Space debris collision detection digital twinning method and system

Abstract

The invention relates to the technical field of digital twinning, and particularly discloses a space debris collision detection digital twinning method and system, and the method comprises the steps: carrying out the grid processing of space debris through a space grid between the earth and the moon; performing space debris collision detection on the space debris by using a grid collision screening algorithm; and according to a space debris collision detection result, screening out space debris which may be collided, and sending out an early warning. According to the method, the space grid collision screening algorithm based on the space grid between the earth and the moon is adopted to carry out collision screening and secondary screening on the space debris, a large number of space debris which cannot be collided can be efficiently rejected, and therefore resources are concentrated to carry out more accurate analysis on high-risk collision.

Description

Technical Field

[0001] The present invention relates to the field of digital twin technology, and in particular to a digital twin method and system for space debris collision detection. Background Art

[0002] In recent years, the number of space debris has gradually increased, which has brought negative impacts that cannot be ignored on conventional space missions and space science research. At present, existing technologies can already manage these known space debris. The orbital error ellipsoid of space debris calculated by TLE orbital elements is used to calculate the major semi-axis of the error ellipsoid at the initial moment as the major semi-axis of the unified error ellipsoid, so as to manage space debris. Then, collision screening and detection are performed based on these space debris data. By setting different threshold ranges, two levels of minimum circle unit sets are established to screen out space debris that may collide.

[0003] Although there are currently methods for space debris collision detection, there may still be some shortcomings in data processing efficiency and warning accuracy. Although the processing efficiency has been improved through grid management and screening processes, there may still be efficiency bottlenecks when processing large amounts of space debris data; existing technologies also mainly rely on preset threshold ranges for collision screening, especially in complex orbital dynamic environments, and may not be able to accurately predict all collision events.

[0004] Therefore, how to improve the efficiency of space debris management and collision warning is a technical problem that needs to be urgently solved by technicians in this field. Summary of the invention

[0005] To achieve the purpose of the present invention, the present application provides a digital twin method for space debris collision detection, comprising:

[0006] Step S1: The space grid between the earth and the moon is used to grid the space debris;

[0007] Step S2: performing space debris collision detection on the space debris through a space grid collision screening algorithm; including: taking the spacecraft as the center, defining two area sets with different finenesses, corresponding to different detection thresholds respectively, using a coarser area set for preliminary screening to exclude those space debris without collision risk, and using a finer area set for secondary screening to determine a potential collision space debris set.

[0008] Step S3: Based on the set of space debris that may collide, screen out space debris that may collide and issue a warning.

[0009] In some specific embodiments, the step S1 further includes: establishing a ternary data set to achieve gridding processing of space debris;

[0010] The ternary data set includes: determining the orbital position of space debris through the spatiotemporal coding of specific area units at the sampling time within a specific time range, and also associating the characteristics of the space debris in these area units and related environmental information.

[0011] In some specific embodiments, step S2 includes:

[0012] Step S21: extracting the time code by performing a binary XOR operation on the time-space code to extract a circle unit set having the same time code as the time code to form a first code set;

[0013] Step S22: extracting a spatial code according to the spatiotemporal code of the circle body unit, removing the circle body units in the first code set that are different from the spatial code and are not in a reference spatial body, extracting a circle body unit set with the same spatial code as the spatial code to form a second code set, and performing a first shift on the spatial code to obtain a first shifted spatial code;

[0014] Step S23: in the second code set, according to the space grid between the earth and the moon, find the adjacent ring unit set of the first shifted space code, and use the space code and its adjacent ring unit code as screening conditions to perform a first round of screening procedures, for the second set of code sets, to determine the code set of the first set of space debris;

[0015] Step S24: Based on the coding set of the first group of spatial fragments as a screening criterion, the corresponding circle units are retrieved to construct a third coding set, and a second shift operation is performed on these spatial codes to obtain a second set of shifted spatial codes.

[0016] Step S25: In the third code set, the adjacent circle unit set of the second shift space code is searched according to the space grid between the earth and the moon, and the second shift space code and its adjacent circle unit code are used as screening conditions to perform a second round of screening procedure for the second group of code sets to identify potential collision risk space debris groups.

[0017] In some specific embodiments, the spatial encoding is binary Hilbert encoding.

