Space debris collision detection digital twin method and system

Abstract

The application relates to the technical field of digital twinning, and particularly discloses a space debris collision detection digital twinning method and system, wherein the method comprises the following steps: carrying out grid processing on space debris by a space grid between the earth and the moon; carrying out space debris collision detection on the space debris by using a grid collision screening algorithm; and screening out space debris that is likely to collide according to the result of the space debris collision detection and issuing a warning. The space debris collision screening secondary screening is carried out by using the space grid collision screening algorithm based on the space grid between the earth and the moon, a large number of space debris that is impossible to collide can be efficiently rejected, and resources can be concentrated to more accurately analyze high-risk collisions.

Description

Technical Field

[0001] This invention relates to the field of digital twin technology, specifically to a digital twin method and system for detecting space debris collisions. Background Technology

[0002] In recent years, the number of space debris has been gradually increasing, bringing significant negative impacts to conventional space missions and space science research. Current technologies can manage this known space debris. By calculating the orbital error ellipsoid of space debris using TLE orbital elements, and using the semi-major axis of the error ellipsoid at the initial moment as the unified semi-major axis, space debris management can be achieved. Then, based on this space debris data, collision screening and detection can be performed. By setting different threshold ranges, two levels of minimum sphere unit sets are established to filter out space debris that may potentially collide.

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

[0004] Therefore, how to improve the efficiency of space debris management and collision warning is a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

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

[0006] Step S1: The space grid between Earth and the Moon is used to mesh space debris;

[0007] Step S2: Perform space debris collision detection on the space debris using a space grid collision screening algorithm; including: taking the spacecraft as the center, defining two sets of regions with different levels of fineness, each corresponding to a different detection threshold, using the coarser set of regions for preliminary screening to exclude space debris that does not pose a collision risk, and using the finer set of regions for secondary screening to determine the set of potential collision space debris.

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

[0009] In some specific embodiments, step S1 further includes: establishing a ternary dataset to achieve gridded processing of spatial fragments;

[0010] The ternary dataset includes: within a specific time range, determining the orbital position of space debris by using the spatiotemporal coding of a specific regional unit where the sampling time is located, while also associating the characteristics of the space debris and related environmental information within these regional units.

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

[0012] Step S21: Extract the set of concentric units that are the same as the time code by performing a binary XOR operation on the time code extracted from the spatiotemporal code to form the first code set;

[0013] Step S22: Extract spatial codes based on the spatiotemporal codes of the ring units, remove ring units in the first coding set that are different from the spatial codes and not in the same reference space, extract the ring unit set that is the same as the spatial codes to form a second coding set, and perform a first shift on the spatial codes to obtain the first shifted spatial codes;

[0014] Step S23: In the second coding set, search for the set of neighboring sphere units of the first displacement space code according to the space grid between the Earth and the Moon, and perform the first round of screening procedure with the space code and its neighboring sphere unit codes as the screening conditions to determine the coding set of the first group of space debris for the second coding set.

[0015] Step S24: Based on the coding set of the first set of spatial fragments as the filtering criteria, retrieve the corresponding sphere units to construct the third set of coding sets, and perform a second displacement operation on these spatial codes to obtain the spatial codes after the second displacement.

[0016] Step S25: In the third coding set, search for the set of neighboring sphere units of the second displacement space code according to the space grid between the Earth and the Moon, and perform a second round of screening procedure using the second displacement space code and its neighboring sphere unit codes as screening conditions to identify potential collision risk space debris groups for the second coding set.

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

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

[0019] After issuing the warning, the space debris that may collide with the spacecraft will be observed with high precision. If the probability of a collision is too high, the spacecraft will take evasive action.

