A method for rapid orbit prediction of space targets based on optical observation

Abstract

The invention discloses a method for rapid orbit prediction of space targets based on optical observation, which belongs to the field of space orbit prediction. The method for rapid orbit prediction of space targets based on optical observation has the following specific steps: parameter determination of space targets, preliminary determination of space targets, determination of reference orbits of space targets, state parameter splitting of space targets, verification of reference orbits, segmentation verification of space target running trajectories, calculation of separated trajectories, splicing of separated running trajectories, determination of predicted trajectories, determination of target running trajectories and safety prediction. It can rapidly predict the orbits of space targets to a large extent, while ensuring the docking safety and flight safety of space targets.

Description

Technical Field

[0001] The present invention relates to the field of space orbit prediction, and more specifically, to a method for rapid orbit prediction of space targets based on optical observation. Background Art

[0002] A space target refers to a target or moving object in the air. When a space target moves, it will evolve into a corresponding moving trajectory over time. At this time, the future orbit of the space target is predicted based on the space target's operating posture and the external environmental factors in which the space target is located at that time, and it is subdivided based on whether the space target has a power source.

[0003] Based on the above, the inventors found that:

[0004] When predicting the future orbit of a space target, if the space target is not in the predetermined space orbit, the orbit of the space target needs to be clarified. If there are docking targets or other operating targets near the space target, the docking of the space target may fail or the operating attitude may be disturbed during the detailed analysis and prediction of the space target's orbit.

[0005] Therefore, in view of this, the existing structure is studied and improved to provide a method for rapid orbit prediction of space targets based on optical observation, in order to achieve a more practical purpose. Summary of the invention

[0006] 1. Technical issues to be solved

[0007] In view of the problems existing in the prior art, the purpose of the present invention is to provide a method for rapid orbit prediction of space targets based on optical observation, which can quickly predict the orbit of space targets to a large extent while ensuring the docking safety and flight safety of space targets.

[0008] 2. Technical solution

[0009] To solve the above problems, the present invention adopts the following technical solutions.

[0010] A method for rapid orbit prediction of space targets based on optical observation, the specific steps of which are as follows:

[0011] Step S1, determining the parameters of the space target: selecting the space target to be observed and obtaining the state parameters of the space target;

[0012] Step S2, preliminary determination of the space target: based on the space target selection in step S1, the current orbital parameters of the space target are obtained based on the optical observation method, and the matching between the state parameters of the space target and the orbital parameters is determined;

[0013] Step S3, determining the reference orbit of the space target; based on step S1, when it is determined that there is no match between the state parameters of the space target and the orbit parameters, determining the reference orbit of the current position of the space target;

[0014] Step S4, splitting the state parameters of the space target: based on the space target selection in step S1, and based on the fact that the state parameters of the space target do not match the orbital parameters in step S2, splitting the state parameters of the space target;

[0015] Step S5, verification of reference orbit: based on the data after the space target state parameter is split in step S4, the reference orbit is substituted for verification to determine whether the reference orbit of the space target is accurate. If the reference orbit is accurate, proceed to step S6;

[0016] Step S6, segmentation and verification of the space target running trajectory: collecting the running trajectory of the space target and dividing it into time periods, and then calculating the running trajectory in the divided time periods;

[0017] Step S7, calculation of the separated trajectory: based on the separated trajectory in step S6, performing trajectory calculation for each separated trajectory;

[0018] Step S8, splicing the separated running tracks: splicing multiple running tracks to determine the longer track of the space target;

[0019] Step S9, determination of predicted orbit: Substitute the orbit calculation of step S7 into step S8 to determine the computational orbit of the space target;

[0020] Step S10, determining the target object's running trajectory: Scanning the target object or obstacle near the space target based on the optical observation method, and determining the running trajectory of the target object or obstacle based on the steps of step S6, step S8 and step S9;

[0021] Step S11, safety forecast: Based on step S9 and step S10, determine the safety of the space target flight.