[0018] In some specific embodiments, step S3 further includes:

[0019] After the warning is issued, high-precision observations will be made on the space debris that may collide. If the probability of collision is too high, evasive maneuvers will be carried out on the aircraft.

[0020] To achieve the same invention purpose, the present application also provides a space debris collision detection digital twin system, including:

[0021] Grid processing module: used for grid processing of space debris in the space grid between the earth and the moon;

[0022] Collision detection module: used for performing space debris collision detection on the space debris through a space grid collision screening algorithm; including: taking the spacecraft as the center, defining two area sets with different fineness, corresponding to different detection thresholds respectively, using a coarser area set for preliminary screening to exclude those space debris without collision risk, and using a finer area set for secondary screening to determine the potential collision space debris set.

[0023] Early warning module: used for screening out space debris that may collide and issuing an early warning based on the set of space debris that may collide.

[0024] In some specific embodiments, the grid processing module is further used to: establish a ternary data set to achieve grid processing of space debris;

[0025] The ternary data set includes: determining the orbital position of space debris through the spatiotemporal coding of specific area units at the sampling time within a specific time range, and also associating the characteristics of the space debris in these area units and related environmental information.

[0026] In some specific embodiments, the collision detection module is used to perform the following steps:

[0027] Extracting the time code by performing binary XOR operation on the space-time code to extract the circle unit set with the same time code to form a first code set;

[0028] Extracting a spatial code according to the spatiotemporal code of the circle body unit, removing the circle body units in the first code set that are different from the spatial code and are not in a reference spatial body, extracting a circle body unit set with the same spatial code as the spatial code to form a second code set, and performing a first shift on the spatial code to obtain a first shifted spatial code;

[0029] In the second code set, the adjacent circle unit set of the first shifted spatial code is found according to the spatial grid between the earth and the moon, and the first round of screening procedure is performed with the spatial code and its adjacent circle unit code as screening conditions, for the second group of code sets to determine the code set of the first group of space debris.

[0030] Based on the coding set of the first set of spatial fragments as the screening criteria, the corresponding ring units are retrieved to construct the third set of coding sets. Subsequently, a second shift operation is performed on these spatial codes to obtain the second set of shifted spatial codes.

[0031] In the third code set, the adjacent circle unit set of the second shift space code is found according to the space grid between the earth and the moon, and the second shift space code and its adjacent circle unit code are used as screening conditions to perform a second round of screening procedure for the second group of code sets to identify potential collision risk space debris groups.

[0032] In some specific embodiments, the spatial encoding is binary Hilbert encoding.

[0033] In some specific embodiments, the early warning module is also used to perform high-precision observation of the space debris that may collide after issuing the early warning, and if the probability of collision is too high, the aircraft will be evasive.

[0034] Beneficial effects of the above technical solution:

[0035] The present invention converts geographic coordinates into a coded form through an innovative method, and uses coded binary bit operations to bypass some complex steps in traditional screening technology. These steps include screening orbital heights, calculating the intersection of orbital planes, and evaluating orbital phases, etc. These processes usually consume a large amount of central processing unit (CPU) resources and time to execute iterative solution algorithms. In this way, the tedious process of screening each orbital height one by one can be avoided, and the complex calculation of calculating the intersection of orbital planes can be omitted, and there is no need to perform detailed comparative analysis of orbital phases. Thereby reducing the consumption of computing resources and improving processing efficiency. This means that potential collision risks can be identified more quickly, leaving more time for taking avoidance measures. When performing space debris collision screening, traditional methods usually require a complex screening process of five stages to achieve a debris exclusion rate of 99%. This efficiency improvement not only saves computing resources, but also completes collision risk assessment in a shorter time. The space grid between the earth and the moon is used to implement refined grid management of space debris. At the same time, according to the proximity relationship between the earth and the moon, the space debris collision warning and screening process can be efficiently performed. This allows the space debris that may collide to be quickly screened out and an early warning to be issued when a potential collision risk is detected, providing a time window for taking further avoidance measures. After completing the early warning procedure, a high-precision observation strategy needs to be further implemented to optimize the measurement accuracy of orbital parameters and covariance matrices, thereby deriving more accurate orbital values. This helps to more accurately assess the risk of collision and provide more reliable data support for avoidance maneuvers. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0037] Figure 1 A schematic diagram of a flow chart of a digital twin method for space debris collision detection provided by an embodiment of the present invention;

[0038] Figure 2 A schematic diagram of the structure of a digital twin system for space debris collision detection provided by one embodiment of the present invention;

[0039] Figure 3 A display effect diagram of space debris after gridding of a digital twin method for space debris collision detection provided by an embodiment of the present invention;

[0040] Figure 4 A rendering of a satellite constellation for space grid management between the Earth and the Moon, providing a digital twin method for space debris collision detection according to an embodiment of the present invention. DETAILED DESCRIPTION

[0041] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments.

