Finite element model correction method and device for space debris risk assessment

Abstract

The invention provides a method and a device for correcting a finite element model for space debris risk assessment. The method comprises the following steps: acquiring a finite element model of a spacecraft; wherein the finite element model comprises a point unit, a beam unit, a shell unit and an entity unit; all types of units in the finite element model are identified, and node parameters of the identified entity units are extracted; deleting a point unit, a beam unit and an entity unit identified in the finite element model; based on the node parameters, reconstructing the deleted entity unit into a target shell unit; and combining the target shell unit with the shell unit identified by the finite element model to correct the finite element model, so that the entity unit is quickly optimized into the shell unit, the original shielding relationship can be maintained, the finite element model is ensured to be smoothly applied to space debris risk assessment software, and the space debris risk assessment efficiency is improved. The calculation efficiency and accuracy of the finite element model in risk assessment software can be improved.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft on-orbit flight technology, and in particular to a correction method and device for a finite element model used for space debris risk assessment. Background Art

[0002] With the development of space technology and the increase of space activities, the space debris environment is deteriorating, and the threat of space debris to spacecraft in orbit is also increasing. Space debris includes objects of various sizes, from abandoned satellites and rocket wreckage to tiny paint flakes and dust. They orbit the earth at high speeds and pose a serious threat to spacecraft in orbit. Therefore, conducting space debris risk assessment on spacecraft and calculating the probability of them being hit has become an important topic in the aerospace field.

[0003] Traditional space debris risk assessment methods rely on finite element models to simulate the structure of spacecraft. These models usually include different types of units such as point units, beam units, shell units and solid units to facilitate dynamic or thermodynamic simulation calculations. However, existing space debris risk assessment software can only read in shell units for calculation. When solid units are included in the finite element model, it will encounter difficulties in processing, resulting in reduced calculation efficiency and even inability to perform effective risk assessment.

[0004] In addition, some existing solutions, such as the finite element model correction method with patent application number 202410158237.6, mainly focus on optimizing the dynamic characteristics of the model, such as adjusting concentrated mass points, center of gravity or multi-point constraints, but do not fully consider the occlusion relationship between units and cannot directly serve risk assessment. Summary of the invention

[0005] The present invention provides a method and device for correcting a finite element model for space debris risk assessment, which are used to solve the technical problem in the prior art that solid elements cannot be quickly converted into shell elements.

[0006] In one aspect, the present invention provides a method for correcting a finite element model for space debris risk assessment, comprising:

[0007] Acquire a finite element model of the spacecraft; wherein the finite element model includes point elements, beam elements, shell elements and solid elements;

[0008] Identify all types of units in the finite element model and extract node parameters of the identified solid units;

[0009] Deleting point elements, beam elements, and solid elements identified in the finite element model;

[0010] Based on the node parameters, reconstructing the deleted solid elements into target shell elements;

[0011] The target shell element is merged with the shell element identified in the finite element model to modify the finite element model.

[0012] According to a method for correcting a finite element model for space debris risk assessment provided by the present invention, the step of identifying all types of units in the finite element model comprises:

[0013] Based on the unit position vectors and the node position vectors in the finite element model, construct a first equation to be identified; wherein the coefficients of the unit position vectors and the node position vectors in the first equation are unknown parameters;

[0014] Based on the unit position vector and the node position vector in the finite element model, construct a second equation for identification; wherein the coefficients of the unit position vector and the node position vector in the second equation are known parameters;

[0015] determining an error vector based on the first equation and the second equation;

[0016] Based on the error vector, construct an optimal function equation;

[0017] constructing an iterative function based on the error vector;

[0018] Based on the optimal function equation and the iterative function, all types of elements in the finite element model are identified.