[0022] Furthermore, in step S1, the state parameters of the space target include the deadweight of the space target, the running direction of the space target, the running speed of the space target and the running posture of the space target.

[0023] Furthermore, in step S2, the orbital parameters of the space target obtained are the determined orbit of the space target.

[0024] Furthermore, in step S3, the conditions for determining the reference orbit include determining the operating altitude of the space target and determining the celestial body gravity to which the space target is subjected when the space target is at the position on the orbit;

[0025] The celestial bodies include the Earth gravity model, the Sun gravity model, the Moon gravity model, the Sun light pressure model, the atmospheric drag model, the Earth emission pressure model and the tidal perturbation model.

[0026] Furthermore, when the reference orbit is scheduled, a 50×50 order earth gravity model, sun gravity model, moon gravity model, solar light pressure model, atmospheric drag model, earth emission pressure model and tidal perturbation model are established.

[0027] Furthermore, when the state parameters of the space target are decomposed in step S4, the running direction of the space target, the running speed of the space target and the running posture of the space target are decomposed by using the cross decomposition method;

[0028] The cross decomposition method decomposes the running direction of the space target, including the running direction of the space target in the reference orbit and the running direction of the space target out of the predefined orbit;

[0029] The cross decomposition method decomposes the running speed of the space target, including the running speed of the space target in the reference orbit and the running speed of the space target out of the predefined orbit;

[0030] The cross decomposition method decomposes the running attitude of the space target, including the running attitude of the space target in the reference orbit and the running attitude of the space target out of the predefined orbit.

[0031] Furthermore, in step S6, reference factors of the method for segmenting the running track include track length and running time.

[0032] Furthermore, when running track separation is performed:

[0033] When the space target is operating at a low altitude and at a low speed, the trajectory separation is performed using the same operating time period;

[0034] When the space target is in high altitude operation, the running tracks of the same length are used for segmentation;

[0035] When the space target is running at high speed, the running trajectories of the same length are used for segmentation.

[0036] Furthermore, the factors referenced when making the safety forecast in step S11 are the running time and running trajectory of the space target.

[0037] 3. Beneficial effects

[0038] Compared with the prior art, the advantages of the present invention are:

[0039] This scheme, when predicting the future flight orbit of a space target, verifies the determined orbit of the space target based on the state parameters such as the space target's own weight, running direction, running speed and running attitude, and then calculates the reference orbit of the space target in conjunction with the space target's altitude and the gravity of the celestial body. When the space target is not in a determined orbit or a reference orbit, the cross decomposition method is used to decompose the state parameters of the space target and make a final prediction of the orbit of the space target. At the same time, the same method is used to predict the running orbit of the space target's docking or possible obstacles, and to determine the precise docking of the space target or the safety of the flight attitude. This method can quickly predict the orbit of the space target to a large extent, while ensuring the docking safety and flight safety of the space target. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 It is a schematic diagram of the process of the present invention. DETAILED DESCRIPTION

[0041] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention; it is obvious that the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments, and all other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making creative work are within the scope of protection of the present invention.

[0042] Embodiment 1:

[0043] See also Figure 1 ,A method for rapid orbit prediction of space targets based on optical observation, the specific steps are as follows;

[0044] Step S1, determining the parameters of the space target: selecting the space target to be observed and obtaining the state parameters of the space target;

[0045] Step S2, preliminary determination of the space target: based on the space target selection in step S1, the current orbital parameters of the space target are obtained based on the optical observation method, and the matching between the state parameters of the space target and the orbital parameters is determined;

[0046] Step S3, determining the reference orbit of the space target; based on step S1, when it is determined that there is no match between the state parameters of the space target and the orbit parameters, determining the reference orbit of the current position of the space target;

[0047] Step S4, splitting the state parameters of the space target: based on the space target selection in step S1, and based on the fact that the state parameters of the space target do not match the orbital parameters in step S2, splitting the state parameters of the space target;

