Multistage sandwich beam patching and repairing parameterized modeling method, equipment and medium

Abstract

The invention provides a parameterized modeling method and equipment for patching and repairing a multi-stage sandwich beam and a medium. The parameterized modeling method comprises the following steps: defining parameters required by a model; establishing a geometric model of each component of the multi-stage sandwich beam patching and repairing structure; importing material parameters of each component, and endowing each component with section attributes; assembling a honeycomb sandwich structure and a reinforcing rib structure in an axial symmetry manner, and assembling a multi-stage sandwich beam structure, a repair patch, a replacement core and an adhesive layer according to damage information; dividing grids, setting a contact relation and applying a load; the method comprises the following steps: establishing a bucket analysis step, calculating a buckling mode of a model, importing a dynasc excicit analysis step, and calculating a limit lateral compression load of the model. According to the method, the Python language is used for carrying out secondary development on the Abaqus, compared with a traditional Abaqus modeling process, several hours of modeling time is saved, and rapid modeling and analysis of a complex finite element model are achieved.

Description

Technical Field

[0001] The invention belongs to the technical field of composite material structure repair, and in particular relates to a parameterized modeling method, equipment and medium for repairing a multi-level sandwich beam by cutting and patching. Background Art

[0002] Lightweighting is an eternal topic in the aviation industry. Composite materials are widely used in secondary load-bearing structural components of fuselage because they can significantly reduce structural weight while meeting structural strength requirements and meet lightweighting needs.

[0003] Multi-level sandwich beams are used in aircraft radomes. Their unique honeycomb-filled reinforcement rib structure can significantly improve the bearing capacity of the overall structure. However, radomes often suffer from damage such as cracks, debonding and pits during service. In order to ensure the aerodynamic integrity of the radome, adhesive bonding and patching are usually used for repair. At the same time, the radome is often subjected to lateral compression loads. It is of great significance to study the post-buckling bearing capacity of the reinforced structure and its lateral compression performance.

[0004] When the above structures need to be repaired or repaired beyond the manual, different sizes, materials, layers and other parameters need to be constructed during modeling due to the differences in aircraft models, damage locations and damage degrees. At the same time, due to the complexity of the assembled structure itself (upper and lower panels of composite materials, honeycomb sandwich, reinforcement ribs, adhesive layers, patches), it is necessary to set the position relationship of the components and the contact relationship between the components. The traditional modeling method of Abaqus consumes a lot of time for complex and repetitive operations, which reduces engineering efficiency. Summary of the invention

[0005] In view of this, the present invention aims to overcome the deficiencies of the above-mentioned problems in the prior art and proposes a parametric modeling method, equipment and medium for excavation and repair of multi-level sandwich beams.

[0006] To achieve the above object, the technical solution of the present invention is achieved as follows:

[0007] A first aspect of the present invention provides a parameterized modeling method for repairing a multi-level sandwich beam, comprising the following steps:

[0008] Step 1: Define the parameters required for the model;

[0009] Step 2: Establish geometric models of various components of the multi-level sandwich beam repair structure, including the honeycomb sandwich structure model and the stiffener model. According to the damage location and damage information, remove the damaged areas of the motherboard and the sandwich. According to the damage information, create patch models, core replacement models and glue layer models that match the damaged areas.

[0010] Step 3: Import the material parameters of each component and assign cross-sectional properties to each component;

[0011] Step 4: Assemble the honeycomb sandwich structure and the stiffener structure by axisymmetric assembly, and assemble the multi-level sandwich beam structure and the repair patch, replacement core, and adhesive layer according to the damage information;

[0012] Step 5: Divide the mesh, set the contact relationship, and apply the load;

[0013] Step 6: Create a buckle analysis step to calculate the buckling mode of the model, import the dynamic explicit analysis step, and calculate the ultimate lateral compression load of the model.

[0014] Furthermore, in step 2, constructing a honeycomb sandwich structure model includes:

[0015] Use the Abaqus built-in function setPrimaryObject to enter the sketch interface and draw the sketch;

[0016] The rectangle is constructed by the function rectangle, and its shape is the projection of the honeycomb sandwich structure on the sketch plane;

[0017] The rectangle is stretched to different depths through the BasesolidExtrude function to construct the upper and lower panels and the honeycomb sandwich model of the honeycomb sandwich structure.

