Accurate determination method for space target orbit
By constructing a binocular observation system and triangulation principle, combined with the traceless Kalman filtering algorithm, the accuracy and efficiency problems of spatial target track determination are solved, high-precision track determination and new calendar generation are achieved, and subsequent track forecasting and tracking are supported.
Patent Information
- Application Number
- CN202510318830.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-18
- Publication Date
- 2025-07-04
AI Technical Summary
The prior art is difficult to efficiently and accurately determine the orbit of space targets, especially the orbital perception requirements of near-Earth non-cooperation targets and high dynamic targets within the finite field of view of deep space have not been met.
A binocular observation system is built, using triangulation principle and traceless Kalman filtering algorithm, combined with optical observation equipment and multi-platform observation, and the precise position and orbit of the spatial target are determined by optimizing the objective function and iterative calculation.
Improve the accuracy and efficiency of spatial target track determination, ensure the accuracy and reliability of observation data, and generate high-precision new calendars to support subsequent track forecasting and tracking.
Smart Images
Figure CN120252628A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of space observation, and more specifically, the present invention relates to a method for accurately determining the orbit of a space target. Background Art
[0002] With the continuous development of space technology, space situation awareness has become the focus of attention of countries around the world. The determination of the orbit of space targets is becoming a research hotspot in the space field. In particular, space targets such as near-Earth non-cooperative targets and high-dynamic targets within the limited field of view of deep space are facing urgent sensing needs. The detection of space targets has important application values, such as predicting the orbits of space targets to issue warnings about possible collisions, etc. Space targets include artificial objects (spacecraft, space debris) and some natural celestial bodies, micrometeoroids, etc. The target characteristics of space targets include size, shape, and orbit. In the field of determining the orbit of space targets, an important issue is the determination of the orbit of space targets. Summary of the Invention
[0003] In order to overcome the deficiencies of the prior art, the present invention provides a method for accurately determining the orbit of a space target.
[0004] To achieve the above object, the present invention provides the following technical solution: A method for accurately determining the orbit of a space target, comprising the following steps: Step 1: Set the parameters of the optical observation equipment and the observation platform; Step 2: Calculate the position of the target in the epoch geocentric celestial coordinate system; Step 3: Obtain the information of the same target imaged by the observation platform within a period of time, and calculate the observed time period; Step 4: Construct an optimization objective function with the distance between the starting point and the ending point within the imaging duration as the undetermined parameter, and solve the optimization problem; Step 5: Set up an additional observation platform, construct a dual-platform system, and use the principle of triangulation to realize the solution of the space target position; Step 6: Generate a new ephemeris of the space target according to the precise orbit determination result; Step 7: Change the two-line data of the target orbit, and repeat Steps 3 to 6 to determine the target orbit.
[0005] As a preferred technical solution of the present invention, in the above Step 1, determining the positions of the optical observation equipment and the observation platform in the epoch geocentric celestial coordinate system includes, but is not limited to, geographical coordinates and altitude, and then setting the specific parameters of the optical observation equipment, including, but is not limited to, the focal length of the telescope, the type of sensor, and the resolution.
[0006] As a preferred technical solution of the present invention, in the second step, two rows of data of the target orbit are input, and the two rows of data include, but are not limited to, the basic information and parameters of the target orbit; according to the two rows of data, using the orbital mechanics model and related algorithms, the position of the target in the geocentric celestial coordinate system at the epoch is calculated.
[0007] As a preferred technical solution of the present invention, in the third step, the following steps are included: Step A1: Continuously or intermittently image and observe a specific space target through a space-based optical monitoring platform, and collect image data of the target at different time points; Step A2: Process and analyze the collected image data; Step A3: Based on the processed data, calculate the continuous observation time period of the space-based optical monitoring platform for the same target; Step A4: Record the calculated observation time period and use it as input data for subsequent orbit determination and prediction.
[0008] As a preferred technical solution of the present invention, in Step A1, the image data includes, but is not limited to, the position, velocity, and acceleration of the target; in Step A2, the image data processing includes, but is not limited to, image denoising, enhancement, and feature extraction.
[0009] As a preferred technical solution of the present invention, in the fourth step, use mathematical methods and algorithms to solve the optimization problem, obtain the minimum or maximum value of the objective function, and determine the optimal orbital parameters; convert the solution result into orbital state variables, and use the orbital state variables as undetermined parameters to construct the optimization objective function again; improve the orbital state variables through the least squares method or other numerical methods to improve the accuracy of orbit determination; repeat the above process iteratively to improve the accuracy.