[0020] To achieve the same inventive objective, this application also provides a digital twin system for space debris collision detection, comprising:

[0021] Mesh processing module: Used for meshing space debris between Earth and the Moon;

[0022] Collision detection module: used to perform space debris collision detection on the space debris using a space grid collision screening algorithm; including: taking the spacecraft as the center, defining two sets of regions with different levels of fineness, each corresponding to different detection thresholds, using the coarser set of regions for preliminary screening to exclude space debris that does not pose a collision risk, and using the finer set of regions for secondary screening to determine the set of potential collision space debris.

[0023] Early warning module: used to filter out space debris that may collide with the set of space debris that may collide and issue an early warning.

[0024] In some specific embodiments, the gridding processing module is further used to: establish a ternary dataset to achieve gridding processing of spatial fragments;

[0025] The ternary dataset includes: within a specific time range, determining the orbital position of space debris by using the spatiotemporal coding of a specific regional unit where the sampling time is located, while also associating the characteristics of the space debris and related environmental information within these regional units.

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

[0027] The first encoding set is formed by extracting the set of concentric units that are identical to the time encoding through binary XOR operation of the time encoding extracted from the spatiotemporal encoding;

[0028] Based on the spatiotemporal coding of the sphere unit, the spatial coding is extracted. The sphere units in the first coding set that are different from the spatial coding and are not in the same reference space are removed. The sphere unit set that is the same as the spatial coding is extracted to form the second coding set. The spatial coding is then shifted for the first time to obtain the first shifted spatial coding.

[0029] In the second set of codes, the set of neighboring sphere units of the first shifted space code is searched according to the space grid between the Earth and the Moon. The first round of screening is performed using the space code and its neighboring sphere unit codes as screening conditions. For the second set of codes, the set of codes for the first set of space debris is determined.

[0030] Using the first set of spatial fragment codes as a filtering criterion, corresponding sphere units are retrieved to construct the third set of codes. Subsequently, a second displacement operation is performed on these spatial codes to obtain the second set of displacement spatial codes.

[0031] In the third coding set, the set of neighboring sphere units of the second displacement space code is searched according to the space grid between the Earth and the Moon. Using the second displacement space code and its neighboring sphere unit codes as filtering conditions, a second round of filtering is performed to identify potential collision risk space debris groups for the second coding set.

[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 an early warning, and to perform avoidance operations on the aircraft if the probability of collision is too high.

[0034] The beneficial effects of the above technical solution are as follows:

[0035] This invention utilizes an innovative method to convert geographic coordinates into an encoded form and employs binary bit manipulation to bypass some complex steps in traditional screening techniques. These steps include screening for orbital altitudes, calculating orbital plane intersections, and assessing orbital phases, processes that typically consume significant central processing unit (CPU) resources and time to execute iterative solutions. This approach avoids the tedious process of screening each orbital altitude individually, eliminates the complex calculation of orbital plane intersections, and eliminates the need for detailed comparative analysis of orbital phases. This reduces computational resource consumption and improves processing efficiency. This means potential collision risks can be identified more quickly, allowing more time for avoidance measures. Traditional methods for space debris collision screening typically require a complex five-stage screening process to achieve a 99% debris rejection rate. This increased efficiency not only saves computational resources but also allows for collision risk assessment in a shorter time. A spatial grid between Earth and the Moon enables refined grid-based management of space debris. Furthermore, based on the proximity between Earth and the Moon, the space debris collision early warning and screening process can be executed efficiently. This allows for the rapid screening of potential collision debris and the issuance of early warnings upon detection of a potential collision risk, providing a window of opportunity for further avoidance measures. Following the early warning process, a high-precision observation strategy is needed to optimize the accuracy of orbital parameter and covariance matrix measurements, thereby deriving more accurate orbital values. This contributes to a more accurate assessment of collision risk and provides more reliable data support for evasive maneuvers. Attached Figure Description

[0036] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0037] Figure 1 A flowchart illustrating a digital twin method for space debris collision detection, provided as 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 is provided as an embodiment of the present invention;

[0039] Figure 3 This is a display effect diagram of the space debris meshing after a digital twin method for space debris collision detection is provided as an embodiment of the present invention;

[0040] Figure 4 An artist's rendering of a space grid management satellite constellation between Earth and the Moon, provided as an embodiment of the present invention, for a space debris collision detection digital twin method. Detailed Implementation

[0041] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments.

