Screening Method for Space Hazard Rendezvous Targets, Computer Device, and Readable Storage Medium

Abstract

This application relates to the field of space technology, and specifically discloses a method for screening space dangerous rendezvous targets, including obtaining the orbital elements of the target spacecraft and each space target in the set of targets to be screened; screening to obtain a first target set according to the prediction time and the perigee and apogee heights corresponding to the orbital elements of the space targets; respectively determining the orbital plane intersection lines, intersection positions, and times passing through the intersections of the target spacecraft and each space target in the first target set, and screening to obtain a second target set; setting an extrapolation interval and a step size and predicting the positions 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; correcting the rendezvous times of each space target in the third target set with the target spacecraft to obtain a dangerous rendezvous target set and a sequence of dangerous rendezvous time windows. Thereby, the screening accuracy and integrity of dangerous rendezvous targets are improved.

Description

Technical Field

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

[0002] Space collision warning technology mainly includes space catalog data acquisition, orbit real-time update, dangerous target screening, collision risk assessment, etc. The methods for 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 remaining targets can be evaluated for collision risk to determine the on-orbit safety of the spacecraft.

[0003] However, the accuracy of the current methods for screening dangerous targets is relatively low, and the safety of the spacecraft still cannot be guaranteed. Summary of the Invention

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

[0005] According to the first aspect of the embodiments of the present application, a method for screening space dangerous rendezvous targets is provided, including:

[0006] Obtain the orbital elements of the target spacecraft and the orbital elements of each space target in the set of targets to be screened;

[0007] Screen each space target in the set of targets to be screened according to the prediction time corresponding to the orbital elements of the space target and the perigee and apogee altitudes of the space target to obtain a first target set;

[0008] Determine the orbital plane intersection lines, intersection positions, and times passing through the intersections of the target spacecraft and each space target in the first target set respectively, and screen each space target in the first target set according to the intersection positions and times passing through the intersections to obtain a second target set;

[0009] Set an extrapolation interval and a step size, and predict the positions of the target spacecraft and each space target in the second target set at each step to screen each space target in the second target set to obtain a third target set;

[0010] Correct the rendezvous times of each space target in the third target set with the target spacecraft to obtain a set of dangerous rendezvous targets and a sequence of dangerous rendezvous time windows.

[0011] In one embodiment, the step of screening each space target in the target set to be screened according to the prediction time corresponding to the orbital elements of the space target and the apoapsis and periapsis altitudes of the space target to obtain a first target set includes:

[0012] Screening out the space targets in the target set to be screened whose prediction times corresponding to the orbital elements fall within the early warning time interval to obtain a space target set;

[0013] For each space target in the space target set: if the periapsis altitude of the target spacecraft and the apoapsis altitude of the space target exceed the safety distance, or the apoapsis altitude of the space target and the periapsis altitude of the target spacecraft exceed the safety distance, then the corresponding space target is removed from the space target set to obtain the first target set.

[0014] In one embodiment, the step of respectively determining the orbital plane intersection lines, intersection point positions, and times of intersection of the target spacecraft with each space target in the first target set, and screening each space target in the first target set according to the intersection point positions and times of intersection to obtain a second target set includes:

[0015] Within the early warning time interval, use the two-body model to determine the orbital plane intersection lines and intersection point positions of the target spacecraft with each space target in the first target set 、 and the times of intersection 、 ;

[0016] Determine the minimum values of each group and the minimum values of each group ; ; ;

[0017] Remove the space targets where and the space targets where from the first target set to obtain the second target set, where ; is the distance threshold, and is the time threshold.

[0018] In one embodiment, the step of setting an extrapolation interval and a step size, and predicting the positions of the target spacecraft and each space target in the second target set at each step size to screen each space target in the second target set to obtain a third target set includes:

[0019] Set a first extrapolation interval and a first step size, and use the simplified conventional perturbation model to predict the position of the target spacecraft at each of the first step sizes and the positions of each space target in the second target set ;

[0020] Determine each group of minimum values ;

[0021] Remove the space targets from the second target set to obtain the first set;

[0022] Set the second extrapolation interval and the second step size, and use the high-precision orbit prediction model to predict the positions of the target spacecraft at each of the second step sizes , and use the simplified conventional perturbation model to predict the positions of each of the space targets in the first set at each of the second step sizes ;

[0023] Determine each group of minimum values ;

[0024] Remove the space targets from the first set to obtain the third target set;

[0025] wherein, and are both distance thresholds.