[0048] Step S5, verification of reference orbit: based on the data after the space target state parameter is split in step S4, the reference orbit is substituted for verification to determine whether the reference orbit of the space target is accurate. If the reference orbit is accurate, proceed to step S6;

[0049] Step S6, segmentation and verification of the space target running trajectory: collecting the running trajectory of the space target and dividing it into time periods, and then calculating the running trajectory in the divided time periods;

[0050] Step S7, calculation of the separated trajectory: based on the separated trajectory in step S6, performing trajectory calculation for each separated trajectory;

[0051] Step S8, splicing the separated running tracks: splicing multiple running tracks to determine the longer track of the space target;

[0052] Step S9, determination of predicted orbit: Substitute the orbit calculation of step S7 into step S8 to determine the computational orbit of the space target;

[0053] Step S10, determining the target object's running trajectory: Scanning the target object or obstacle near the space target based on the optical observation method, and determining the running trajectory of the target object or obstacle based on the steps of step S6, step S8 and step S9;

[0054] Step S11, safety forecast: Based on step S9 and step S10, determine the safety of the space target flight.

[0055] Example 2

[0056] Based on the above-mentioned embodiment 1, further discussion is given.

[0057] See also Figure 1 , in step S1, the state parameters of the space target include the deadweight of the space target, the running direction of the space target, the running speed of the space target and the running posture of the space target;

[0058] Whether the current running state of the space target is controllable is determined by the deadweight of the space target and the running posture of the space target, and the running direction and speed of the space target determine the running orbit of the space target.

[0059] See also Figure 1 , in step S2, the orbital parameters of the space target obtained are the determined orbit of the space target;

[0060] When a space target is running on a known orbit, the orbital parameters are selected for calculation and substituted into the state parameters of the space target to determine whether the state parameters of the space target match the orbital parameters and whether it is in the normal operating state of the orbit. When the state parameters of the space target match the orbital parameters, the orbital parameters are the operating orbit of the space target.

[0061] See also Figure 1 In step S3, the conditions for determining the reference orbit include determining the operating altitude of the space target and determining the celestial body gravity to which the space target is subjected when the space target is at the position in the orbit;

[0062] The celestial bodies include the gravity of the earth, the sun, the moon, the solar light pressure, the atmospheric drag, the earth's emission pressure and the tidal perturbations;

[0063] Simply determine the reference orbit of the space target. If the space target is at this position and orbits the reference orbit, the reference orbit is the orbit of the space target. Among them, for the different position heights of the space target, the factors that affect the operating attitude of the space target from the earth's gravity, the sun's gravity, the moon's gravity, the sun's light pressure, the atmospheric drag, the earth's emission pressure and the tidal perturbation are selected for analysis to ensure the accuracy of the reference orbit of the space target.

[0064] See also Figure 1 , when the reference orbit is scheduled, a 50×50 order earth gravity model, sun gravity model, moon gravity model, sun light pressure model, atmospheric drag model, earth emission pressure model and tidal perturbation model are established;

[0065] By establishing a model and calculating the reference orbit, the interference of other uncontrollable factors in calculating the reference orbit can be reduced, while ensuring the rapid calculation of the reference orbit under the gravitational effect of multiple factors.

[0066] See also Figure 1 , when splitting the state parameters of the space target in step S4, the cross decomposition method is used to decompose the running direction of the space target, the running speed of the space target and the running posture of the space target;

[0067] The cross decomposition method decomposes the running direction of the space target, including the running direction of the space target in the reference orbit and the running direction of the space target out of the predefined orbit;

[0068] The cross decomposition method decomposes the running speed of the space target, including the running speed of the space target in the reference orbit and the running speed of the space target out of the predefined orbit;

[0069] The cross decomposition method decomposes the running attitude of the space target, including the running attitude of the space target in the reference orbit and the running attitude of the space target out of the predefined orbit;

[0070] By using the cross decomposition method to decompose the moving direction, moving speed and moving attitude of the space target, it is possible to quickly determine whether the space target is moving smoothly within the reference orbit.