[0019] According to a correction method for a finite element model for space debris risk assessment provided by the present invention, the first equation is shown as follows:

[0020]

[0021] Among them, x represents the unit position vector, u represents the node position vector, A and B represent the coefficients of x and u respectively, which are unknown parameters. represents the time derivative of the cell position vector;

[0022] The second equation is shown as follows:

[0023]

[0024] Among them, M and N represent the coefficients of x and u respectively, which are known parameters. represents the time derivative of the unit position vector under the known parameters M and N;

[0025] The error vector is shown in the following formula:

[0026] e=xx p ;

[0027] Where e represents the error vector, x p Represents the unit position vector under the influence of known parameters M and N.

[0028] According to a method for correcting a finite element model for space debris risk assessment provided by the present invention, the optimal function equation is shown in the following formula:

[0029]

[0030] in, P represents the result of the optimal function equation.

[0031] According to a method for correcting a finite element model for space debris risk assessment provided by the present invention, the iterative function is shown in the following formula:

[0032]

[0033] Where i and j are both positive integers, i represents the number of iterations, j represents the element number, j≤3; h j Denotes each pair of elements of the matrix H, H = [m 11 m 12 m 21 m 22 n1 n2] T ;m 11 、m 12 、m 21 、m 22 is an element of M; n1 and n2 are elements of N; α, β, γ, λ are coefficients greater than 0; u i represents the node position vector of the i-th iteration; u i+1 Represents the node position vector of the i+1th iteration.

[0034] According to a method for correcting a finite element model for space debris risk assessment provided by the present invention, the deleted solid elements are reconstructed into target shell elements based on the node parameters, comprising:

[0035] Based on the node parameters, determining the node positions and connection relationships of the target shell element;

[0036] Based on the determined node positions and connection relationships, the geometric shape of the target shell element is determined;

[0037] Based on the geometric shape, target shell elements are constructed.

[0038] According to a method for correcting a finite element model for space debris risk assessment provided by the present invention, merging the target shell element with the shell element identified by the finite element model comprises:

[0039] Merge the node information of the newly created target shell element and the original shell element to remove redundant nodes;

[0040] Updates the connections between all shell elements to maintain the integrity of the finite element model.

[0041] According to a method for modifying a finite element model for space debris risk assessment provided by the present invention, before deleting the point elements, beam elements and solid elements identified in the finite element model, the method further includes:

[0042] The point elements, beam elements and solid elements identified in the finite element model are backed up.

[0043] On the other hand, the present invention also provides a correction device for a finite element model for space debris risk assessment, comprising:

[0044] A unit acquisition module, which acquires a finite element model of the spacecraft; wherein the finite element model includes point elements, beam elements, shell elements and solid elements;

[0045] A unit identification module, identifying all types of units in the finite element model and extracting node parameters of the identified entity units;

[0046] A deletion module is used to delete the point elements, beam elements and solid elements identified in the finite element model;

[0047] A reconstruction module, based on the node parameters, reconstructs the deleted solid elements into target shell elements;

[0048] A merging module is used to merge the target shell element with the shell element identified by the finite element model to modify the finite element model.

[0049] On the other hand, the present invention also provides an electronic device, comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, it implements any of the above-mentioned methods for correcting a finite element model for space debris risk assessment.

[0050] The method and device for correcting a finite element model for space debris risk assessment provided by the present invention identify all types of units in the finite element model and extract node parameters of the identified entity units; delete point units, beam units and entity units identified in the finite element model; reconstruct the deleted entity units into target shell units based on the node parameters; merge the target shell units with the shell units identified by the finite element model to correct the finite element model, thereby realizing rapid optimization of the entity units into shell units and maintaining the original occlusion relationship, thereby ensuring that the finite element model is smoothly applied to space debris risk assessment software, and improving the calculation efficiency and accuracy of the finite element model in the risk assessment software. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] In order to more clearly illustrate the technical solutions in the present invention or the prior art, a brief introduction will be given below to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0052] Figure 1 is a flow chart of a method for correcting a finite element model for space debris risk assessment provided by an embodiment of the present invention;

[0053] Figure 2 is a schematic structural diagram of a finite element model to be optimized provided by an embodiment of the present invention;

[0054] Figure 3 is a schematic diagram of the structure of each unit of the finite element model provided in an embodiment of the present invention;