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

[0043] Example 1

[0044] One embodiment of the present invention provides a digital twin method for space debris collision detection, as described in this application. Figure 1 As shown, it includes:

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

[0046] In a specific embodiment of the present invention, step S1 further includes: establishing a ternary dataset, which includes: within a specific time period, a spatiotemporal encoding set of the sphere unit where the space debris orbit is located at the sampling instant, as well as detailed attribute information and environmental data of the space debris inside the associated sphere unit, thereby realizing grid-based management and processing of space debris.

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

[0048] To reduce the semi-major axis of the error ellipsoid, the semi-major axis of the error ellipsoid calculated at T0 is selected and used as the semi-major axis of the error ellipsoid in the time interval [T0, T0+ΔT]. Alternatively, sampling T can also be used. i a(T) i In this way, the spatiotemporal code of each spatial fragment in a specific interval can be determined.

[0049] The trajectories of the fragments within the time interval [T0, T0+ΔT] correspond to the code set SolidCellCode. i ′ N Meanwhile, the attributes and other relevant data of the space debris are recorded as {A} m This method allows us to construct ternary datasets within a specified time interval.

[0050] The TLE data of 11,080 space debris items from 12:00 to 15:00 on December 2, 2014, were gridded to obtain the three-dimensional data records of all space debris items. Figure 3 To display fragments of space. Figure 4 A rendering of the space grid between Earth and the Moon, showing the management of different satellite constellations: (a) shows BeiDou satellites and (b) shows some navigation satellites.

[0051] When conducting detection, the thresholds are typically set at ±5 km radially, ±25 km directionally, and ±5 km laterally. Once a possibility of collision is detected, these thresholds are adjusted to be more stringent, namely, the radial threshold is reduced to ±2 km, the directional threshold to ±5 km, and the lateral threshold to ±2 km, to ensure more accurate identification of potential collision risks.

[0052] First, let c be the average number of collisions between two spatial objects i and j within a given time interval dt and within a volume element dU. This number can be expressed by the formula c = S i S j V imp The calculation is performed using AcdUdt, where S i and S jV represents the distribution density of objects i and j within the volume element dU, respectively. imp Let represent the relative collision velocity between the two objects, and Ac be their collision cross-section. According to statistical principles, if the number of collisions follows a Poisson distribution within a given time and space, then the probability of two objects colliding zero times can be expressed as exp(-c). Therefore, the probability P that objects i and j collide at least once is... ij It can be obtained through the complement, i.e., Pij = 1 - exp(-c).

[0053] In practical applications, we typically focus on spatial 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 radius dc. Based on this, we can adjust the above formula to suit the actual situation, thereby calculating the collision probability P between spatial objects i and j. ij .

[0054] Step S2: Perform space debris collision detection using a space grid collision screening algorithm; this includes: establishing two sets of concentric circles with different granularities, centered on the spacecraft and based on different threshold ranges; using the coarser set of concentric circles for initial screening to exclude space debris without collision risk; then using a finer set of concentric circles for a second round of screening to identify space debris that may collide and classify them into a potential collision set.

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

[0056] Step S21: Extract the time code based on the spatiotemporal code of a spacecraft's ring unit, and extract the set of ring units with the same time code through binary XOR operation to form the first code set;

[0057] Step S22: Extract spatial codes based on the spatiotemporal codes of the ring units, remove ring units in the first coding set that are different from the spatial codes and not in the same reference space, extract the ring unit set that is the same as the spatial codes to form a second coding set, and perform a first shift on the spatial codes to obtain the first shifted spatial codes;

[0058] Step S23: In the second encoding set, search for the set of neighboring sphere units of the first shifted space code according to the space grid between the Earth and the Moon, and perform the first round of screening procedure with the space code and its neighboring sphere unit codes as the screening conditions to determine the encoding set of the first group of space debris for the second encoding set.

