Screening method of space dangerous rendezvous targets, computer equipment and readable storage medium

Abstract

The invention relates to the technical field of spaceflight, and particularly discloses a method for screening space dangerous rendezvous targets, and the method comprises the steps: obtaining the orbital elements of a target spacecraft and each space target in a to-be-screened target set; a first target set is obtained through screening according to forecast moments and far and near point heights corresponding to the orbital elements of the space targets; determining an orbital plane intersection line, an intersection point position and intersection point passing time of the target spacecraft and each space target in the first target set, and performing screening to obtain a second target set; setting an extrapolation interval and stepping, and forecasting the positions of the target spacecraft and each space target in the second target set under each stepping, so as to screen each space target in the second target set to obtain a third target set; and correcting the rendezvous time of each space target in the third target set and the target spacecraft to obtain a danger rendezvous target set and a danger rendezvous time window sequence. Therefore, the screening accuracy and integrity of the dangerous rendezvous targets are improved.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a method for screening dangerous space rendezvous targets, a computer device, and a readable storage medium. Background Art

[0002] Space collision warning technology mainly includes space catalog data acquisition, real-time orbit update, dangerous target screening, collision risk assessment, etc. The methods of screening dangerous targets usually include altitude screening, geometric screening, and time screening. By screening dangerous targets, most of the space targets that do not intersect with the spacecraft can be eliminated, and the collision risk assessment of the remaining targets can be performed to determine the safety of the spacecraft on orbit.

[0003] However, the current methods for screening dangerous targets have low accuracy and still cannot guarantee the safety of spacecraft. Summary of the invention

[0004] Based on this, it is necessary to provide a method for screening dangerous space rendezvous targets, a computer device and a readable storage medium to address the above problems.

[0005] According to a first aspect of an embodiment of the present application, a method for screening dangerous space rendezvous targets is provided, comprising: Obtain the orbital elements of the target spacecraft and the orbital elements of each space target in the target set to be screened; Screening each space target in the target set to be screened according to the predicted time corresponding to the orbital element of the space target and the periapsis height of the space target to obtain a first target set; respectively determining the orbital plane intersection line, intersection position and intersection time of the target spacecraft and each space target in the first target set, and screening each space target in the first target set according to the intersection position and intersection time to obtain a second target set; Setting an extrapolation interval and a step, and predicting the position of the target spacecraft and each space target in the second target set at each step, so as to screen each space target in the second target set to obtain a third target set; The rendezvous time between each of the space targets in the third target set and the target spacecraft is corrected to obtain a dangerous rendezvous target set and a dangerous rendezvous time window sequence.

[0006] In one embodiment, the step of screening each space target in the target set to be screened according to the predicted time corresponding to the orbital element of the space target and the apogee height of the space target to obtain the first target set includes: Filtering out space targets whose forecast moments corresponding to the orbital elements fall within the warning time interval from the set of targets to be filtered, to obtain a set of space targets; For each space target in the space target set: if the perigee height of the target spacecraft and the apogee height of the space target exceed the safety distance, or the perigee height of the space target and the apogee height of the target spacecraft exceed the safety distance, the corresponding space target will be removed from the space target set to obtain the first target set.

[0007] In one embodiment, the step of respectively determining the orbital plane intersection line, intersection position, and intersection time of the target spacecraft and each space target in the first target set, and screening each space target in the first target set according to the intersection position and the intersection time to obtain the second target set includes: In the early warning time interval, the two-body model is used to determine the intersection line and intersection point positions of the orbital planes of the target spacecraft and each space target in the first target set. , and the crossing time , ; Determine each group Minimum value of And each group Minimum value of ; Will space goals and The space targets of are removed from the first target set to obtain the second target set, where: , is the distance threshold, is the time threshold.

[0008] In one embodiment, the step of setting the extrapolation interval and step, and predicting the position of the target spacecraft and each space target in the second target set at each step, so as to screen each space target in the second target set to obtain the third target set comprises: Setting a first extrapolation interval and a first step, and predicting the position of the target spacecraft under each first step using a simplified conventional perturbation model and the position of each space target in the second target set ; Determine each group Minimum value of ; Will The space target is removed from the second target set to obtain a first set; Setting a second extrapolation interval and a second step, and using a high-precision orbit prediction model to predict the position of the target spacecraft at each of the second steps , using a simplified conventional perturbation model to predict the position of each of the space targets in the first set at each of the second steps ; Determine each group Minimum value of ; Will The space targets are removed from the first set to obtain the third target set; in, and Both are distance thresholds.