[0055] Figure 4 It is a structural schematic diagram of shell elements and node parameters of a finite element model provided by an embodiment of the present invention;

[0056] Figure 5 is a schematic structural diagram of a finite element model of a reconstructed target shell element provided by an embodiment of the present invention;

[0057] Figure 6 is a schematic structural diagram of a merged finite element model provided by an embodiment of the present invention;

[0058] Figure 7 It is a schematic structural diagram of a correction device for a finite element model for space debris risk assessment provided by an embodiment of the present invention;

[0059] Figure 8 It is a schematic diagram of the structure of an electronic device provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0060] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0061] Figure 1 It is a flow chart of a method for correcting a finite element model for space debris risk assessment provided by an embodiment of the present invention. The executor of the method may be a computer, a mobile phone, a smart wearable device, etc. The finite element model of a spacecraft is a numerical analysis method used to simulate and analyze the structural performance of a spacecraft. This method discretizes a complex continuous structure (such as various components of a spacecraft) into a finite number of small elements, namely finite elements, each of which has a simple geometric shape (such as a beam, a shell, a solid, etc.), and these elements are connected by nodes.

[0062] See also Figure 1 , a method for correcting a finite element model for space debris risk assessment may include the following steps 101 to 105.

[0063] 101. Obtain a finite element model of the spacecraft; wherein the finite element model includes point elements, beam elements, shell elements, and solid elements.

[0064] You can store the finite element model to a specified location and then read the finite element model.

[0065] 102. Identify all types of units in the finite element model and extract the node parameters of the identified solid units.

[0066] Specifically, all types of elements in the finite element model are identified including:

[0067] Based on the unit position vector and the node position vector in the finite element model, a first equation to be identified is constructed; wherein the coefficients of the unit position vector and the node position vector in the first equation are unknown parameters;

[0068] Based on the unit position vector and the node position vector in the finite element model, a second equation for identification is constructed; wherein the coefficients of the unit position vector and the node position vector in the second equation are known parameters;

[0069] Based on the first equation and the second equation, determining an error vector;

[0070] Based on the error vector, construct the optimal function equation;

[0071] Based on the error vector, an iterative function is constructed;

[0072] Based on the optimal function equation and iterative function, all types of elements in the finite element model are identified.

[0073] 103. Delete the point elements, beam elements and solid elements identified in the finite element model.

[0074] You can use the delete command or API provided by the finite element analysis software to delete the specified point elements, beam elements and solid elements according to the element identifier; or provide a visualization tool to delete them.

[0075] 104. Based on the node parameters, the deleted solid elements are reconstructed into target shell elements.

[0076] Nodal parameters generally include nodal coordinates, nodal connectivity, material properties, and geometric characteristics (such as volume, surface area, etc.).

[0077] Specifically, based on the node parameters, the deleted solid elements are reconstructed into target shell elements including:

[0078] Based on the node parameters, determine the node position and connection relationship of the target shell element;

[0079] Based on the determined node positions and connection relationships, the geometric shape of the target shell element is determined;

[0080] Based on the geometry, the target shell elements are constructed.

[0081] 105. Merge the target shell element with the shell element identified in the finite element model to correct the finite element model.

[0082] Specifically, merging the target shell element with the shell element identified by the finite element model includes:

[0083] Merge the node information of the newly created target shell element and the original shell element to remove redundant nodes;

[0084] Updates the connections between all shell elements to maintain the integrity of the finite element model.

[0085] In this embodiment, all types of units in the finite element model are identified, and the node parameters of the identified solid units are extracted; the point units, beam units and solid units identified in the finite element model are deleted; based on the node parameters, the deleted solid units are reconstructed into target shell units; the target shell units are merged with the shell units identified in the finite element model to correct the finite element model, thereby achieving rapid optimization of the solid units into shell units and maintaining the original occlusion relationship, thereby ensuring the smooth application of the finite element model in the space debris risk assessment software, and improving the computational efficiency and accuracy of the finite element model in the risk assessment software.