[0059] Step S24: Based on the coding set of the first set of spatial fragments as the filtering criteria, the corresponding sphere units are retrieved to construct the third set of coding sets. Subsequently, a second displacement operation is performed on these spatial codes to obtain the second set of displacement spatial codes.

[0060] Step S25: In the third coding set, search for the set of neighboring sphere units of the second displacement space code according to the space grid between the Earth and the Moon, and perform a second round of screening procedure using the second displacement space code and its neighboring sphere unit codes as screening conditions to identify potential collision risk space debris groups for the second coding set.

[0061] A spacecraft A orbiting in orbit forms a set of three-dimensional data elements across all the orbital units it traverses within the time interval [T0, T0+ΔT]. All spatial fragments also constitute an independent set of ternary data, represented as In this way, collision analysis of spacecraft A can be performed by assessing the distance between two ring elements and their adjacency. This method transforms the assessment of collision risk into an analysis of the geometric relationships between elements in the dataset.

[0062] When assessing the collision risk between space debris and spacecraft, a coarse-grained ensemble of ring cells is used for initial screening to eliminate debris that is clearly unlikely to collide. Subsequently, a finer-grained ensemble of ring cells is applied for further screening to identify potential collisions.

[0063] Specifically, the dimensions are defined as radial ±5 km, track ±25 km, and lateral ±5 km. Based on this, the partitioning level N1 is defined as the smallest outer envelope volume unit. A spatial fragmentation dataset is constructed based on this level, represented as follows: The second set of thresholds has a narrower range: radial ±2 km, trace ±5 km, and lateral ±2 km. The corresponding minimum unit subdivision level is N², forming a unit set and generating a corresponding ternary dataset, represented as follows:

[0064] The following is a process description.

[0065] Step 1: After selecting a three-dimensional unit of spacecraft A, obtain the spatiotemporal code of that unit, denoted as... (where time encoding and sampling time T) i Correspondingly),

[0066] Subsequently, by comparing the time codes, the time code T was selected. Code-iB Matching 3D units and determining the subdivision level N of these units ultimately form the corresponding encoding set C.N .

[0067] Step 2: Extraction of Next, sphere units without celestial identifiers and those from different reference space bodies are excluded, forming the coding set C. N' Considering the characteristics of Hilbert encoding, we will encode... Perform a right shift operation of N - N1 to obtain the Hilbert code after the shift.

[0068] Step 3: Use the model to calculate and find the neighboring sphere cells of the space grid between the Earth and the Moon. The set of neighboring concentric units is then used to record the corresponding codes of these neighboring concentric units. As a filtering criterion, from set C N' Extract the ring-shaped units whose first N1 bits match the selection criteria to form a new code set. Through this process, we are able to roughly filter out sets of space debris that may collide.

[0069] Step 4: Perform further filtering, using sets as the filtering criteria. The retrieved unit is denoted as Since N > N², the binary representation of SolidCellCode is... Perform a right shift operation of N - N2, followed by binary operations, to obtain the shifted Hilbert code.

[0070] Step 5: Search based on neighboring sphere units, in Search in Then perform further filtering, with the following filtering criteria: from Extract the first N2 bits and Same encoding, forming The final result is a collection of collision space fragments.

[0071] Step S3: Based on the results of the space debris collision detection, screen out space debris that may collide and issue an early warning.

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

[0073] After issuing the warning, the space debris that may collide with the spacecraft will be observed with high precision. If the probability of a collision is too high, the spacecraft will take evasive action.