[0009] In one embodiment, the first extrapolation interval is , the second extrapolation interval is ,in, for The corresponding forecast time is is the time threshold, .

[0010] In one embodiment, , the first step is greater than the second step.

[0011] In one of the embodiments, in the step of correcting the rendezvous time between each of the space targets in the third target set and the target spacecraft, the Newton iteration method is used to correct the rendezvous time.

[0012] In one of the embodiments, before the step of screening each space target in the target set to be screened to obtain the first target set, the method for screening space dangerous intersection targets further includes: splitting each space target in the target set to be screened into a plurality of sub-sets; For each of the subsets, subsequent screening steps are performed respectively, and the dangerous intersection target set is a set of third target sets obtained after screening each of the subsets respectively.

[0013] According to a second aspect of an embodiment of the present application, there is provided a computer device, comprising a memory and a processor, wherein the memory stores a computer program, and the processor implements the above-mentioned method for screening space hazardous rendezvous targets when executing the computer program.

[0014] According to a third aspect of an embodiment of the present application, there is provided a computer-readable storage medium on which a computer program is stored. When the computer program is executed by a processor, the above-mentioned method for screening space hazardous rendezvous targets is implemented.

[0015] The method for screening dangerous space rendezvous targets provided in the embodiment of the present application can first obtain the orbital elements of the target spacecraft and the orbital elements of each space target in the target set to be screened, and then preliminarily screen each space target in the target set to be screened according to the predicted time corresponding to the orbital elements of the space target and the periapsis height of the space target to obtain a first target set, and then respectively determine the orbital plane intersection line, intersection position and intersection time between the target spacecraft and each space target in the first target set, and further screen each space target in the first target set according to the intersection position and intersection time to obtain a second target set, and then set the extrapolation interval and step, and predict the position of the target spacecraft and each space target in the second target set under each step, so as to screen each space target in the second target set again to obtain a third target set, and finally correct the rendezvous time between each space target in the third target set and the target spacecraft to obtain a dangerous rendezvous target set and a dangerous rendezvous time window sequence. Therefore, through the above-mentioned multiple screenings, we have broken through the conventional screening limited to the two-body sense, and comprehensively considered the influence of various factors on the orbital elements. The final set of dangerous rendezvous targets and dangerous rendezvous time window sequence are more complete and accurate, avoiding missed alarms. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A flowchart of a method for screening dangerous space rendezvous targets provided in one embodiment of the present application; Figure 2 A flowchart of step S300 in a method for screening dangerous space rendezvous targets provided in an embodiment of the present application; Figure 3 A schematic diagram of the structure of a computer device provided in one embodiment of the present application. DETAILED DESCRIPTION

[0017] In order to facilitate the understanding of the present application, the present application will be described more fully below with reference to the relevant drawings. The preferred embodiments of the present application are given in the drawings. However, the present application can be implemented in many different forms and is not limited to the embodiments described herein. On the contrary, the purpose of providing these embodiments is to understand the disclosure of the present application more thoroughly and comprehensively.

[0018] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0019] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0020] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art to which this application belongs. The terms used herein in the specification of this application are only for the purpose of describing specific embodiments and are not intended to limit this application. The term "and / or" used herein includes any and all combinations of one or more of the related listed items.

[0021] In one embodiment, a method for screening dangerous space rendezvous targets is provided, by which space targets that have a risk of space collision with a target spacecraft within a warning time interval can be screened out more accurately and completely.

[0022] Reference Figure 1 The method for screening dangerous space rendezvous targets provided in this embodiment includes the following steps: Step S100, obtaining the orbital elements of the target spacecraft and the orbital elements of each space target in the target set to be screened; Step S300, screening each space target in the target set to be screened according to the predicted time corresponding to the orbital element of the space target and the periapsis height of the space target, to obtain a first target set; Step S500, respectively determining the orbital plane intersection line, intersection position and intersection time between the target spacecraft and each space target in the first target set, and screening each space target in the first target set according to the intersection position and intersection time to obtain a second target set; Step S700, setting an extrapolation interval and a step, and predicting the position of the target spacecraft and each space target in the second target set at each step, so as to screen each space target in the second target set to obtain a third target set; Step S900: Correct the rendezvous time between each of the space targets in the third target set and the target spacecraft to obtain a dangerous rendezvous target set and a dangerous rendezvous time window sequence.