[0086] In one embodiment of the present specification, the first equation is as shown in the following formula (1):

[0087]

[0088] Among them, x represents the unit position vector, u represents the node position vector, A and B represent the coefficients of x and u respectively, which are unknown parameters. represents the time derivative of the cell position vector;

[0089] The second equation is shown in formula (2):

[0090]

[0091] Among them, M and N represent the coefficients of x and u respectively, which are known parameters. represents the time derivative of the unit position vector under the known parameters M and N;

[0092] From formula (1) and formula (2), we can get the following formula (3):

[0093]

[0094] in, is the time derivative of the error vector;

[0095] The error vector is shown in the following formula (4):

[0096] e=xx p (4);

[0097] Where e represents the error vector, x p represents the unit position vector under the known parameters M and N, x p is a known quantity.

[0098] In this embodiment, M may be a 2×2 matrix, and N may be a 2×1 matrix. Since x and u are linearly independent, When A→M, B→N, the arrows represent the meaning of approaching. The above parameters and formulas together constitute a system identification framework based on a neural network algorithm, which is used to optimize the unit type identification and key node parameter extraction of the spacecraft finite element model.

[0099] In one embodiment of the present specification, the optimal function equation is shown in the following formula (5):

[0100]

[0101] in, P represents the result of the optimal function equation. The optimal function equation can be understood as the minimum value of P.

[0102] In this embodiment, it is obvious that P→0 is related to Equivalent, the arrow indicates the meaning of approaching. From formula (5), we can get the following formula (6):

[0103] In one embodiment of the present specification, the iterative function is as shown in the following formula (7):

[0104]

[0105] Where i and j are both positive integers, i represents the number of iterations, j represents the element number, j≤3; h j Denotes each pair of elements of the matrix H, H = [m 11 m 12 m 21 m 22 n1 n2] T ;m 11 、m 12 、m 21 、m 22 is an element of M; n1 and n2 are elements of N; α, β, γ, λ are coefficients greater than 0; u i represents the node position vector of the i-th iteration; u i+1 Represents the node position vector of the i+1th iteration.

[0106] In this embodiment, the process of the above-mentioned optimal function equation tending to a minimum is the process of the estimated matrices M and N gradually converging to the actual matrices A and B. By constructing an iterative function, the iteration of M and N can be gradually completed, infinitely approaching A and B, and finally, the node parameters of the entity unit in the finite element model are automatically identified (the node parameters here are generally key parameters). α, β, γ, λ mainly depend on factors such as the envelope size of the finite element model, the density of the grid, and the minimum spacing of the nodes. The gradually obtained stable u i Substituting into formula (8), we can get the stable h i , you can get A and B.

[0107] In one embodiment of the present specification, before deleting the point elements, beam elements and solid elements identified in the finite element model, the method further includes:

[0108] Back up the point elements, beam elements, and solid elements identified in the finite element model.

[0109] In this embodiment, a backup is performed before deleting any unit, which provides a safety mechanism to prevent errors in the deletion operation or the need to roll back to the original state, thereby increasing the flexibility and safety of the operation.

[0110] Combine the following Figures 2 to 6 , taking a simple tablet as an example, the present invention is further introduced. Figures 2 to 6 In the above diagram, we can see the specific direction of the space debris flow. Figure 3 The number 1 in the figure represents a point element, the number 2 represents a beam element, the number 3 represents a shell element, and the number 4 represents a solid element. Figure 4 The number 5 in represents the extracted node parameters of the identified entity elements. Figure 5 The number 6 in represents the target shell element of the reconstruction.

[0111] like Figure 2 As shown, Figure 2 It is a structural schematic diagram of the finite element model to be optimized provided by an embodiment of the present invention, and the finite element model to be optimized is used as the initial model. The initial model contains 1 point unit, 1 beam unit, 56 shell units, and 72 solid units, a total of four categories, a total of 130 finite units. If the initial model is directly read into the space debris risk assessment software to carry out calculations related to the occlusion algorithm, the software will carry out calculations for each unit. The process is relatively cumbersome, and it is difficult to process solid units. If they are adjusted manually one by one, the efficiency is low.