[0018] Construct the hierarchical points of the upper and lower panels through the function DatumPointByoffset;

[0019] The panel is layered using the function DatumCsyByThreePoints.

[0020] Furthermore, in step 2, constructing the reinforcement rib model includes:

[0021] In the sketch, use the Line function to connect all the inflection points of the ribs to form a closed curve, and then stretch it to build a rib model;

[0022] In the sketch, some inflection points of the stiffener are connected by the Line function to form a closed curve embedded in the stiffener sketch, and then the honeycomb sandwich model in the stiffener is constructed by stretching;

[0023] The function OffsetFaces is used to offset different face sets of the stiffener to complete the stiffener layering.

[0024] Furthermore, in step 2, removing the damaged area of ​​the motherboard and the interlayer according to the damage position and damage information includes:

[0025] Determine the damage location and damage information based on the parameters;

[0026] Enter the upper panel plane editing through the function MakeSketchTransform, and use the CutExtrude function to loft the panel and interlayer according to the damage location and damage information.

[0027] Furthermore, the step 3 comprises:

[0028] Use the custom functions readlaminate, readadhesive, and readhoney to read the properties of composite materials, adhesive layers, and honeycomb sandwich materials stored in Excel, import them into Abaqus, and form the corresponding section properties;

[0029] The cross-sectional properties of composite materials, adhesive layers, and honeycomb interlayers stored in Excel are read through the custom functions readply_sequence, readsec_adhesive, and readsec_honey to complete the cross-sectional property assignment.

[0030] Further, the step 4 comprises:

[0031] The rotate function is used to implement the component's rotation instruction, and the instanceList function is used to define the rotation object and the rotation angle;

[0032] The component translation instruction is implemented through the translate function, and the vector function defines the translation vector, which is defined by custom parameters;

[0033] According to the damage location information, the patch, core replacement, and adhesive layer are assembled in the damaged area through functions such as rotate and translate.

[0034] Further, the step 5 comprises:

[0035] Meshing includes:

[0036] Determine the grid size through the seedPart function;

[0037] Determine the mesh type through the setElementtype function and the setMeshControls function;

[0038] Define the stacking direction through the assignStackDirection function;

[0039] Setting up contact relationships includes:

[0040] Bind the contact surfaces of components through the Tie function;

[0041] The contact surface is located by the findAt function, and the master and slave surfaces are determined by the master and slave functions;

[0042] Construct the overall contact relationship through the ContactProperty function;

[0043] Applying loads includes defining boundary conditions and loads. Along the axial direction of the stiffener, one end is fixed and the other sides are free. At the other end of the fixed end, a 1N lateral compression load is applied, including:

[0044] Use the ReferencePoints function to establish reference points at the fixed end and the loading end;

[0045] Set the reference point as a set through the Set function;

[0046] The two reference points are coupled to the fixed end and the loading end respectively through the Coupling function;

[0047] The constraints on the fixed end and the application of force loads on the loading end are completed through the EncastreBC and ConcentratedForce functions.

[0048] Further, the step 6 comprises:

[0049] Use the custom function GetBlockPosition to locate the pointer to the relevant position in the inp file, and insert the corresponding code through the insert function to realize the buckling mode extraction function;

[0050] First, calculate the Buckle analysis step through the waitForCompletion function and extract the first-order buckling mode in the result file;

[0051] Create an explicit dynamics analysis step through the ExplicitDynamicsStep function, in which the history output variables and field output variables are defined through the HistoryOutputRequest function and the fieldOutputRequests function respectively;

[0052] Define the displacement load through the DisplacementBC function, define the assignment curve through the SmoothStepAmplitude function, and apply the amplitude curve to the displacement load to improve the stability of the result;

[0053] Use the custom function GetBlockPosition to locate the pointer to the relevant position of the inp file and introduce the buckling mode in the Buckle analysis step;

[0054] The user-defined subroutine is imported through the function userSubroutine, and the stiffness degradation criteria of each material are introduced to calculate the compressive strength and failure mode of the finite element model under lateral compression load.

[0055] A second aspect of the present invention 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, the above-mentioned parameterized modeling method for cutting and repairing a multi-level sandwich beam is implemented.

[0056] A third aspect of the present invention provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the above-mentioned parametric modeling method for cutting and repairing a multi-level sandwich beam.