[0010] As a preferred technical solution of the present invention, in the fifth step, two observation platforms observe the same space target at different positions to obtain different perspectives and observation data; based on the principle of triangulation, use the target angle information observed by the two platforms to calculate the accurate position of the target in space; jointly input the calculated target position and angle measurement information into the unscented Kalman filter algorithm, and through the steps of target state prediction, observation prediction, unscented transformation, and state update, iterate and optimize to obtain a more accurate target orbit.
[0011] As a preferred technical solution of the present invention, in the sixth step, the generated new ephemeris of the space target contains the position and velocity information of the space target in the future for a period of time.
[0012] As a preferred technical solution of the present invention, in step seven, two rows of data of the target orbit are modified to change the initial position, speed, and orbital inclination parameters of the target; after the orbit determination process of the target orbit after all modifications is completed, statistical analysis is performed on all results.
[0013] Compared with the prior art, the beneficial effects of the present invention are as follows: By constructing a binocular observation system, using the principle of triangulation and solving the target position, and accurately calculating the positions of the platform and the target, the accuracy and reliability of the observation data can be ensured, thereby further improving the accuracy of orbit determination and effectively improving the accuracy and efficiency of orbit determination. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] Figure 1 It is a flowchart of the steps of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS
[0015] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.
[0016] As Figure 1 shown, the present invention provides a method for accurately determining the orbit of a space target, including the following steps: Step 1: Set the parameters of the optical observation device and the observation platform; In step one, determine the positions of the optical observation device and the observation platform in the epoch geocentric celestial coordinate system, including but not limited to geographical coordinates and altitude, and then set the specific parameters of the optical observation device, including but not limited to the focal length of the telescope, the type of sensor, and the resolution.
[0017] Ensure that the optical observation device and the observation platform are in the best state to provide a solid foundation for the accurate determination of the space target orbit.
[0018] Step 2: Calculate the position of the target in the epoch geocentric celestial coordinate system; Input two rows of data of the target orbit, and the two rows of data include but not limited to the basic information and parameters of the target orbit; according to the two rows of data, use the orbital mechanics model and related algorithms to calculate the position of the target in the epoch geocentric celestial coordinate system. This provides a basis for subsequent observations and data analysis. By accurately calculating the positions of the platform and the target, the accuracy and reliability of the observation data can be ensured, thereby further improving the accuracy of orbit determination.
[0019] Step 3: Obtain the information of the imaging of the same target by the observation platform within a period of time, and calculate the observed time period. Specifically, it includes the following steps: Step A1: Continuously or intermittently image and observe a specific space target through a space-based optical monitoring platform, and collect the image data of the target at different time points. Step A2: Process and analyze the collected image data. Step A3: Based on the processed data, calculate the continuous observation time period of the space-based optical monitoring platform for the same target. Step A4: Record the calculated observation time period and use it as the input data for subsequent orbit determination and prediction.
[0020] Among them, in Step A1, the image data includes but is not limited to the position, velocity, and acceleration of the target; in Step A2, the image data processing includes but is not limited to image denoising, enhancement, and feature extraction.
[0021] Step 3 involves multiple aspects such as data collection, processing, analysis, and calculation. Through this step, the continuous observation time period of the space-based optical monitoring platform for the same target can be obtained, providing important data support for subsequent orbit determination and prediction.
[0022] Step 4: Construct an optimization objective function with the distance between the starting point and the ending point within the imaging duration as the undetermined parameter, and solve the optimization problem. Use mathematical methods and algorithms to solve the optimization problem, obtain the minimum or maximum value of the objective function, and determine the optimal orbit parameters; convert the solution result into orbit state variables, and use the orbit state variables as undetermined parameters to construct the optimization objective function again; improve the orbit determination accuracy by using the least squares method or other numerical methods to improve the orbit state variables; repeat the above process iteratively to improve the accuracy. Improve the orbit determination accuracy by constructing and solving the optimization problem. This step needs to comprehensively consider multiple factors such as observation data, random noise, and algorithm performance.
[0023] Step 5: Set up an additional observation platform, construct a dual-platform system, and use the principle of triangulation to achieve the solution of the space target position. Two observation platforms observe the same space target at different positions to obtain different perspectives and observation data; based on the principle of triangulation, using the target angle information observed by the two platforms, the precise position of the target in space is calculated; the calculated target position and the angle measurement information are jointly input into the unscented Kalman filter algorithm, and through the steps of target state prediction, observation prediction, unscented transformation, and state update, iterative optimization is carried out to obtain a more accurate target orbit. By constructing a binocular observation system, using the principle of triangulation to solve the target position, and combining with the unscented Kalman filter algorithm to improve the accuracy of orbit determination.