[0023] The method for screening dangerous space rendezvous targets provided in the embodiment of the present application can first obtain the orbital elements of the target spacecraft and the orbital elements of each space target in the target set to be screened, and then preliminarily screen each space target in the target set to be screened according to the predicted time corresponding to the orbital elements of the space target and the periapsis height of the space target to obtain a first target set, and then respectively determine the orbital plane intersection line, intersection position and intersection time between the target spacecraft and each space target in the first target set, and further screen each space target in the first target set according to the intersection position and intersection time to obtain a second target set, and then set the extrapolation interval and step, and predict the position of the target spacecraft and each space target in the second target set under each step, so as to screen each space target in the second target set again to obtain a third target set, and finally correct the rendezvous time between each space target in the third target set and the target spacecraft to obtain a dangerous rendezvous target set and a dangerous rendezvous time window sequence. Therefore, through the above-mentioned multiple screenings, we have broken through the conventional screening limited to the two-body sense, and comprehensively considered the influence of various factors on the orbital elements. The final set of dangerous rendezvous targets and dangerous rendezvous time window sequence are more complete and accurate, avoiding missed alarms.

[0024] In step S100, the orbital elements of the target spacecraft and the orbital elements of each space target in the target set to be screened can be obtained first, wherein the orbital elements are also called orbital elements or orbital parameters, which are a set of parameters used to describe the state of a celestial body in its orbit. Usually, it refers to the six parameters necessary to describe the motion of a celestial body along a conic curve using the classical law of universal gravitation.

[0025] Reference Figure 2 In one embodiment, step S300, i.e., the step of screening the space targets in the target set to be screened according to the predicted time corresponding to the orbital element of the space target and the periapsis height of the space target to obtain the first target set, comprises: Step S310, filtering out space targets whose forecast moments corresponding to orbital elements fall within the warning time interval from the target set to be filtered, to obtain a space target set; Step S330, for each space target in the space target set: if the perigee height of the target spacecraft and the apogee height of the space target exceed the safety distance, or the perigee height of the space target and the apogee height of the target spacecraft exceed the safety distance, the corresponding space target is removed from the space target set to obtain the first target set.

[0026] In the above step S300, epoch time and near and far locations are mainly used for screening, so as to eliminate a large number of non-threatening space targets from the target set to be screened.

[0027] Among them, the first is to perform epoch time screening, that is, to screen out the space targets whose forecast moments corresponding to the orbital elements fall within the warning time interval from the target set to be screened, and obtain the space target set. This is because the accuracy of the orbital encounter is restricted by the forecast time length. As the forecast period increases, its forecast accuracy will decrease. Therefore, some orbital elements with too long forecast periods can be removed first. For example, the warning time interval is , the predicted time of the orbital element of a space target is ,like , the space target can be removed from the set of targets to be screened. is the screening threshold. In this embodiment, it can be set to .

[0028] After the epoch time is screened, the perigee and apogee can be screened. Specifically, assuming that the perigee height of the target spacecraft is , the apogee height is , the perigee height of the space target is , the apogee height is , then, if Compare Above safe distance ,or, Compare Above safe distance , it means that in the short-term forecast process, the target spacecraft will not collide with the space target, and the space target can be removed from the space target set. Set to .

[0029] Through epoch time screening and near and far location screening, a large number of non-threatening targets can be preliminarily screened out, and the remaining space targets constitute the first target set.

[0030] Subsequently, a secondary precise screening can be carried out. The secondary precise screening process comprehensively considers the perturbation factors. The main perturbation factors are the long-term term of the earth's oblateness perturbation and the atmospheric damping perturbation. By using TwoBody (two-body model) distance screening, SGP4 (Simplified General Perturbations 4, simplified general perturbation model) distance screening, HPOP (High Precision Orbit Propagator, high-precision orbit prediction model) distance screening and time screening, dangerous targets can be quickly screened out, and then the time window sequence of high-risk rendezvous can be obtained completely and accurately.