[0026] In one embodiment, the first extrapolation interval is , and the second extrapolation interval is , wherein, is corresponding prediction time, is the time threshold, .

[0027] In one embodiment, , the first step size is greater than the second step size.

[0028] In one embodiment, in the step of correcting the rendezvous time of each of the space targets in the third target set with the target spacecraft, the Newton iteration method is used to correct the rendezvous time.

[0029] In one embodiment, before the step of screening each space target in the to-be-screened target set to obtain the first target set, the screening method for space dangerous rendezvous targets further includes: splitting each space target in the to-be-screened target set into several subsets;

[0030] For each of the said subsets, the subsequent screening steps are respectively executed, and the set of dangerous rendezvous targets is the set of third target sets obtained by respectively screening each of the said subsets.

[0031] According to the second aspect of the embodiments of the present application, there is provided a computer device, including a memory and a processor, where the memory stores a computer program, and when the processor executes the computer program, the above-mentioned screening method for spatial dangerous rendezvous targets is implemented.

[0032] According to the third aspect of the embodiments of the present application, there is provided a computer-readable storage medium, on which a computer program is stored, and when the computer program is executed by a processor, the above-mentioned screening method for spatial dangerous rendezvous targets is implemented.

[0033] The screening method for spatial dangerous rendezvous targets provided by the embodiments of the present application can first obtain the orbital elements of the target spacecraft and the orbital elements of each spatial target in the set of targets to be screened, and then, according to the prediction time corresponding to the orbital elements of the spatial target and the apoapsis and periapsis heights of the spatial target, preliminarily screen each spatial target in the set of targets to be screened to obtain a first target set. Then, respectively determine the orbital plane intersection lines, intersection point positions, and times passing through the intersection points of the target spacecraft and each spatial target in the first target set, and further screen each spatial target in the first target set according to the intersection point positions and times passing through the intersection points to obtain a second target set. Next, set the extrapolation interval and step size, and predict the positions of the target spacecraft and each spatial target in the second target set at each step to screen each spatial target in the second target set again to obtain a third target set. Finally, correct the rendezvous times of each spatial target in the third target set with the target spacecraft to obtain a set of dangerous rendezvous targets and a sequence of dangerous rendezvous time windows. Thus, through the above multiple screenings, the conventional screening limited to the two-body sense is broken through, and the influence of various factors on the orbital elements is comprehensively considered. The finally obtained set of dangerous rendezvous targets and the sequence of dangerous rendezvous time windows are more complete and accurate, avoiding false alarms. Description of the Drawings

[0034] Figure 1 It is a flowchart of the screening method for spatial dangerous rendezvous targets provided by an embodiment of the present application;

[0035] Figure 2 It is a flowchart of step S300 in the screening method for spatial dangerous rendezvous targets provided by an embodiment of the present application;

[0036] Figure 3 It is a schematic structural diagram of a computer device provided by an embodiment of the present application. Detailed Embodiments

[0037] To facilitate the understanding of this application, the following will provide a more comprehensive description of this application with reference to the relevant drawings. The preferred embodiments of this application are shown in the drawings. However, this 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 this application more thoroughly and comprehensively.

[0038] In this application, unless otherwise clearly specified and defined, terms such as "installation", "connection", "linkage", "fixation", etc. shall be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two components or the interaction relationship between two components, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0039] The terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of this application, the meaning of "a plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0040] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the technical field to which this application belongs. The terms used 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.

[0041] In one embodiment, a screening method for space dangerous rendezvous targets is provided. Through this screening method, space targets that pose a space collision risk to the target spacecraft within the early warning time interval can be screened out more accurately and completely.