[0057] Compared with the prior art, the parametric modeling method, device and medium for repairing multi-level sandwich beams described in the present invention have the following advantages:

[0058] The present invention uses Python language to carry out secondary development of Abaqus and build a parametric modeling platform, which realizes accurate modeling of complex finite element models, can greatly save finite element modeling time, and can also verify with engineering test results to improve engineering efficiency.

[0059] The present invention realizes a parameterized modeling method, equipment and medium for a multi-level sandwich beam structure excavation and repair model, and automatic modeling and analysis of the model can be realized by simply changing parameters. BRIEF DESCRIPTION OF THE DRAWINGS

[0060] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0061] Figure 1 It is a schematic flow chart of a parameterized modeling method for repairing a multi-level sandwich beam according to the present invention;

[0062] Figure 2 It is a diagram explaining the structural parameters of the multi-level sandwich beam reinforcement ribs of the present invention;

[0063] Figure 3 It is an explanation diagram of the repair parameters of the upper panel of the multi-level sandwich beam of the present invention;

[0064] Figure 4 An exemplary diagram of the positional relationship of components of the multi-stage sandwich beam overall structure of the present invention;

[0065] Figure 5 This is a partial result diagram of the simulation of the multi-level sandwich beam patching and repair according to the present invention. DETAILED DESCRIPTION

[0066] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0067] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", and the like are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", and the like may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0068] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0069] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0070] Embodiment 1

[0071] like Figure 1 As shown, the present invention provides a parametric modeling method for a multi-level sandwich beam structure excavation and repair model, and the specific steps include:

[0072] Step 1: Define the parameters required for the model;

[0073] 1.1 Define the Buckle analysis step model and the Dynamic explicit analysis step model name respectively (the default is a string object);

[0074] 1.2 Define the parameters required for the honeycomb sandwich structure, including the geometric parameters of the upper and lower panels and the honeycomb sandwich: length, width, height (default is a floating point object), material parameters and section property parameters (default is an xls file) and mesh size parameters (default is a floating point object);

[0075] 1.3 Define the parameters required for the reinforcement structure, including its geometric parameters: the number of outermost plies (the default is an integer constant object), the thickness of a single ply, the overall structure length, the bottom length of the reinforcement, the height of the reinforcement, the angle of the reinforcement, the extension length of the reinforcement ply 1, the extension length of the reinforcement ply 2 (the default is a floating point object) and the section attribute parameters (the default is an xls file);

[0076] 1.4 Define the parameters required for damage, including its damage location parameters: horizontal and vertical coordinates of the damage center point (default is a floating-point object), damage information parameters: damage radius, single-layer thickness of the patch (default is a floating-point object), number of patch layers, and patch miter rate (default is an integer constant);

[0077] 1.5 Define the parameters required for the glue layer, including its geometric parameters: thickness (default is a floating point object) and material parameters (default is an xls file);

[0078] 1.6 Define the parameters required for the work, including displacement load size (default is floating point object), Buckle analysis step work name, Dynamic explicit analysis step work name (default is string object), CPU calculation core number (default is integer constant object), user subroutine selection (default is for file);

[0079] Step 2: Construct a honeycomb sandwich structure model;

[0080] Specifically, step 2 includes the following steps:

[0081] 2.1 Enter the sketch interface through the Abaqus built-in function setPrimaryObject and draw the sketch;

[0082] 2.2 Use the rectangle function to construct a rectangle. The function constructs a rectangle through the positions of two points. The coordinates of the two points are expressed by parameters: (-length / 2,-width / 2).

[0083] (length / 2,width / 2), the rectangle is the projection of the honeycomb sandwich structure on the sketch plane. The honeycomb sandwich structure includes the upper and lower panels of the composite material and the honeycomb sandwich;

[0084] 2.3 Use the function BasesolidExtrude to stretch the rectangle to different depths. The depths are defined by parameters: Depth1, Depth2, Depth_Honey, to construct the upper and lower panels and honeycomb sandwich model of the honeycomb sandwich structure;

[0085] 2.4 Use the function DatumPointByoffset to construct the delamination points of the upper and lower panels respectively. The spacing between the delamination points is determined by reading the ply thickness in the Excel database;

[0086] 2.5 The panels are layered through the function DatumCsyByThreePoints to form the structural characteristics of the composite material.