[0042] Examples of the embodiments are shown in the accompanying drawings, wherein the same or similar symbols throughout represent the same or similar elements or elements with the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0043] Embodiment 1

[0044] One embodiment of the present invention provides a space debris collision detection digital twin method, referring to Figure 1 As shown, including:

[0045] Step S1: The space grid between the Earth and the Moon is used to grid the space debris.

[0046] In a specific embodiment of the present invention, step S1 also includes: establishing a ternary data set, which includes: a set of spatiotemporal codes of the ring unit where the orbit of the space debris is located at the sampling moment, and detailed attribute information and environmental data of the space debris inside the associated ring unit within a specific time period, thereby realizing grid management and processing of space debris.

[0047] Specifically, the safe operation of on-orbit spacecraft faces a high proportion of threats from space debris.

[0048] In order to reduce the error ellipsoid major axis, the error ellipsoid major axis calculated at T0 is selected and used as the error ellipsoid major axis in the time interval [T0, T0+ΔT]. i a(T i )Through this method, the spatiotemporal coding of each spatial fragment in a specific interval can be determined.

[0049] The orbit of the fragment in the time interval [T0, T0+ΔT] corresponds to the code set SolidCellCode i ' N At the same time, the properties and other relevant data of space debris are recorded as {A m}. Through this method, it is possible to construct a triple dataset within a specified time interval.

[0050] The TLE data of 11,080 pieces of space debris from 12:00 to 15:00 on December 2, 2014 were gridded, and finally the ternary data records of all space debris were obtained. Figure 3 A display of space debris. Figure 4 Image of how different satellite constellations are managed to create a spatial grid between the Earth and the Moon: (a) BeiDou satellites and (b) part of a navigation satellite.

[0051] During detection, the thresholds commonly used are set at ±5 km in radial direction, ±25 km in track direction, and ±5 km in lateral direction. Once the possibility of intersection is detected, these thresholds will be adjusted more strictly accordingly, that is, reduced to ±2 km in radial direction, ±5 km in track direction, and ±2 km in lateral direction, to ensure more accurate identification of potential collision risks.

[0052] First, define the average number of collisions between two space objects i and j in a given time interval dt and in a volume element dU, denoted as c. This number can be obtained by the formula c = S i S j V imp AcdUdt is calculated, where S i and S jRespectively represent the distribution density of objects i and j in the volume element dU. imp represents the relative collision speed between the two, and Ac is their collision cross section. According to statistical principles, if the number of collisions follows a Poisson distribution within a specified time and space, then the probability of zero collisions between two objects can be expressed as exp(-c). Therefore, the probability P of objects i and j colliding at least once is ij It can be obtained by complement, that is, Pij=1-exp(-c).

[0053] In practical applications, we usually focus on those space objects whose Euclidean distance is within dc. In this case, the volume element dU is no longer the volume of a cube, but the volume of a sphere with a radius of dc. Based on this, we can adjust the above formula to adapt to the actual situation, thereby calculating the collision probability P between space objects i and j ij .

[0054] Step S2: Perform space debris collision detection on the space debris by using a space grid collision screening algorithm; including: taking the spacecraft as the center, establishing two ring unit sets with different granularities according to different threshold ranges; using a coarser ring unit set for preliminary screening, the purpose is to exclude those space debris without collision risk. Then use a finer ring unit set for a second round of screening, the purpose is to determine those space debris that may collide, and classify them into the potential collision set.