[0042] Referring to Figure 1 , the screening method for space dangerous rendezvous targets provided in this embodiment includes the following steps:

[0043] Step S100: Obtain the orbital elements of the target spacecraft and the orbital elements of each space target in the set of targets to be screened;

[0044] Step S300: Screen each space target in the set of targets to be screened according to the prediction time corresponding to the orbital elements of the space target and the apoapsis and periapsis altitudes of the space target, and obtain a first target set;

[0045] Step S500: Determine the orbital plane intersection lines, intersection point positions, and times of passing through the intersection points of the target spacecraft and each space target in the first target set respectively, and screen each space target in the first target set according to the intersection point positions and times of passing through the intersection points to obtain a second target set;

[0046] Step S700: Set an extrapolation interval and a step size, and predict the positions 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;

[0047] Step S900: Correct the rendezvous times of each space target in the third target set with the target spacecraft to obtain a dangerous rendezvous target set and a sequence of dangerous rendezvous time windows.

[0048] For the screening method of space dangerous rendezvous targets provided by the embodiments of the present application, first, 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. Then, according to the predicted time corresponding to the orbital elements of the space target and the apoapsis and periapsis altitudes of the space target, each space target in the target set to be screened is preliminarily screened to obtain a first target set. Next, the orbital plane intersection lines, intersection point positions, and times of passing through the intersection points of the target spacecraft and each space target in the first target set are determined respectively, and each space target in the first target set is further screened according to the intersection point positions and times of passing through the intersection points to obtain a second target set. Then, an extrapolation interval and a step size are set, and the positions of the target spacecraft and each space target in the second target set at each step are predicted to screen each space target in the second target set again to obtain a third target set. Finally, the rendezvous times of each space target in the third target set with the target spacecraft are corrected to obtain a dangerous rendezvous target set and a sequence of dangerous rendezvous time windows. Thus, through the above multiple screenings, the limitation of the conventional screening limited to the two-body meaning is broken through, and the influence of various factors on the orbital elements is comprehensively considered. The finally obtained dangerous rendezvous target set and the sequence of dangerous rendezvous time windows are more complete and accurate, avoiding false alarms.

[0049] In step S100, first, 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. Among them, the orbital elements, also known as orbital elements or orbital parameters, are a set of parameters used to describe the orbital motion state of celestial bodies. Usually, it refers to the 6 parameters necessary to describe the motion of celestial bodies along conic curves using the classical law of universal gravitation.

[0050] Refer to Figure 2, in one embodiment, step S300, that is, the step of screening each space target in the to-be-screened target set according to the prediction time corresponding to the orbital elements of the space target and the perigee and apogee heights of the space target to obtain the first target set includes:

[0051] Step S310: Screen out the space targets in the to-be-screened target set whose prediction times corresponding to the orbital elements fall within the early warning time interval to obtain a space target set;

[0052] 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, then remove the corresponding space target from the space target set to obtain the first target set.

[0053] In the above steps of step S300, mainly the epoch time and the perigee and apogee are used for screening, and a large number of non-threatening space targets are removed from the to-be-screened target set.

[0054] Among them, first, epoch time screening is performed, that is, the space targets in the to-be-screened target set whose prediction times corresponding to the orbital elements fall within the early warning time interval are screened out to obtain a space target set. This is because the accuracy of the orbit encounter is restricted by the prediction duration, and as the prediction period increases, its prediction accuracy will decrease. Therefore, some orbital elements with too long prediction periods can be removed first. For example, the early warning time interval is , the prediction time of the orbital elements of a certain space target is , if , then this space target can be removed from the to-be-screened target set. Among them is the screening threshold. In this embodiment, it can be set to .

[0055] After the epoch time screening, the perigee and apogee screening can be carried out. 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 is higher than by the safety distance , or, is higher than by the safety distance , it means that in the short-term prediction process, the target spacecraft and this space target will not collide, and this space target can be removed from the space target set. Among them, in this embodiment, the safety distance Set to .

[0056] After epoch time screening and near - far location screening, a large number of non - threatening targets can be initially screened out, and the remaining space targets form the first target set.

[0057] Subsequently, secondary precise screening can be carried out. The secondary precise screening process comprehensively considers perturbation factors. The main perturbation factors are the long - term term of the Earth's oblateness perturbation and the atmospheric drag perturbation. Using TwoBody (two - body model) distance screening, SGP4 (Simplified General Perturbations 4) distance screening, HPOP (High - Precision Orbit Propagator) distance screening, and time screening, dangerous targets can be quickly screened out, and then the time - window sequence of high - risk encounters can be obtained completely and accurately.