[0087] Step 3: Construct the reinforcement model;

[0088] Specifically, step 3 includes the following steps:

[0089] 3.1 As Figure 2 As shown, Figure 2 The geometric structure of the multi-level sandwich beam component and the meaning of the parameters required for parameterization are explained. In the sketch, all the inflection points of the stiffener are connected by the Line function to form a closed curve, and then the stiffener model is constructed by stretching. The coordinates of the 20 inflection points of the stiffener are defined by parameters. The parameter coordinates are expressed from 1 to 10 as follows: (-length / 2, 0), (-length / 2, -num_ply*depth),

[0090] (-length / 2+x-num_ply*depth / n2,-num_ply*depth),

[0091] (-length / 2+x-num_ply*depth / n2+depth / n1,

[0092] -(num_ply+1)*depth)、

[0093] (-length / 2+x-num_ply*depth / n2+depth / n1+length3-n3,

[0094] -(num_ply+1)*depth)、

[0095] (-length / 2+x-num_ply*depth / n2+2*depth / n1+length3-n3,

[0096] -(num_ply+1)*depth)、

[0097] (-length / 2+x+length3+length2-(num_ply+2)*depth / n2,

[0098] -(num_ply+2)*depth)、

[0099] (-length / 2+x+length2+length3+depth / sin(angle)+height / n1-(num_ply+3)*depth / n2, -height-(num_ply+3)*depth),

[0100] (-length / 2+length2+length3+x+height / n1+depth / math(angle),-height),

[0101] (-length / 2+x+length2+length3+depth / sin(angle), 0), where the parameter n1 value is tan(angle), the x value is (length-length1 / 2-length2-leng3-depth / sin(angle)-height / n1, angle2=90-angle / 2, the n2 value is tan(angle2), the n3 value is depth / sin(angle) / sin(angle2), the coordinates of inflection point 11 to inflection point 20 are symmetric with the coordinates of inflection point 1 to inflection point 10 about the y-axis, and the horizontal coordinates are changed to the relative values ​​of the horizontal coordinates of the corresponding symmetric points, which will not be repeated here;

[0102] 3.2 In the sketch, some inflection points of the stiffener are connected by the Line function to form a closed curve embedded in the stiffener sketch, and then the honeycomb sandwich model in the stiffener is constructed by stretching;

[0103] 3.3 Use the function OffsetFaces to offset different face sets of the stiffener to complete the stiffener layering, and the faces in the face set are positioned by parameters.

[0104] Step 4: Remove the damaged areas of the motherboard and the interlayer according to the damage location and damage information;

[0105] Specifically, step 4 includes the following steps:

[0106] 4.1 As Figure 3 As shown, the present invention can customize the damage position and damage information, determine the damage position (Coord_xdam, Coord_ydam) and damage information (r_dam, thick_dam, num_dam, K) according to the customized parameters, and provide parameters for the subsequent construction of the repair hole, r_dam is the damage radius, thick_dam is the thickness of the single layer of the repair, num_dam is the number of repair layers, and K is the repair miter rate;

[0107] 4.2 Use the MakeSketchTransform function to enter the upper panel and honeycomb interlayer sketch plane editing, and use the CutExtrude function to loft the upper panel and honeycomb interlayer according to the damage position and damage information. The damaged hole of the honeycomb interlayer is cylindrical, while the damaged hole of the upper panel is a stepped structure.

[0108] Step 5: Create a patch model, a core replacement model, and a glue layer model that match the damaged area based on the damage information;

[0109] Step 6: Assign material properties to the plain woven plate, honeycomb interlayer, and adhesive layer;

[0110] Specifically, step 6 includes the following steps:

[0111] 6.1 Read the material property parameters of composite materials, adhesive layers, and honeycomb sandwich materials stored in Excel through the xlrd library and the custom functions readlaminate, readadhesive, and readhoney, import them into Abaqus, form the corresponding materials, and

[0112] Functions such as HomogeneousSolidSection establish cross-section properties;

[0113] 6.2 Use the custom functions readply_sequence, readsec_adhesive, and readsec_honey to read the cross-sectional properties of composite materials, adhesive layers, and honeycomb sandwiches stored in Excel, and use SectionAssignment to assign cross-sectional properties. Composite materials and honeycomb sandwiches need to define the ply stacking direction, and their cross-sectional property databases contain the ply direction and thickness of each ply.