[0055] In a specific embodiment of the present invention, step S2 includes:

[0056] Step S21: extracting a time code according to the space-time code of a loop unit of the spacecraft, and extracting a set of loop units with the same time code through binary XOR operation to form a first code set;

[0057] Step S22: extracting a spatial code according to the spatiotemporal code of the circle body unit, removing the circle body units in the first code set that are different from the spatial code and are not in a reference spatial body, extracting a circle body unit set with the same spatial code as the spatial code to form a second code set, and performing a first shift on the spatial code to obtain a first shifted spatial code;

[0058] Step S23: In the second code set, the adjacent ring unit set of the first shifted spatial code is searched according to the spatial grid between the earth and the moon, and the spatial code and its adjacent ring unit code are used as screening conditions to perform a first round of screening procedures for the second set of code sets to determine the code set of the first set of space debris.

[0059] Step S24: Based on the coding set of the first set of spatial fragments as a screening criterion, the corresponding circle units are retrieved to construct a third set of coding sets. Subsequently, a second shift operation is performed on these spatial codes to obtain a second set of shifted spatial codes.

[0060] Step S25: In the third code set, the adjacent circle unit set of the second shift space code is searched according to the space grid between the earth and the moon, and the second shift space code and its adjacent circle unit code are used as screening conditions to perform a second round of screening procedure for the second group of code sets to identify potential collision risk space debris groups.

[0061] For a spacecraft A running in orbit, all the loop units that the spacecraft A passes through in the time interval [T0, T0+ΔT] form a three-dimensional data set, which is expressed as All space debris also constitute an independent triple data set, expressed as In this way, the collision analysis of spacecraft A can be achieved by evaluating the distance between two ring elements and their adjacency. This method transforms the assessment of collision risk into an analysis of the geometric relationship between elements in the data set.

[0062] When assessing the collision risk between space debris and spacecraft, a coarser-grained set of ring grids is used for initial screening to exclude those debris that are clearly not likely to collide, followed by a further refined screening by applying a finer-grained set of ring cells to identify possible collisions.

[0063] The specific settings are ±5km in radial direction, ±25km in track direction, and ±5km in lateral direction. The subdivision level N1 is defined as the smallest outer envelope unit. Based on this level, the space debris dataset is constructed, which is expressed as The second set of thresholds has a narrower range, which is ±2 km radially, ±5 km in the direction of the track, and ±2 km in the lateral direction. The corresponding minimum unit segmentation level is N2, forming a unit set and generating a corresponding ternary data set, which is expressed as

[0064] The following is a description of the process.

[0065] Step 1: After selecting a stereo unit of spacecraft A, obtain the spatiotemporal code of the unit, recorded as (where the time code is the same as the sampling time T i corresponding),

[0066] Then, by comparing the time codes, the time code T Code-iB Matching stereo units, and determine the subdivision level N of these units, and finally form the corresponding coding set CN .

[0067] Step 2: Extract of Next, the circle units without celestial body identification and different reference space bodies are excluded to form the coding set C N' Considering the characteristics of Hilbert coding, we will encode Perform a right shift operation of N-N1 to obtain the Hilbert code after the shift processing

[0068] Step 3: Use the model to calculate and find the adjacent ring cells of the space grid between the Earth and the Moon The corresponding codes of these adjacent circle units are recorded. As a filter condition, from the set C N' Extract the circle units whose first N1 bits of the code match the screening conditions to form a new code set Through this process, we are able to roughly screen out the set of space debris that may be prone to collision.

[0069] Step 4: Filter again, the filtering condition is set The retrieved unit is denoted as Since N>N2, the second Perform a right shift N-N2 operation, followed by a binary operation, to obtain the shifted Hilbert code

[0070] Step 5: Search by neighboring circle units. Search Then filter, the filtering conditions are from Extract the first N2 bits and The same code, forming Finally, we get a collection of colliding space debris.

[0071] Step S3: Screen out space debris that may collide based on the result of the space debris collision detection and issue a warning.

[0072] In a specific embodiment of the present invention, step S3 includes:

[0073] After the warning is issued, high-precision observations will be made on the space debris that may collide. If the probability of collision is too high, evasive maneuvers will be carried out on the aircraft.