[0112] According to the above formula of the present invention, the identification process is as follows.

[0113] Step 1: Setup x=[x1x2]=[23t 24t], indicating the unit position vector; set u1=[u 11 u 12 ]=[23t 2 24t 2 ], represents the node position vector.

[0114] Configurable

[0115] Step 2: Based on the above formula, we can get H = [1 0 0 1 1 0].

[0116] Step 3: Based on the above formula, we can get u2=[u 21 u 22 ]=[19t 2 20t 2 ].

[0117] Step 4: Repeat steps 1 to 3 until u 965 -u 964 ≤0.001, that is, it can be considered that a stable u is finally obtained 965 , at this time, i=964.

[0118] Step 5: Using formula (7), we can get h j, that is, H = [11 0 0 12 10 0], we get Identification is complete.

[0119] By comparison Figure 2 and Figure 6 , in a given space debris flow direction, Figure 6 and Figure 2 The projection area and the occlusion relationship between the units are exactly the same. This shows that Figure 6 A large number of units that do not affect the occlusion relationship and projection area have been deleted, and the number and types of finite units have been greatly reduced. Figure 6 There are only 71 shell elements in the model, which greatly improves the calculation efficiency. At the same time, it does not affect the calculation of the occlusion algorithm, so it does not affect the evaluation results of the space debris risk assessment software.

[0120] Based on the same general inventive concept, the present invention also protects a correction device for a finite element model for space debris risk assessment, such as Figure 7 As shown, Figure 7 1 is a schematic diagram of the structure of the correction device of the finite element model for space debris risk assessment provided by an embodiment of the present invention. The correction device of the finite element model for space debris risk assessment provided by the present invention is described below. The correction device of the finite element model for space debris risk assessment described below and the correction method of the finite element model for space debris risk assessment described above can be referred to each other.

[0121] The correction device of the finite element model for space debris risk assessment includes a unit acquisition module 701, a unit identification module 702, a deletion module 703, a reconstruction module 704 and a merging module 705.

[0122] The unit acquisition module 701 acquires a finite element model of the spacecraft; wherein the finite element model includes point elements, beam elements, shell elements and solid elements;

[0123] The unit identification module 702 identifies all types of units in the finite element model and extracts node parameters of the identified entity units;

[0124] The deletion module 703 deletes the point elements, beam elements and solid elements identified in the finite element model;

[0125] The reconstruction module 704 reconstructs the deleted solid elements into target shell elements based on the node parameters;

[0126] The merging module 705 merges the target shell element with the shell element identified in the finite element model to modify the finite element model.

[0127] Figure 8 It is a schematic diagram of the structure of an electronic device provided by an embodiment of the present invention.

[0128] like Figure 8 As shown, the electronic device may include: a processor 810, a communications interface 820, a memory 830, and a communications bus 840, wherein the processor 810, the communications interface 820, and the memory 830 communicate with each other via the communications bus 840. The processor 810 may call the logic instructions in the memory 830 to execute the correction method of the finite element model for space debris risk assessment.

[0129] In addition, the logic instructions in the above-mentioned memory 830 can be implemented in the form of a software functional unit and can be stored in a computer-readable storage medium when it is sold or used as an independent product. Based on this understanding, the technical solution of the present invention is essentially or the part that contributes to the prior art or the part of the technical solution can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions to enable a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk and other media that can store program codes.

[0130] On the other hand, the present invention also provides a computer program product, which includes a computer program. The computer program can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the correction method of the finite element model for space debris risk assessment provided by the above methods.

[0131] On the other hand, the present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, is implemented to execute the correction method of the finite element model for space debris risk assessment provided by the above-mentioned methods.