[0024] Step Six: Generate a new ephemeris of the space target according to the precise orbit determination result; The generated new ephemeris of the space target contains the position and velocity information of the space target in a future period of time. By generating a new ephemeris, it provides a basis for subsequent orbit prediction and tracking, and high-precision models and algorithms are used to ensure the accuracy and reliability of the new ephemeris.
[0025] Step Seven: Modify two lines of data of the target orbit, and repeat Steps Three to Six to determine the target orbit; Modify two lines of data of the target orbit to change the initial position, velocity, and orbital inclination parameters of the target; after completing the orbit determination process of the modified target orbit, perform statistical analysis on all results. By modifying and repeatedly calculating the target orbit data, and performing statistical analysis on the results, the performance and reliability of the orbit determination method are comprehensively evaluated.
[0026] It should be noted that in this article, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements, but also includes other elements not expressly listed, or also includes elements inherent to such process, method, article or device.
[0027] Although the embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that various changes, modifications, substitutions and variations can be made in these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the appended claims and their equivalents.
Claims
1. A method for accurately determining the orbit of a space target, characterized in that It includes the following steps: Step 1: Set the parameters of the optical observation equipment and the observation platform; Step 2: Calculate the position of the target in the geocentric celestial coordinate system at the epoch; Step 3: Obtain the information of the observation platform imaging the same target within a period of time, and calculate the observed time period; Step 4: Construct an optimization objective function with the distance between the starting point and the ending point within the imaging duration as the undetermined parameter, and solve the optimization problem; Step 5: Set up an additional observation platform, construct a dual-platform system, and use the principle of triangulation to realize the solution of the spatial target position; Step 6: Generate a new ephemeris of the spatial target according to the precise orbit determination result; Step 7: Change the two-line data of the target orbit, and repeat Steps 3 to 6 to determine the target orbit.
2. The method for accurately determining the orbit of a space target according to claim 1, wherein: In Step 1, determine the positions of the optical observation equipment and the observation platform in the geocentric celestial coordinate system at the epoch, including but not limited to geographical coordinates and altitude, and then set the specific parameters of the optical observation equipment, including but not limited to the focal length of the telescope, the type of sensor, and the resolution.
3. A method for accurately determining the orbit of a space target according to claim 1, characterized in that: In Step 2, input the two-line data of the target orbit, and the two-line data include but not limited to the basic information and parameters of the target orbit; according to the two-line data, use the orbit mechanics model and related algorithms to calculate the position of the target in the geocentric celestial coordinate system at the epoch.
4. A method for accurately determining the orbit of a space target according to claim 1, characterized in that: In Step 3, it includes the following steps: Step A1: Continuously or intermittently image and observe a specific spatial target through a space-based optical monitoring platform, and collect the image data of the target at different time points; Step A2: Process and analyze the collected image data; Step A3: Based on the processed data, calculate the continuous observation time period of the space-based optical monitoring platform for the same target; Step A4: Record the calculated observation time period and use it as the input data for subsequent orbit determination and prediction.
5. A method for accurately determining the orbit of a space target according to claim 4, characterized in that: In Step A1, the image data includes but not limited to the position, velocity, and acceleration of the target; in Step A2, the image data processing includes but not limited to image denoising, enhancement, and feature extraction.
6. The method for accurately determining the orbit of a space target according to claim 1, characterized in that: In Step 4, use mathematical methods and algorithms to solve the optimization problem, obtain the minimum or maximum value of the objective function, and determine the optimal orbit parameters; Convert the solution result into orbit state variables, and use the orbit state variables as undetermined parameters to construct an optimization objective function again; improve the orbit determination accuracy by improving the orbit state variables through the least squares method or other numerical methods; repeat the above process iteratively to improve the accuracy.
7. A method for accurately determining the orbit of a space target according to claim 1, characterized in that: In Step 5, the two observation platforms observe the same spatial target at different positions, and obtain different perspectives and observation data; Based on the principle of triangulation, use the target angle information observed by the two platforms to calculate the precise position of the target in space; jointly input the calculated target position and the angle measurement information into the unscented Kalman filter algorithm, and through the steps of target state prediction, observation prediction, unscented transformation, and state update, iterate and optimize to obtain a more accurate target orbit.
8. A method for accurately determining the orbit of a space target according to claim 1, characterized in that: In Step 6, the generated new ephemeris of the spatial target contains the position and velocity information of the spatial target within a future period of time.
9. The method for accurately determining the orbit of a space target according to claim 1, characterized in that: In step 7, two rows of data of the target orbit are modified to change the initial position, velocity, and orbital inclination parameters of the target. After the orbit determination process of the target orbit after all modifications is completed, statistical analysis is performed on all results.