[0058] In one embodiment, step S500, that is, the step of respectively determining the orbital plane intersection line, intersection point position, and time passing through the intersection point 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 point position and time passing through the intersection point to obtain the second target set includes:

[0059] Step S510: Within the early - warning time interval, use the two - body model to determine the orbital plane intersection line and intersection point position of the target spacecraft and each space target in the first target set 、 and the time passing through the intersection point 、 ;

[0060] Step S520: Determine the minimum value of each group and the minimum value of each group ; ; ;

[0061] Step S530: Exclude the space targets with and the space targets with from the first target set to obtain the second target set, where , is the distance threshold, is the time threshold.

[0062] In this embodiment, the distance threshold can be set to , and can be set to .

[0063] In one embodiment, step S700, i.e., the step of setting the extrapolation interval and the step size, and predicting the positions of the target spacecraft and each space target in the second target set at each step size to screen each space target in the second target set to obtain the third target set, includes:

[0064] Step S710: Set the first extrapolation interval and the first step size, and use the simplified general perturbation model to predict the position of the target spacecraft at each of the first step sizes and the positions of each space target in the second target set ; wherein, prior to this, the instantaneous osculating orbital elements of the target spacecraft can be first converted into orbital elements suitable for the SGP4 model.

[0065] Step S720: Determine the minimum value of each group ;

[0066] Step S730: Exclude the space targets that meet the conditions from the second target set to obtain the first set;

[0067] Step S740: Set the second extrapolation interval and the second step size, and use the high-precision orbit prediction model to predict the position of the target spacecraft at each of the second step sizes , and use the simplified general perturbation model to predict the positions of each space target in the first set at each of the second step sizes ;

[0068] Step S750: Determine the minimum value of each group ;

[0069] Step S760: Exclude the space targets that meet the conditions from the first set to obtain the third target set;

[0070] wherein, and are both distance thresholds.

[0071] In the above steps, SGP4 distance screening is first performed, and then the more accurate HPOP model is used for further screening. During the further screening process, the HPOP model and the SGP4 model are combined. In conventional geometric screening, in order to reduce the risk of missed reports, the set value of the approach distance D is often increased, which will lead to an increase in misselected targets and a decrease in screening efficiency. In the embodiments of the present application, in the above steps of step S700, SGP4 combined with HPOP is used for distance screening, which can effectively reduce the risk of mis-screening or missing dangerous targets due to the too small setting of the minimum approach distance D.​​​​

[0072] Among them, for low-earth orbit space targets, SGP4 simplifies the complex perturbation terms during the operation of space targets, considering that the general perturbation terms include the long-term and periodic perturbation effects of the earth's oblateness, solar and lunar gravitation, as well as the gravitational resonance and orbital decay caused by atmospheric drag. Compared with the TwoBody prediction, the accuracy of the SGP4 prediction is higher, and the maximum position error of the 3-day prediction is about 3 km (taking the spaceborne GNSS precise orbit as the nominal orbit).

[0073] For spacecraft, HPOP is used for high-precision orbit prediction. HPOP comprehensively considers the perturbations of the orbit and uses a complete set of high-fidelity mechanical models, including the highest-precision earth gravity field model JGM-2, the combined gravity field model, the solar and lunar gravity field model, the atmospheric drag model, and the solar radiation pressure model, so as to provide more accurate orbit calculation. Compared with the SGP4 prediction, HPOP takes longer calculation time but has higher prediction accuracy, and the maximum position error of the 3-day prediction is several hundred meters (taking the spaceborne GNSS precise orbit as the nominal orbit).

[0074] In one embodiment, considering that the moment when the distance between the real target spacecraft and the space target is the smallest is near , the first extrapolation interval can be set to . In addition, the second extrapolation interval can be set to , where is corresponding to the predicted time, is the time threshold, .

[0075] In one embodiment , the first step size is greater than the second step size.

[0076] In a specific example, the first step size can be set to 1 s, and the second step size can be set to 0.1 s. can be set to , set to be , set to be . can be set to 30 s, and can be set to 5 s.

[0077] In one embodiment, in step S900, that is, the step of correcting the rendezvous time between each space target in the third target set and the target spacecraft, the Newton iteration method is used to correct the rendezvous time.