[0074] In a specific embodiment of the present invention, the space grid between the earth and the moon is used to implement refined grid management of space debris. At the same time, based on the proximity relationship between the earth and the moon, the space debris collision warning and screening process can be efficiently performed. Its advantages are:

[0075] This is achieved through the conversion of geographic coordinates to codes and binary coding operations. This method avoids the iterative root-finding algorithms in traditional methods that require a lot of CPU time, such as orbital height screening, orbital plane intersection calculation, orbital phase analysis, and minimum approach distance evaluation. In addition, this method also significantly reduces the number of judgments required in the collision detection process. In the traditional collision screening process, in order to achieve a 99% debris exclusion rate, it is usually necessary to go through a complex screening process consisting of five stages. The new method improves the efficiency of the screening process by reducing these unnecessary calculation steps.

[0076] The rejection rate of space debris is high. The orbital data of 8,000 pieces of space debris are managed through the space grid between the earth and the moon.

[0077] The spatial grid collision screening algorithm was used for France's SPOT-7 at 12:00 on December 2, 2014. The following table shows the experimental results.

[0078] Table 1 Space debris collision screening performance of the space grid between the Earth and the Moon

[0079] Collision screening Rejection % Pass number % Rough screening 94.9 4.6 Fine screening 99.1 0.7

[0080] After screening the results of space debris collisions through the space grid between the Earth and the Moon, the system will immediately activate the early warning mechanism and issue a warning after identifying a potential collision risk. Once the early warning procedure is completed, more accurate observations are enabled to further confirm and evaluate the possibility of collision. The measurement accuracy of orbital parameters and covariance matrices is optimized, and the system will conduct in-depth calculations to obtain more accurate values. The possibility of collision is further analyzed. When the evaluation results reveal that the collision risk value exceeds the predetermined safety limit, the system will recommend evasive actions for the aircraft to ensure its safety.

[0081] Traditional methods usually require a five-stage complex screening process to achieve a 99% debris exclusion rate when screening for space debris collisions. This efficiency improvement not only saves computing resources, but also completes collision risk assessment in a shorter time. The orbital data of space debris is managed through the space grid between the Earth and the Moon, and the grid collision screening algorithm is used for screening. The experimental results show that through coarse and fine screening, a large number of space debris that are unlikely to collide can be efficiently rejected, so that resources can be concentrated for more accurate analysis of high-risk collisions. The space grid between the Earth and the Moon is used to implement refined grid management of space debris. At the same time, based on the proximity relationship between the Earth and the Moon, the space debris collision warning and screening process can be efficiently performed. This allows the space debris that may collide to be quickly screened out and a warning to be issued when a potential collision risk is detected, providing a time window for taking further avoidance measures. After completing the warning procedure, a high-precision observation strategy needs to be further implemented to optimize the measurement accuracy of orbital parameters and covariance matrices, so as to derive more accurate orbital values. This helps to more accurately assess the risk of collision and provide more reliable data support for avoidance maneuvers.

[0082] Embodiment 2

[0083] An embodiment of the present invention provides a space debris collision detection digital twin system, referring to Figure 2 As shown, including:

[0084] Grid processing module 10: used for grid processing of space debris using the space grid between the earth and the moon;

[0085] The collision detection module 20 is used to perform space debris collision detection on the space debris by using a space grid collision screening algorithm; it includes: taking the spacecraft as the center, defining two area sets with different fineness, corresponding to different detection thresholds respectively. A coarser area set is used for preliminary screening to exclude those space debris without collision risk. Subsequently, a more refined area set is used for secondary screening to determine the potential collision space debris set.

[0086] The early warning module 30 is used to screen out the space debris that may collide based on the set of space debris that may collide and issue an early warning.

[0087] In a specific embodiment of the present invention, the grid processing module 10 is also used to: establish a ternary data set, which includes: a set of space-time codes of the ring unit where the orbit of the space debris is located at the sampling moment, and detailed attribute information and environmental data of the space debris inside the associated ring unit within a specific time period, thereby realizing grid management and processing of space debris.

[0088] In a specific embodiment of the present invention, the collision detection module 20 is used to perform the following steps:

[0089] Extracting a time code according to a space-time code of a loop unit of the spacecraft, extracting a set of loop units having the same time code through a binary XOR operation to form a first code set;

[0090] Extracting a spatial code according to the spatiotemporal code of the circle body unit, removing the circle body units in the first code set that are different from the spatial code and are not in a reference spatial body, extracting a circle body unit set with the same spatial code as the spatial code to form a second code set, and performing a first shift on the spatial code to obtain a first shifted spatial code;

[0091] In the second code set, the adjacent circle unit set of the first shifted spatial code is found according to the spatial grid between the earth and the moon, and the first round of screening procedure is performed with the spatial code and its adjacent circle unit code as screening conditions, for the second group of code sets to determine the code set of the first group of space debris.