[0071] See also Figure 1 , in step S6, the reference factors of the method for segmenting the running track include the track length and the running time;

[0072] According to the actual operation of the space target, the trajectory length or running time is used for separation, which makes it easy to ensure the uniformity and rationality of trajectory separation.

[0073] See also Figure 1 , when running track separation:

[0074] When the space target is operating at a low altitude and at a low speed, the trajectory separation is performed using the same operating time period;

[0075] When the space target is in high altitude operation, the running tracks of the same length are used for segmentation;

[0076] When the space target is running at high speed, the running tracks of the same length are used for segmentation;

[0077] According to the operating status parameters of the space target, different methods are used to separate the trajectories, ensuring that the operating orbit of the space target can be quickly calculated.

[0078] See also Figure 1 , the factors referenced when making safety forecast in step S11 are the running time and running trajectory of the space target;

[0079] When the space target and the docking are at the same running time and docking is guaranteed, or the space target and the obstacle are at the same running time and no space trajectory interaction occurs, the space target is determined to be in a safe state.

[0080] Example 3

[0081] Based on the above-mentioned Embodiment 1 and Embodiment 2, further discussion is given.

[0082] When this method is used for rapid orbit prediction of space targets:

[0083] First, the space target to be observed is selected, and the parameters of the space target including the weight of the space target, the running direction of the space target, the running speed of the space target and the running attitude state of the space target are obtained;

[0084] Then, the determined orbital parameters of the space target are obtained, and the matching of the state parameters of the space target and the orbital parameters is determined. If the space target is at this position and orbits the reference orbit, the reference orbit is the orbit of the space target. According to the different position heights of the space target, the 50×50 order earth gravity model, solar gravity model, moon gravity model, solar light pressure model, atmospheric drag model, earth emission pressure model and tidal perturbation model are selected to analyze the factors affecting the running attitude of the space target, so as to ensure the accuracy of the reference orbit of the space target.

[0085] Then, the reference orbit is verified: based on the data after the state parameter of the space target is split in step S4, the reference orbit is substituted for verification to determine whether the reference orbit of the space target is accurate. When the reference orbit and the determined orbit are not suitable for the space target, the running direction, running speed and running attitude of the space target are decomposed by the cross decomposition method. When the running direction of the space target is decomposed by the cross decomposition method, it includes the running direction of the space target in the reference orbit and the running direction of the space target out of the predefined orbit. When the running speed of the space target is decomposed by the cross decomposition method, it includes the running speed of the space target in the reference orbit and the running speed of the space target out of the predefined orbit. When the running attitude of the space target is decomposed by the cross decomposition method, it includes the running attitude of the space target in the reference orbit and the running attitude of the space target out of the predefined orbit.

[0086] Then, the orbit calculation is performed for each segmented trajectory. In this process, when the space target is running at a low altitude and at a low speed, the trajectory is separated using the same running time period. When the space target is running at a high altitude, the running trajectory is separated using the same length. When the space target is running at a high speed, the running trajectory is separated using the same length. The running trajectories after separation are spliced, and multiple running trajectories are spliced ​​to determine the longer orbit of the space target, and then the calculation orbit of the space target is determined.

[0087] Then, based on the optical observation method, the target or obstacle near the space target is scanned, and the trajectory of the target is determined, the safety of the space target flight is confirmed, and a safety forecast is made;

[0088] This completes the entire method of rapid orbit prediction of space targets based on optical observation.