[0031] In one embodiment, step S500, i.e., the step of respectively determining the orbital plane intersection line, intersection position, and intersection time of the target spacecraft and each space target in the first target set, and screening each space target in the first target set according to the intersection position and the intersection time, to obtain the second target set includes: Step S510: within the warning time interval, using the two-body model to determine the intersection line and intersection point positions of the orbital planes of the target spacecraft and each space target in the first target set. , and the crossing time , ; Step S520: Determine the Minimum value of And each group Minimum value of ; Step S530: space goals and The space targets of are removed from the first target set to obtain the second target set, where: , is the distance threshold, is the time threshold.

[0032] In this embodiment, the distance threshold Set to , you can Set to .

[0033] In one embodiment, step S700, i.e., setting the extrapolation interval and step, and predicting the position of the target spacecraft and each space target in the second target set at each step, so as to screen each space target in the second target set and obtain the third target set, comprises: Step S710: Set a first extrapolation interval and a first step, and use a simplified conventional perturbation model to predict the position of the target spacecraft under each first step. and the position of each space target in the second target set ; Prior to this, the instantaneous osculating orbit elements of the target spacecraft can be first converted into orbit elements suitable for the SGP4 model.

[0034] Step S720: Determine the groups Minimum value of ; Step S730: The space target is removed from the second target set to obtain a first set; Step S740: Set a second extrapolation interval and a second step, and use a high-precision orbit prediction model to predict the position of the target spacecraft at each of the second steps. , using a simplified conventional perturbation model to predict the position of each of the space targets in the first set at each of the second steps ; Step S750: Determine the Minimum value of ; Step S760: The space targets are removed from the first set to obtain the third target set; in, and Both are distance thresholds.

[0035] In the above steps, SGP4 distance screening is first performed, and then a more accurate HPOP model is used for further screening. In the further screening process, the HPOP model and the SGP4 model are combined. Conventional geometric screening often increases the setting value of the approach distance D to reduce the risk of missed reports, which will lead to an increase in the number of misselected targets and a decrease in screening efficiency. In the embodiment of the present application, in the above step S700, SGP4 is used in combination with HPOP for distance screening, which can effectively reduce the risk of incorrectly screening or missing dangerous targets due to the minimum approach distance D being set too small.

[0036] Among them, for low-orbit space targets, SGP4 simplifies the complex perturbations of space targets during operation, taking into account general perturbations including the Earth's oblateness, the long-term and periodic perturbations of the sun and moon's gravity, and the gravitational resonance and orbital decay caused by atmospheric drag. Compared with the TwoBody forecast, the SGP4 forecast is more accurate, with a maximum position error of about 3 kilometers in a 3-day forecast (taking the onboard GNSS precision orbit as the nominal orbit).

[0037] HPOP is used for high-precision orbit prediction for spacecraft. HPOP takes orbit perturbations into account more comprehensively and uses a complete set of high-fidelity mechanical models, including the highest-precision Earth gravity field model JGM-2, the joint gravity field model, the sun-moon gravity field model, the atmospheric drag model, and the solar light pressure model, thereby providing more accurate orbit calculations. Compared with the SGP4 forecast, HPOP calculations take longer and have higher forecast accuracy. The maximum position error of the 3-day forecast is hundreds of meters (with the onboard GNSS precision orbit as the nominal orbit).

[0038] In one embodiment, the moment when the distance between the actual target spacecraft and the space target is the smallest is considered. is Therefore, the first extrapolation interval can be set to In addition, the second extrapolation interval can be set to ,in, for The corresponding forecast time is is the time threshold, .

[0039] In one embodiment, , the first step is greater than the second step.

[0040] In a specific example, the first step can be set to 1s and the second step can be set to 0.1s. for ,set up for ,set up for . You can set It is 30s and can be set 5s.

[0041] In one of the embodiments, in step S900, i.e., the step of correcting the rendezvous time between each of the space targets in the third target set and the target spacecraft, the Newton iteration method is used to correct the rendezvous time.

[0042] In the pre-selection, in order to speed up the calculation, the step time of the extrapolated orbit is set to 0.1s. However, for low-orbit targets, the displacement can reach about 700m within 0.1s, so the predicted orbit state is not accurate enough. In order to calculate more accurately The orbit state at the closest approach within the range, this embodiment uses the criterion that the relative position vector is perpendicular to the relative velocity vector at the closest approach, adopts the Newton iteration method to analyze the predicted value, and corrects the rendezvous time.