[0092] Based on the coding set of the first set of spatial fragments as the screening criteria, the corresponding ring units are retrieved to construct the third set of coding sets. Subsequently, a second shift operation is performed on these spatial codes to obtain the second set of shifted spatial codes.

[0093] In the third code set, the adjacent circle unit set of the second shift space code is found according to the space grid between the earth and the moon, and the second shift space code and its adjacent circle unit code are used as screening conditions to perform a second round of screening procedure for the second group of code sets to identify potential collision risk space debris groups.

[0094] In a specific embodiment of the present invention, the spatial coding is binary Hilbert coding.

[0095] In a specific embodiment of the present invention, the early warning module is also used to perform high-precision observation of the space debris that may collide after issuing the early warning, and if the probability of collision is too high, the aircraft will be evasive.

[0096] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

[0097] Each embodiment in this specification is described in a progressive manner, and each embodiment focuses on the differences from other embodiments, and the same and similar parts between the embodiments can be referred to each other. The embodiments of the present invention are described by flowcharts and / or block diagrams, which can be understood as computer program instructions. These diagrams depict the implementation process of the method of the present invention, terminal equipment (system), and computer program products. It should be recognized that each step and / or module in the flowchart and / or block diagram, as well as the combination thereof, can be implemented by computer program instructions. These instructions can be configured on a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to form a machine capable of performing specific functions.

[0098] In addition, these computer program instructions can be stored in computer-readable storage media, and when these media are loaded onto a computer or other programmable data processing device, they can guide the device to operate in a predetermined manner, thereby realizing the functions described in the flowchart or block diagram. The storage and execution of these instructions provide a basis for manufacturing devices that can realize specific functions, and these devices can execute one or more steps in the flowchart or block diagram. Although the preferred embodiments of the embodiments of the present invention have been described, once the technical personnel in this field know the basic creative concept, they can make additional changes and modifications to these embodiments. Therefore, the attached claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the embodiments of the present invention. Finally, the relational words such as "first" and "second" used are only used to distinguish different entities or operations, and do not necessarily indicate that there is an actual connection or order between them. In addition, "including", "comprising" and their synonyms refer to non-restrictive inclusion, meaning that the series of elements, steps, articles or devices involved not only include the elements explicitly listed, but may also include other elements that are not explicitly mentioned, or include those inherent elements. In the absence of other restrictions, the expression "including one..." The elements defined by the expression do not exclude the possibility of the existence of other identical elements.

[0099] The method and device provided by the present invention are introduced in detail above. Specific examples are used in this article to illustrate the principle and implementation mode of the present invention. The description of the above embodiments is only used to help understand the method of the present invention and its core idea. At the same time, for those skilled in the art, according to the idea of ​​the present invention, there will be changes in the specific implementation mode and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

[0100] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", "one specific embodiment" or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner.

[0101] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit it. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A digital twin method for space debris collision detection, characterized in that: include: Step S1: The space grid between the earth and the moon is used to grid the space debris; Step S2: performing space debris collision detection on the space debris through a space grid collision screening algorithm, including: taking the spacecraft as the center, defining two area sets with different finenesses, corresponding to different detection thresholds respectively, using a coarser area set for preliminary screening to exclude those space debris without collision risk, and using a finer area set for secondary screening to determine a potential collision space debris set. Step S3: Based on the set of space debris that may collide, screen out space debris that may collide and issue a warning.

2. The digital twin method for space debris collision detection according to claim 1, characterized in that: The step S1 further includes: establishing a ternary data set to achieve gridding processing of space debris; The ternary data set includes: determining the orbital position of space debris through the spatiotemporal coding of specific area units at the sampling time within a specific time range, and also associating the characteristics of the space debris and related environmental information within these area units.