[0132] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0133] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0134] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention 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 deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for modifying a finite element model for space debris risk assessment, characterized in that: include: Acquire a finite element model of the spacecraft; wherein the finite element model includes point elements, beam elements, shell elements and solid elements; Identify all types of units in the finite element model and extract node parameters of the identified solid units; Deleting point elements, beam elements, and solid elements identified in the finite element model; Based on the node parameters, reconstructing the deleted solid elements into target shell elements; The target shell element is merged with the shell element identified in the finite element model to modify the finite element model.

2. The method for correcting a finite element model for space debris risk assessment according to claim 1, characterized in that: The identifying of all types of elements in the finite element model comprises: Based on the unit position vectors and the node position vectors in the finite element model, construct a first equation to be identified; wherein the coefficients of the unit position vectors and the node position vectors in the first equation are unknown parameters; Based on the unit position vector and the node position vector in the finite element model, construct a second equation for identification; wherein the coefficients of the unit position vector and the node position vector in the second equation are known parameters; determining an error vector based on the first equation and the second equation; Based on the error vector, construct an optimal function equation; constructing an iterative function based on the error vector; Based on the optimal function equation and the iterative function, all types of elements in the finite element model are identified.

3. The method for correcting a finite element model for space debris risk assessment according to claim 2, characterized in that: The first equation is shown as follows: Among them, x represents the unit position vector, u represents the node position vector, A and B represent the coefficients of x and u respectively, which are unknown parameters. represents the time derivative of the cell position vector; The second equation is shown as follows: Among them, M and N represent the coefficients of x and u respectively, which are known parameters. represents the time derivative of the unit position vector under the known parameters M and N; The error vector is shown in the following formula: e=x-x p ; Where e represents the error vector, x p Represents the unit position vector under the influence of known parameters M and N.

4. The method for correcting a finite element model for space debris risk assessment according to claim 3, characterized in that: The optimal function equation is shown in the following formula: in, P represents the result of the optimal function equation.

5. The method for correcting a finite element model for space debris risk assessment according to claim 4, characterized in that: The iterative function is shown in the following formula: Where i and j are both positive integers, i represents the number of iterations, j represents the element number, j≤3; h j Denotes each pair of elements of the matrix H, H = [m 11 m 12 m 21 m 22 n1 n2] T ;m 11 、m 12 、m 21 、m 22 is an element of M; n1 and n2 are elements of N; α, β, γ, λ are all values ​​greater than 0; u i represents the node position vector of the i-th iteration; u i+1 Represents the node position vector of the i+1th iteration.

6. The method for correcting a finite element model for space debris risk assessment according to claim 1, characterized in that: The step of reconstructing the deleted solid elements into target shell elements based on the node parameters includes: Based on the node parameters, determining the node positions and connection relationships of the target shell element; Based on the determined node positions and connection relationships, the geometric shape of the target shell element is determined; Based on the geometric shape, target shell elements are constructed.

7. The method for correcting a finite element model for space debris risk assessment according to claim 1, characterized in that: The step of merging the target shell element with the shell element identified by the finite element model comprises: Merge the node information of the newly created target shell element and the original shell element to remove redundant nodes; Updates the connections between all shell elements to maintain the integrity of the finite element model.

8. The method for correcting a finite element model for space debris risk assessment according to claim 1, characterized in that: Before deleting the point elements, beam elements and solid elements identified in the finite element model, the method further includes: The point elements, beam elements and solid elements identified in the finite element model are backed up.

9. A correction device for a finite element model for space debris risk assessment, characterized in that: include: A unit acquisition module, which acquires a finite element model of the spacecraft; wherein the finite element model includes point elements, beam elements, shell elements and solid elements; A unit identification module, identifying all types of units in the finite element model and extracting node parameters of the identified entity units; A deletion module is used to delete the point elements, beam elements and solid elements identified in the finite element model; A reconstruction module, based on the node parameters, reconstructs the deleted solid elements into target shell elements; A merging module is used to merge the target shell element with the shell element identified by the finite element model to modify the finite element model.

10. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that: When the processor executes the program, the method for correcting the finite element model for space debris risk assessment as described in any one of claims 1 to 8 is implemented.

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