[0074] In one specific embodiment of the present invention, a spatial grid between the Earth and the Moon is used to achieve refined grid-based management of space debris. Simultaneously, based on the proximity between the Earth and the Moon, a space debris collision early warning and screening process can be efficiently executed. Its advantages are:

[0075] This is achieved through the conversion of geographic coordinates to codes and binary encoding operations. This method avoids the CPU-intensive iterative root-finding algorithms of traditional methods, such as orbital altitude screening, orbital plane intersection calculation, orbital phase analysis, and minimum approach distance evaluation. Furthermore, this method significantly reduces the number of judgments required in the collision detection process. In traditional collision screening, achieving a 99% debris rejection rate typically requires a complex screening process involving five stages. The new method improves the efficiency of the screening process by reducing these unnecessary computational steps.

[0076] The space debris rejection rate is high. Orbital data from 8,000 pieces of space debris are managed through a space grid between Earth and the Moon.

[0077] The spatial grid collision screening algorithm was used on SPOT-7 in France at 12:00 on December 2, 2014. The experimental results are shown in the table below.

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

[0079] Collision screening Rejection rate By several percent Coarse screening 94.9 4.6 Fine screening 99.1 0.7

[0080] After filtering space debris collision results using the space grid between Earth and the Moon, the system immediately activates an early warning mechanism and issues a warning upon identifying a potential collision risk. Once the early warning procedure is complete, more precise observations are initiated to further confirm and assess the likelihood of a collision. The measurement accuracy of orbital parameters and covariance matrices is optimized, and the system performs in-depth calculations to obtain more accurate values. Further analysis of the collision probability is then conducted. When the assessment results reveal that the collision risk value exceeds predetermined safety limits, the system will recommend evasive action for the spacecraft to ensure its safety.

[0081] Traditional methods for space debris collision screening typically require a complex five-stage screening process to achieve a 99% debris rejection rate. This improved efficiency not only saves computational resources but also allows for collision risk assessment in a shorter time. By managing space debris orbital data through a spatial grid between Earth and the Moon and employing a grid-based collision screening algorithm, experimental results show that coarse and fine screening can efficiently reject a large number of space debris unlikely to collide, thus concentrating resources on more precise analysis of high-risk collisions. The spatial grid between Earth and the Moon enables refined grid-based management of space debris. Simultaneously, based on the proximity between Earth and the Moon, the space debris collision warning and screening process can be executed efficiently. This allows for the rapid screening of potentially colliding space debris and the issuance of warnings when potential collision risks are detected, providing a time window for further avoidance measures. After completing the warning procedure, a high-precision observation strategy is needed to optimize the accuracy of orbital parameter and covariance matrix measurements, thereby deriving more accurate orbital values. This helps to more accurately assess collision risks and provides more reliable data support for avoidance maneuvers.

[0082] Example 2

[0083] One embodiment of the present invention provides a digital twin system for space debris collision detection, referring to... Figure 2 As shown, it includes:

[0084] Mesh Processing Module 10: Used for meshing space debris between Earth and the Moon;

[0085] Collision detection module 20: used to perform space debris collision detection on the space debris using a space grid collision screening algorithm; including: centering on the spacecraft, defining two sets of regions with different levels of fineness, each corresponding to a different detection threshold. A coarser set of regions is used for initial screening to exclude space debris that does not pose a collision risk. Subsequently, a finer set of regions is used for secondary screening to determine the set of potential collision space debris.

[0086] Early warning module 30: Used to filter out 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 gridding processing module 10 is further configured to: establish a ternary dataset, the ternary dataset including: within a specific time period, a spatiotemporal encoding set of the sphere unit where the space debris orbit is located at the sampling instant, and detailed attribute information and environmental data of the space debris inside the associated sphere unit, thereby realizing gridded management and processing of space debris.

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

[0089] The time code is extracted based on the spatiotemporal code of a spacecraft's ring unit, and the set of ring units with the same time code is extracted by binary XOR operation to form the first code set;

[0090] Based on the spatiotemporal coding of the sphere unit, the spatial coding is extracted. The sphere units in the first coding set that are different from the spatial coding and are not in the same reference space are removed. The sphere unit set that is the same as the spatial coding is extracted to form the second coding set. The spatial coding is then shifted for the first time to obtain the first shifted spatial coding.