[0089] The above is only a preferred specific implementation of the present invention; however, the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes according to the technical solution and its improved conception within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A method for rapid orbit prediction of space targets based on optical observation, characterized in that: The specific steps are as follows; Step S1, determining the parameters of the space target: selecting the space target to be observed, and obtaining the state parameters of the space target; the state parameters of the space target include the deadweight of the space target, the running direction of the space target, the running speed of the space target and the running posture of the space target; Step S2, preliminary determination of the space target: based on the space target selection in step S1, the current orbital parameters of the space target are obtained based on the optical observation method, and the matching between the state parameters of the space target and the orbital parameters is determined; Step S3, determining the reference orbit of the space target; based on step S1, when it is determined that there is no match between the state parameters of the space target and the orbit parameters, determining the reference orbit of the current position of the space target; Step S4, splitting the state parameters of the space target: based on the space target selection in step S1, and based on the fact that the state parameters of the space target do not match the orbital parameters in step S2, splitting the state parameters of the space target; Step S5, verification of reference orbit: based on the data after the space target state parameter is split in step S4, the reference orbit is substituted for verification to determine whether the reference orbit of the space target is accurate. If the reference orbit is accurate, proceed to step S6; Step S6, segmentation and verification of the space target running trajectory: collecting the running trajectory of the space target and dividing it into time periods, and then calculating the running trajectory in the divided time periods; Step S7, calculation of the separated trajectory: based on the separated trajectory in step S6, performing trajectory calculation for each separated trajectory; Step S8, splicing the separated running tracks: splicing multiple running tracks to determine the longer track of the space target; Step S9, determination of predicted orbit: Substitute the orbit calculation of step S7 into step S8 to determine the computational orbit of the space target; Step S10, determining the target object's running trajectory: Scanning the target object or obstacle near the space target based on the optical observation method, and determining the running trajectory of the target object or obstacle based on the steps of step S6, step S8 and step S9; Step S11, safety forecast: Based on step S9 and step S10, determine the safety of the space target flight.

2. The method for rapid orbit prediction of space targets based on optical observation according to claim 1, characterized in that: In step S2, the orbital parameters of the space target obtained are the determined orbit of the space target.

3. The method for rapid orbit prediction of space targets based on optical observation according to claim 1, characterized in that: In step S3, the conditions for determining the reference orbit include determining the operating altitude of the space target and determining the celestial body gravity to which the space target is subjected when the space target is at the position on the orbit; The celestial bodies include the Earth gravity model, the Sun gravity model, the Moon gravity model, the Sun light pressure model, the atmospheric drag model, the Earth emission pressure model and the tidal perturbation model.

4. The method for rapid orbit prediction of space targets based on optical observation according to claim 3, characterized in that: When the reference orbit is scheduled, a 50×50 order earth gravity model, sun gravity model, moon gravity model, solar light pressure model, atmospheric drag model, earth emission pressure model and tidal perturbation model are established.

5. The method for rapid orbit prediction of space targets based on optical observation according to claim 1, characterized in that: When decomposing the state parameters of the space target in step S4, the running direction of the space target, the running speed of the space target and the running posture of the space target are decomposed by using the cross decomposition method; The cross decomposition method decomposes the running direction of the space target, including the running direction of the space target in the reference orbit and the running direction of the space target out of the predefined orbit; The cross decomposition method decomposes the running speed of the space target, including the running speed of the space target in the reference orbit and the running speed of the space target out of the predefined orbit; The cross decomposition method decomposes the running attitude of the space target, including the running attitude of the space target in the reference orbit and the running attitude of the space target out of the predefined orbit.

6. The method for rapid orbit prediction of space targets based on optical observation according to claim 1, characterized in that: In step S6, the reference factors of the method for segmenting the running track include the track length and the running time.

7. The method for rapid orbit prediction of space targets based on optical observation according to claim 6, characterized in that: When running track separation: When the space target is operating at a low altitude and at a low speed, the trajectory separation is performed using the same operating time period; When the space target is in high altitude operation, the running tracks of the same length are used for segmentation; When the space target is running at high speed, the running trajectories of the same length are used for segmentation.

8. The method for rapid orbit prediction of space targets based on optical observation according to claim 1, characterized in that: The factors referenced when making the safety forecast in step S11 are the running time and running trajectory of the space target.

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