[0043] First, calculate the position error. Calculate the position error between the target spacecraft and the space target when the target spacecraft is closest to the space target. For the target spacecraft, when calculating the position error at the closest moment, select the covariance matrix closest to the minimum moment in time and project it into the encounter coordinate system. For space targets, since they are non-cooperative targets and lack accurate observation data, it is difficult to accurately calculate the variance matrix of their position errors. Therefore, in this embodiment, the historical data of orbital elements are used to fit the covariance evolution function, and the evolution function is used to calculate the position covariance matrix at the closest moment; Secondly, correct the initial value of the orbit state. Use the position covariance matrix to correct the initial value of the orbit state at the time of rendezvous, set the velocity vector to a constant value, and the position vector changes linearly with time; Finally, the rendezvous time is corrected. The Newton iteration method is used to quickly converge to obtain the correction value of the rendezvous time. Δt R , correct The corresponding forecast time is the target spacecraft and space target in the warning time interval [ ] is a time window sequence of high-risk encounters within .

[0044] Conventional time screening will miss the interval corresponding to the actual intersection time when it is far away. In this embodiment, by correcting the initial value and time of the intersection orbit state, the interval corresponding to the intersection time can still be obtained when it is far away from the intersection time, which has good stability.

[0045] Since the number of cataloged space targets is very large, if all high-precision models are used, the calculation of orbital extrapolation and rendezvous relationship will be huge, which will consume a lot of time and cannot meet the timeliness requirements of early warning. Therefore, in order to save calculation time, this method first uses a variety of screening methods to quickly screen out a large number of non-threatening low-orbit targets and time intervals to improve the calculation speed, and then uses the Newton iteration method to accurately correct the dangerous rendezvous time between the spacecraft and the low-orbit target, so as to obtain a complete and accurate sequence of high-risk rendezvous time windows.

[0046] This solution not only ensures high-precision orbit extrapolation, effectively solves the problem of missed dangerous time intervals caused by perturbation factors, but also greatly improves the timeliness of early warning.

[0047] In one of the embodiments, before step S300, i.e., the step of screening each space target in the target set to be screened to obtain the first target set, the method for screening space dangerous intersection targets further includes: splitting each space target in the target set to be screened into a plurality of sub-sets; For each of the subsets, subsequent screening steps are performed respectively, and the dangerous intersection target set is a set of third target sets obtained after screening each of the subsets respectively.

[0048] That is to say, the present application can adopt multi-threaded parallel computing, which has fast computing speed and clear physical meaning, and can obtain the changing law of dangerous time interval, laying the foundation for subsequent collision risk assessment.

[0049] Specifically, parallel computing can be implemented based on the CUDA architecture, and CPU-GPU collaborative computing can significantly accelerate the screening of spatial targets.

[0050] In one embodiment, a computer device is provided, including a memory and a processor, wherein the memory stores a computer program, and the processor implements the above-mentioned method for screening space hazardous rendezvous targets when executing the computer program.

[0051] Figure 3 This is a schematic diagram of the structure of a computer device provided in an embodiment of the present application. The computer device may be a server, and its internal structure diagram may be as follows: Figure 3 As shown. The computer device includes a processor, a memory and a network interface connected through a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store various types of data involved in the method for screening space dangerous rendezvous targets. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, a method for screening space dangerous rendezvous targets is implemented.

[0052] Those skilled in the art will understand that Figure 3 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine certain components, or have a different arrangement of components.

[0053] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the method for screening space hazardous rendezvous targets is implemented.

[0054] In one embodiment, a computer program product is provided, including a computer program, which implements the steps in the above method embodiments when executed by a processor.

[0055] Those of ordinary skill in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to memory, storage, database or other media used in the embodiments provided in this application can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory (ROM), tape, floppy disk, flash memory or optical memory, etc. Volatile memory can include random access memory (RAM) or external cache memory. As an illustration and not limitation, RAM can be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM).

[0056] The technical features of the above-described embodiments may be arbitrarily combined. To make the description concise, not all possible combinations of the technical features in the above-described embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0057] The above-described embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be construed as limiting the scope of the patent. It should be noted that, for a person of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the attached claims.