[0091] In the second set of codes, the set of neighboring sphere units of the first shifted space code is searched according to the space grid between the Earth and the Moon. The first round of screening is performed using the space code and its neighboring sphere unit codes as screening conditions. For the second set of codes, the set of codes for the first set of space debris is determined.

[0092] Using the first set of spatial fragment codes as a filtering criterion, corresponding sphere units are retrieved to construct the third set of codes. Subsequently, a second displacement operation is performed on these spatial codes to obtain the second set of displacement spatial codes.

[0093] In the third coding set, the set of neighboring sphere units of the second displacement space code is searched according to the space grid between the Earth and the Moon. Using the second displacement space code and its neighboring sphere unit codes as filtering conditions, a second round of filtering is performed to identify potential collision risk space debris groups for the second coding set.

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

[0095] In one 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 an early warning, and to perform avoidance operations on the aircraft if the probability of collision is too high.

[0096] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

[0097] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. The embodiments of the present invention are illustrated by flowcharts and / or block diagrams, which can be understood as computer program instructions. These diagrams depict the implementation process of the method, terminal device (system), and computer program product of the present invention. It should be understood that each step and / or module in the flowcharts and / or block diagrams, as well as combinations 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 equipment to form a machine capable of performing a specific function.

[0098] Furthermore, these computer program instructions can be stored in computer-readable storage media, which, when loaded onto a computer or other programmable data processing device, can instruct the device to operate in a predetermined manner to achieve the functions described in the flowchart or block diagram. The storage and execution of these instructions provide a basis for manufacturing devices capable of performing one or more steps in the flowchart or block diagram. Although preferred embodiments of the present invention have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to include both the preferred embodiments and all changes and modifications falling within the scope of the present invention. Finally, the relational terms such as "first" and "second" used are only used to distinguish different entities or operations and do not necessarily indicate an actual connection or order between them. Furthermore, "comprising," "including," and their synonyms refer to non-limiting inclusion, meaning that the series of elements, steps, articles, or devices involved not only includes the expressly listed elements but may also include other elements not expressly mentioned, or include those inherent elements. In the absence of other limitations, the expression "comprising one..." does not exclude the possibility of other identical elements.

[0099] The methods and apparatus provided by the present invention have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of the present invention. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of the present invention. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of the present invention. Therefore, the content of this specification should not be construed as a limitation of the present invention.

[0100] In the description of this specification, references to terms such as "an embodiment," "some embodiments," "example," "specific example," or "a specific embodiment" or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, illustrative expressions of terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0101] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions 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 this application.

Claims

1. A digital twin method for space debris collision detection, characterized in that, include: Step S1: The space grid between Earth and the Moon is used to mesh space debris; Step S2: Perform space debris collision detection on the space debris using a space grid collision screening algorithm, including: taking the spacecraft as the center, defining two sets of regions with different levels of fineness, each corresponding to different detection thresholds, using the coarser set of regions for preliminary screening to exclude space debris that does not pose a collision risk, and using the finer set of regions for secondary screening to determine the set of potential collision space debris. Step S3: Based on the set of space debris that may collide, filter out the space debris that may collide and issue an early warning; Step S2 includes: Step S21: Extract the first encoding set by performing a binary XOR operation on the time encoding extracted from the spatiotemporal encoding; Step S22: Extract spatial codes based on the spatiotemporal codes of the ring units, remove ring units in the first coding set that are different from the spatial codes and not in the same reference space, extract the ring unit set that is the same as the spatial codes to form a second coding set, and perform a first shift on the spatial codes to obtain the first shifted spatial codes; Step S23: In the second coding set, search for the set of neighboring sphere units of the first displacement space code according to the space grid between the Earth and the Moon, and perform the first round of screening procedure with the space code and its neighboring sphere unit codes as the screening conditions to determine the coding set of the first group of space debris for the second coding set. Step S24: Based on the coding set of the first set of spatial fragments as the filtering criteria, retrieve the corresponding sphere units to construct the third set of coding sets, and perform a second displacement operation on these spatial codes to obtain the spatial codes after the second displacement. Step S25: In the third set of codes, search for the set of neighboring sphere units of the second displacement space code according to the space grid between the Earth and the Moon. Using the second displacement space code and its neighboring sphere unit codes as filtering conditions, perform a second round of filtering to identify potential collision risk space debris groups for the second set of codes.

