target at the required distance conversion, and r is the radius of the celestial sphere.

5. The method according to claim 1, characterized in that, When displaying the three-dimensional situation in S6, a preset celestial sphere model is loaded, and reference grids for the celestial equator, ecliptic, and vernal equinox are superimposed.

6. The method according to claim 1, characterized in that, When the S6 is displayed in a three-dimensional situation, the position of the observation equipment is the center of view, and interactive operations such as rotation, scaling and translation are supported. It can switch to special perspectives such as the celestial north pole and celestial equator to observe the trajectory details in the high declination region.

7. The method according to claim 1, characterized in that, In S6, when the situation is displayed in three dimensions, the observed targets are distinguished by different colors, icons, or labels.

8. A three-dimensional simulation system for right ascension and declination data of space target observation, characterized in that, include: The parameter setting module is used to add the load parameters of the observation equipment and the observed target, and to mark the J2000 positions of the observation equipment and the observed target. The visible time period filtering module is used to filter the visible time period from the start time to the end time of the scene, during which the observed target is observed by the payload of the observed equipment. The coordinate transformation module is used to convert the J2000 position of the observed target within the visible time period into the required J2000 position, and the transformed J2000 position data is the right ascension and declination; The projection display module is used to display right ascension and declination in a three-dimensional situation.

9. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the program, it implements the steps of the method as described in any one of claims 1 to 7.

10. A non-transitory computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by a processor, it implements the steps of the method as described in any one of claims 1 to 7.

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