[0114] Step 7: Assemble the honeycomb sandwich structure and the reinforcement ribs according to axisymmetry;

[0115] Specifically, step 7 includes the following steps:

[0116] 7.1 Implement the component rotation instruction through the rotate function, define the rotation object and the rotation angle through the instanceList function;

[0117] 7.2 The translation instruction of the component is implemented through the translate function, and the vector function defines the translation vector, which is defined by custom parameters;

[0118] Step 8: According to the damage location information, the patch and glue layer are assembled in the damaged area through functions such as rotate and translate. The position relationship of each component is as follows: Figure 4 As shown, this invention can quickly assemble multiple components to corresponding positions;

[0119] Step 9: Create a Buckle analysis step using the BuckleStep function, and set the buckling mode to 1st order;

[0120] Step 10: Define boundary conditions and loads. Along the axial direction of the stiffener, one end is fixed and the other sides are free. Apply a 1N lateral compression load at the other end of the fixed end.

[0121] Specifically, step 10 includes the following steps:

[0122] 10.1 Use the ReferencePoints function to establish reference points at the fixed end and the loading end, and use custom parameters to locate the reference point positions;

[0123] 10.2 Set the reference point to a set through the Set function;

[0124] 10.3 Use the Coupling function to couple the two reference points to the fixed end and the loading end respectively, use the side1Face function to select the coupling surface, and use the getByBoundingBox function to locate the coordinates of the coupling surface, so as to achieve the replacement of the reference point with the entire coupling surface;

[0125] Step 11: Set the contact relationship, all are binding contacts;

[0126] Specifically, step 11 includes the following steps:

[0127] 11.1 Use the Tie function to bind the contact surfaces of each component and the instances function to select the component;

[0128] 11.2 Use findAt function to locate the contact surface, master and slave functions to determine the master and slave surfaces, and the order of master surface selection is: composite material > honeycomb interlayer > adhesive layer;

[0129] 11.3 Use the ContactProperty function to build the overall contact relationship, and the appendInSTEP function to import the contact relationship into the finite element calculation, set the overall hard contact, and prevent the mesh penetration phenomenon during the calculation;

[0130] Step 12: Divide the grid into corresponding sizes according to the grid size parameters;

[0131] Specifically, step 12 includes the following steps:

[0132] 12.1 In order to avoid grid distortion caused by arranging the number of seeds to divide the grid, the grid size is determined by the seedPart function, and the grid in the damaged area is locally encrypted;

[0133] 12.2 Determine the mesh type through the setElementtype function and the setMeshControls function. The mesh type of the composite panel and the honeycomb sandwich is C3D8R, swept mesh, and the mesh type of the glue layer is COH3D8, swept mesh. The distortion of the mesh is controlled through the distortionControl function, and the elemDeletion function controls the element deletion.

[0134] 12.3 Define the stacking direction through the assignStackDirection function and locate the top plane position of the stack through the findAt function to ensure that the stacking direction of the composite material and the honeycomb sandwich is correct;

[0135] Step 13: Calculate the Buckle analysis step and extract the first-order buckling mode from the result file, which is applied as the initial defect to the subsequent Dynamic explicit analysis.

[0136] Specifically, step 13 includes the following steps:

[0137] 13.1 Use the custom function GetBlockPosition to locate the pointer to the relevant position in the inp file, the keywordBlock function to edit keywords, and the insert function to insert the corresponding code ("""*NODE FILE, GLOBAL=YES U""") to realize the buckling mode extraction function;

[0138] 13.2 First calculate the Buckle analysis step through the waitForCompletion function and extract the first-order buckling mode in the result file;

[0139] Step 14: Create a Dynamic explicit analysis step, apply a custom displacement load, add an initial defect, and calculate the lateral compression limit load of the model;

[0140] Specifically, step 14 includes the following steps:

[0141] 14.1 Create an explicit dynamics analysis step through the ExplicitDynamicsStep function, in which the history output variables and field output variables are defined through the HistoryOutputRequest function and the fieldOutputRequests function respectively;

[0142] 14.2 Define the displacement load through the DisplacementBC function, define the assignment curve through the SmoothStepAmplitude function, and apply the amplitude curve to the displacement load to improve the stability of the results;

[0143] 14.3 Use the custom function GetBlockPosition to locate the pointer to the relevant position of the inp file, insert the code (""'*IMPERFECTION,FILE='+self.buckle_name+',STEP=1\n''1,0.002\n'"") to import the buckling mode extracted in the Buckle analysis step. The self.buckle_name in the code is the working name of the Buckle analysis step;

[0144] 14.4 Import the user-defined subroutine through the function userSubroutine, introduce the stiffness degradation criteria of each material (the composite panel is the Hashin failure criterion, and the honeycomb sandwich is the equivalent damage criterion), and calculate the ultimate load and failure mode of the finite element model under lateral compression load. Some calculation results are shown in Figure 14.4. Figure 5 As shown, this invention can quickly obtain simulation results such as the buckling mode of the mailbox metamodel and the damage cloud map of each component.