2. The digital twin method for space debris collision detection according to claim 1, characterized in that, Step S1 further includes: establishing a ternary dataset to achieve gridded processing of spatial fragments; The ternary dataset includes: determining the orbital position of space debris by spatiotemporal coding of specific regional units where the sampling time is located within a specific time range, and also associating the characteristics of space debris and related environmental information within these regional units.

3. The digital twin method for space debris collision detection according to claim 1, characterized in that, The spatial encoding is binary Hilbert encoding.

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

5. A digital twin system for space debris collision detection, characterized in that, include: Mesh processing module: Used for meshing space debris between Earth and the Moon; Collision detection module: used to perform space debris collision detection on the space debris using a space grid collision screening algorithm; including: taking the spacecraft as the center, defining two sets of regions with different levels of fineness, each corresponding to different detection thresholds, using the coarser set of regions for preliminary screening to exclude space debris that does not pose a collision risk, and using the finer set of regions for secondary screening to determine the set of potential collision space debris; Early warning module: Used to filter out space debris that may collide with a set of space debris that may collide and issue an early warning; The collision detection module is used to perform the following operations: The first encoding set is formed by extracting the set of concentric units that are identical to the time encoding through binary XOR operation of the time encoding extracted from the spatiotemporal encoding; Based on the spatiotemporal coding of the sphere unit, the spatial coding is extracted. The sphere units in the first coding set that are different from the spatial coding and are not in the same reference space are removed. The sphere unit set that is the same as the spatial coding is extracted to form the second coding set. The spatial coding is then shifted for the first time to obtain the first shifted spatial coding. In the second coding set, the set of neighboring sphere units of the first shifted space code is searched according to the space grid between the Earth and the Moon. The space code and its neighboring sphere unit codes are used as the filtering conditions to perform the first round of filtering. For the second coding set, the coding set of the first group of space debris is determined. Using the first set of spatial fragment codes as a filtering criterion, the corresponding sphere units are retrieved to construct the third set of codes. A second displacement operation is then performed on these spatial codes to obtain the spatial codes after the second displacement. In the third set of codes, the set of neighboring sphere units of the second displacement space code is searched according to the space grid between the Earth and the Moon. The second displacement space code and its neighboring sphere unit codes are used as the filtering criteria to perform a second round of filtering to identify potential collision risk space debris groups for the second set of codes.

6. The digital twin system for space debris collision detection according to claim 5, characterized in that, The gridding processing module is also used to establish a ternary dataset to achieve gridding processing of space debris; wherein, the ternary dataset includes: within a specific time range, determining the orbital position of space debris by the spatiotemporal encoding of the specific regional unit where the sampling time is located, and also associating the characteristics of space debris and related environmental information within these regional units.

7. The digital twin system for space debris collision detection according to claim 5, characterized in that, The spatial encoding is binary Hilbert encoding.

8. The digital twin system for space debris collision detection according to claim 5, characterized in that, The early warning module is also used to conduct high-precision observation of the space debris that may collide after issuing an early warning, assess its risk level based on the collision probability of the space debris, and if the calculated risk value exceeds the preset safety limit, then the spacecraft's avoidance procedure is initiated and maneuvering is performed to ensure safety.

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