[0078] During the pre - screening process, in order to accelerate the calculation speed, the step - time set for the extrapolated orbit is 0.1 s. However, for low - orbit targets, the displacement can reach about 700 m within 0.1 s, and thus the predicted orbit state is not accurate enough. In order to calculate the orbit state at the moment closest to the target within the range more precisely, in this embodiment, the criterion that the relative position vector is perpendicular to the relative velocity vector at the closest moment is utilized, and the Newton iteration method is adopted to analyze the predicted values and correct the rendezvous time.

[0079] First, calculate the position error. Calculate the position error between the target spacecraft and the space target at the moment when they are closest. 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 the space target, since it is a non - cooperative target and lacks accurate observation data, it is difficult to accurately calculate the variance matrix of its position error. Therefore, in this embodiment, the historical data of orbital elements is used to fit the covariance evolution function, and this evolution function is used to calculate the position covariance matrix at the closest moment;

[0080] 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 rendezvous moment, set the velocity vector as a fixed value, and the position vector changes linearly with time;

[0081] Finally, correct the rendezvous time. Use the Newton iteration method to quickly converge to obtain the correction amount of the rendezvous time Δt R , and correct the corresponding predicted moment, which is the time - window sequence of high - risk rendezvous between the target spacecraft and the space target within the warning time interval .

[0082] In the case of conventional time screening when the distance from the actual rendezvous moment is relatively far, the interval corresponding to the actual rendezvous moment will be missed. In this embodiment, by correcting the initial value of the orbit state and time of the rendezvous, the interval corresponding to the rendezvous moment can still be obtained when the distance from the rendezvous moment is relatively far, and it has good stability.

[0083] Since the number of cataloged space targets is extremely large, if all high - precision models are used, it will lead to a huge amount of calculation for orbit extrapolation and rendezvous relationship calculation, consuming a large amount of time and not meeting the timeliness requirements of early warning. Therefore, in order to save calculation time, this method first uses various 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 completely and accurately obtain the high - risk rendezvous time - window sequence.

[0084] This solution not only ensures high-precision orbit extrapolation, better solves the problem of missing warning time intervals caused by perturbation factors, but also greatly improves the timeliness of early warning.

[0085] In one embodiment, before step S300, that is, the step of screening each space target in the to-be-screened target set to obtain the first target set, the screening method for space dangerous rendezvous targets further includes: splitting each space target in the to-be-screened target set into several subsets;

[0086] For each of the subsets, the subsequent screening steps are respectively executed, and the dangerous rendezvous target set is the set of third target sets obtained by respectively screening each of the subsets.

[0087] That is to say, the present application can adopt multi-threaded parallel computing, which has a fast calculation speed, clear physical meaning, can obtain the variation law of the dangerous time interval, and lays a foundation for subsequent collision risk assessment.

[0088] Specifically, parallel computing can be implemented based on the CUDA architecture, and the screening of space targets can be significantly accelerated through CPU-GPU collaborative computing.

[0089] In one embodiment, a computer device is provided, including a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, the above-mentioned screening method for space dangerous rendezvous targets is implemented.

[0090] Figure 3 FIG. is a schematic structural diagram 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 Figure 3 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 related to the screening method for 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 screening method for space dangerous rendezvous targets is implemented.

[0091] Those skilled in the art can understand, Figure 3The structure shown is only a block diagram of some structures related to the solution of this application, and does not constitute a limitation on the computer device to which the solution of this application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine some components, or have a different component arrangement.

[0092] 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 above-mentioned screening method for spatial dangerous rendezvous targets is implemented.

[0093] In one embodiment, a computer program product is provided, including a computer program which, when executed by a processor, implements the steps in the above-mentioned method embodiments.

[0094] Those of ordinary skill in the art can understand that all or part of the processes in the above-mentioned method embodiments can be completed by instructing relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it may include the processes of the above-mentioned method embodiments. Among them, any reference to a memory, storage, database, or other medium used in the various embodiments provided in this application may include at least one of non-volatile and volatile memories. Non-volatile memory may include read-only memory (ROM), magnetic tape, floppy disk, flash memory, or optical memory, etc. Volatile memory may include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM can be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM), etc.

[0095] The technical features of the above-mentioned embodiments can be combined arbitrarily. For the sake of brevity of description, not all possible combinations of the technical features in the above-mentioned embodiments are described. However, as long as there is no contradiction in the combination of these technical features, it should be considered as the scope recorded in this specification.