3. The digital twin method for space debris collision detection according to claim 1, characterized in that: The step S2 comprises: Step S21: extracting the time code by performing a binary XOR operation on the space-time code to extract a circle unit set having the same time code as the time code to form a first code set; Step S22: extracting a spatial code according to the spatiotemporal code of the circle body unit, removing the circle body units in the first code set that are different from the spatial code and are not in a reference spatial body, extracting a circle body unit set with the same spatial code as the spatial code to form a second code set, and performing a first shift on the spatial code to obtain a first shifted spatial code; Step S23: in the second code set, according to the space grid between the earth and the moon, find the adjacent ring unit set of the first shifted space code, and use the space code and its adjacent ring unit code as screening conditions to perform a first round of screening procedures, for the second set of code sets, to determine the code set of the first set of space debris; Step S24: Based on the coding set of the first group of spatial fragments as a screening criterion, the corresponding circle units are retrieved to construct a third set of coding sets, and a second shift operation is performed on these spatial codes to obtain a second set of shifted spatial codes; Step S25: In the third code set, the adjacent circle unit set of the second shift space code is searched according to the space grid between the earth and the moon, and the second shift space code and its adjacent circle unit code are used as screening conditions to perform a second round of screening procedure for the second group of code sets to identify potential collision risk space debris groups.

4. The digital twin method for space debris collision detection according to claim 3, characterized in that: The spatial coding is binary Hilbert coding.

5. The digital twin method for space debris collision detection according to claim 1, characterized in that: The step S3 further comprises: After the warning is issued, the space debris that may collide is observed with high precision, and the risk level is assessed based on the collision probability of the space debris. If the calculated risk value exceeds the preset safety limit, the spacecraft's avoidance procedure is initiated and maneuvers are performed to ensure safety.

6. A digital twin system for space debris collision detection, characterized in that: include: Grid processing module: used for grid processing of space debris in the space grid between the earth and the moon; Collision detection module: used for performing space debris collision detection on the space debris through a space grid collision screening algorithm; including: taking the spacecraft as the center, defining two area sets with different finenesses, corresponding to different detection thresholds respectively, using a coarser area set for preliminary screening to exclude those space debris without collision risk, and using a finer area set for secondary screening to determine a potential collision space debris set; Early warning module: used for screening out space debris that may collide and issuing an early warning based on the set of space debris that may collide.

7. The space debris collision detection digital twin system according to claim 6, characterized in that: The grid processing module is also used to establish a ternary data set to achieve grid processing of space debris; wherein the ternary data set includes: within a specific time range, determining the orbital position of the space debris through the spatiotemporal coding of the specific area unit where the sampling moment is located, and at the same time associating the characteristics of the space debris in these area units and related environmental information.

8. The space debris collision detection digital twin system according to claim 6, characterized in that: The collision detection module is used to perform the following operations: Extracting the time code by performing binary XOR operation on the space-time code to extract the circle unit set with the same time code to form a first code set; Extracting a spatial code according to the spatiotemporal code of the circle body unit, removing the circle body units in the first code set that are different from the spatial code and are not in a reference spatial body, extracting a circle body unit set with the same spatial code as the spatial code to form a second code set, and performing a first shift on the spatial code to obtain a first shifted spatial code; In the second code set, according to the space grid between the earth and the moon, the adjacent ring unit set of the first shifted space code is searched, and the space code and its adjacent ring unit code are used as screening conditions to perform a first round of screening procedures, for the second set of code sets, to determine the code set of the first set of space debris; Based on the coding set of the first set of spatial fragments as the screening criteria, the corresponding circle units are retrieved to construct the third set of coding sets, and a second shift operation is performed on these spatial codes to obtain the second set of shifted spatial codes; In the third code set, the adjacent circle unit set of the second shift space code is found according to the space grid between the earth and the moon, and the second shift space code and its adjacent circle unit code are used as screening conditions to perform a second round of screening procedure for the second group of code sets to identify potential collision risk space debris groups.

9. The space debris collision detection digital twin system according to claim 8, characterized in that: The spatial coding is binary Hilbert coding.

10. The space debris collision detection digital twin system according to claim 6, characterized in that: The warning module is also used to perform high-precision observation of the space debris that may collide after issuing a warning, and evaluate its risk level based on the collision probability of the space debris. If the calculated risk value exceeds the preset safety limit, the spacecraft's avoidance program is initiated and maneuvering operations are performed to ensure safety.

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