Claims

1. A method for screening dangerous space rendezvous targets. It is characterized in that include: Obtain the orbital elements of the target spacecraft and the orbital elements of each space target in the target set to be screened; Screening each space target in the target set to be screened according to the predicted time corresponding to the orbital element of the space target and the periapsis height of the space target to obtain a first target set; respectively determining the orbital plane intersection line, intersection position and intersection time of the target spacecraft and each space target in the first target set, and screening each space target in the first target set according to the intersection position and intersection time to obtain a second target set; Setting an extrapolation interval and a step, and predicting the position of the target spacecraft and each space target in the second target set at each step, so as to screen each space target in the second target set to obtain a third target set; The rendezvous time between each of the space targets in the third target set and the target spacecraft is corrected to obtain a dangerous rendezvous target set and a dangerous rendezvous time window sequence.

2. The method for screening dangerous space rendezvous targets according to claim 1, It is characterized in that The step of screening each space target in the target set to be screened according to the predicted time corresponding to the orbital element of the space target and the apogee height of the space target to obtain the first target set comprises: Filtering out space targets whose forecast moments corresponding to the orbital elements fall within the warning time interval from the set of targets to be filtered, to obtain a set of space targets; For each space target in the space target set: if the perigee height of the target spacecraft and the apogee height of the space target exceed the safety distance, or the perigee height of the space target and the apogee height of the target spacecraft exceed the safety distance, the corresponding space target will be removed from the space target set to obtain the first target set.

3. The method for screening dangerous space rendezvous targets according to claim 1, It is characterized in that The step of respectively determining the orbital plane intersection line, intersection position and intersection time between the target spacecraft and each space target in the first target set, and screening each space target in the first target set according to the intersection position and intersection time to obtain the second target set comprises: In the early warning time interval, the two-body model is used to determine the intersection line and intersection point positions of the orbital planes of the target spacecraft and each space target in the first target set. , and the crossing time , ; Determine each group Minimum value of And each group Minimum value of ; Will space goals and The space targets of are removed from the first target set to obtain the second target set, where: , is the distance threshold, is the time threshold.

4. The method for screening dangerous space rendezvous targets according to claim 3, It is characterized in that The step of setting the extrapolation interval and step, and predicting the position of the target spacecraft and each space target in the second target set at each step, so as to screen each space target in the second target set to obtain the third target set comprises: Setting a first extrapolation interval and a first step, and predicting the position of the target spacecraft under each first step using a simplified conventional perturbation model and the position of each space target in the second target set ; Determine each group Minimum value of ; Will The space target is removed from the second target set to obtain a first set; Setting a second extrapolation interval and a second step, and using a high-precision orbit prediction model to predict the position of the target spacecraft at each of the second steps , using a simplified conventional perturbation model to predict the position of each of the space targets in the first set at each of the second steps ; Determine each group Minimum value of ; Will The space targets are removed from the first set to obtain the third target set; in, and Both are distance thresholds.

5. The method for screening dangerous space rendezvous targets according to claim 4, It is characterized in that The first extrapolation interval is , the second extrapolation interval is ,in, for The corresponding forecast time is is the time threshold, .

6. The method for screening dangerous space rendezvous targets according to claim 4, It is characterized in that , the first step is greater than the second step.

7. The method for screening dangerous space rendezvous targets according to claim 1, It is characterized in that In the step of correcting the rendezvous time between each of the space targets in the third target set and the target spacecraft, the Newton iteration method is used to correct the rendezvous time.

8. The method for screening dangerous space rendezvous targets according to claim 1, It is characterized in that Before the step of screening each space target in the target set to be screened to obtain the first target set, the method for screening space dangerous intersection targets further comprises: splitting each space target in the target set to be screened into a plurality of sub-sets; For each of the subsets, subsequent screening steps are performed respectively, and the dangerous intersection target set is a set of third target sets obtained after screening each of the subsets respectively.

9. A computer device, It is characterized in that The method comprises a memory and a processor, wherein the memory stores a computer program, and the processor implements the method for screening dangerous space rendezvous targets as described in any one of claims 1 to 8 when executing the computer program.

10. A computer-readable storage medium having a computer program stored thereon, It is characterized in that When the computer program is executed by a processor, the method for screening dangerous space rendezvous targets according to any one of claims 1 to 8 is implemented.

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