[0096] The above-mentioned embodiments only represent several implementation manners of this application. The description is relatively specific and detailed, but it should not be construed as a limitation on the scope of the patent. It should be noted that for those of ordinary skill in the art, without departing from the concept of this application, several modifications and improvements can still be made, and these all belong to the protection scope of this application. Therefore, the protection scope of this application should be subject to the appended claims.

Claims

1. A screening method for spatial dangerous rendezvous targets, characterized in that Including: Obtaining the orbital elements of a target spacecraft and the orbital elements of each space target in a set of targets to be screened; Screening each space target in the set of targets to be screened according to the prediction time corresponding to the orbital elements of the space target and the perigee and apogee altitudes of the space target, to obtain a first set of targets; The method comprises: determining the orbital plane intersection line, intersection point position and intersection time of the target spacecraft and each space target in the first target set respectively, and screening each space target in the first target set according to the intersection point position and the intersection time to obtain a second target set; comprising: determining the orbital plane intersection line, intersection point position and intersection point position of the target spacecraft and each space target in the first target set by using a two-body model within the warning time interval. , 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; Setting an extrapolation interval and a step, and predicting the positions of the target spacecraft and each space target in the second set of targets at each step, to screen each space target in the second set of targets, to obtain a third set of targets; Correcting the rendezvous times of each space target in the third set of targets with the target spacecraft, to obtain a set of dangerous rendezvous targets and a sequence of dangerous rendezvous time windows.

2. The screening method for the spatial dangerous rendezvous target according to claim 1, characterized in that, The step of screening each space target in the set of targets to be screened according to the prediction time corresponding to the orbital elements of the space target and the perigee and apogee altitudes of the space target, to obtain a first set of targets includes: Screening out the space targets in the set of targets to be screened whose prediction times corresponding to the orbital elements fall within the early warning time interval, to obtain a set of space targets; For each space target in the set of space targets: if the perigee altitude of the target spacecraft and the apogee altitude of the space target exceed the safe distance, or the perigee altitude of the space target and the apogee altitude of the target spacecraft exceed the safe distance, then removing the corresponding space target from the set of space targets, to obtain the first set of targets.

3. The screening method for space dangerous rendezvous targets according to claim 2, wherein The step of setting an extrapolation interval and a step, and predicting the positions of the target spacecraft and each space target in the second set of targets at each step, to screen each space target in the second set of targets, to obtain a third set of targets includes: Set a first extrapolation interval and a first step, and use a simplified regular perturbation model to predict the position of the target spacecraft under each of the first steps and the positions of the space targets in the second target set ; Determine each group of the minimum value ; Remove the space target from the second target set to obtain a first set; Set a second extrapolation interval and a second step size, and use a high-precision orbit prediction model to predict the positions of the target spacecraft at each of the second step sizes , and use a simplified conventional perturbation model to predict the positions of the space targets in the first set at each of the second step sizes ; Determine each group of the minimum value ; Exclude the space targets from the first set to obtain the third target set; wherein, and are both distance thresholds.

4. The screening method for spatial dangerous rendezvous targets according to claim 3, characterized in that, The first extrapolation interval is , the second extrapolation interval is , where is the corresponding forecast time, is the time threshold, .

5. The screening method for spatial dangerous rendezvous targets according to claim 3, characterized in that , the first step size is greater than the second step size.

6. The screening method for the spatial dangerous rendezvous target according to claim 1, characterized in that, In the step of correcting the rendezvous times of each space target in the third set of targets with the target spacecraft, the Newton iteration method is used for correcting the rendezvous times.

7. The screening method for spatial dangerous rendezvous targets according to claim 1, characterized in that, Before the step of screening each space target in the set of targets to be screened to obtain a first set of targets, the method for screening space dangerous rendezvous targets further includes: splitting each space target in the set of targets to be screened into several subsets; For each of the subsets, the subsequent screening steps are respectively executed, and the set of dangerous rendezvous targets is the set of the third sets of targets obtained by respectively screening each of the subsets.

8. A computer device, characterized in that, Including a memory and a processor, the memory stores a computer program, and when the processor executes the computer program, the method for screening space dangerous rendezvous targets according to any one of claims 1-7 is implemented.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, the method for screening space dangerous rendezvous targets according to any one of claims 1-7 is implemented.

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