[0145] The present invention uses Python language to carry out secondary development of Abaqus. Compared with the traditional Abaqus modeling process, it saves several hours of modeling time and realizes the rapid modeling and analysis of complex finite element models. At the same time, the present invention has more parameters and the model is highly modifiable, which can realize parametric modeling and analysis of various working conditions. It can be used in conjunction with engineering tests to reduce costs, improve test efficiency, and better evaluate and verify the repair plan of multi-level sandwich beams.

[0146] Embodiment 2

[0147] An electronic device comprises a memory, a processor and a computer program stored in the memory and operable on the processor. When the processor executes the program, a parameterized modeling method for excavation and repair of a multi-level sandwich beam structure is implemented.

[0148] Embodiment 3

[0149] A computer-readable storage medium stores a computer program, which, when executed by a processor, implements a parameterized modeling method for patching and repairing a multi-level sandwich beam structure.

[0150] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A parametric modeling method for multi-level sandwich beam repair, characterized in that: The steps include: Step 1: Define the parameters required for the model; Step 2: Establish geometric models of various components of the multi-level sandwich beam repair structure, including the honeycomb sandwich structure model and the stiffener model. According to the damage location and damage information, remove the damaged areas of the motherboard and the sandwich. According to the damage information, create patch models, core replacement models and glue layer models that match the damaged areas. Step 3: Import the material parameters of each component and assign cross-sectional properties to each component; Step 4: Assemble the honeycomb sandwich structure and the stiffener structure by axisymmetric assembly, and assemble the multi-level sandwich beam structure and the repair patch, replacement core, and adhesive layer according to the damage information; Step 5: Divide the mesh, set the contact relationship, and apply the load; Step 6: Create a buckle analysis step to calculate the buckling mode of the model, import the dynamic explicit analysis step, and calculate the ultimate lateral compression load of the model.

2. A parametric modeling method for repairing a multi-level sandwich beam according to claim 1, characterized in that: In the step 2, constructing a honeycomb sandwich structure model includes: Use the Abaqus built-in function setPrimaryObject to enter the sketch interface and draw the sketch; The rectangle is constructed by the function rectangle, and its shape is the projection of the honeycomb sandwich structure on the sketch plane; The rectangle is stretched to different depths through the BasesolidExtrude function to construct the upper and lower panels and the honeycomb sandwich model of the honeycomb sandwich structure. Construct the hierarchical points of the upper and lower panels through the function DatumPointByoffset; The panel is layered using the function DatumCsyByThreePoints.

3. A parameterized modeling method for repairing a multi-level sandwich beam according to claim 1, characterized in that: In the step 2, constructing the reinforcement model includes: In the sketch, use the Line function to connect all the inflection points of the ribs to form a closed curve, and then stretch it to build a rib model; In the sketch, some inflection points of the stiffener are connected by the Line function to form a closed curve embedded in the stiffener sketch, and then the honeycomb sandwich model in the stiffener is constructed by stretching; The function OffsetFaces is used to offset different face sets of the stiffener to complete the stiffener layering.

4. A parametric modeling method for repairing a multi-level sandwich beam according to claim 1, characterized in that: In the step 2, removing the damaged area of ​​the motherboard and the interlayer according to the damage position and damage information includes: Determine the damage location and damage information based on the parameters; Enter the upper panel plane editing through the function MakeSketchTransform, and use the CutExtrude function to loft the panel and interlayer according to the damage location and damage information.

5. The parametric modeling method for repairing a multi-level sandwich beam according to claim 1, characterized in that: The step 3 comprises: Use the custom functions readlaminate, readadhesive, and readhoney to read the properties of composite materials, adhesive layers, and honeycomb sandwich materials stored in Excel, import them into Abaqus, and form the corresponding section properties; The cross-sectional properties of composite materials, adhesive layers, and honeycomb interlayers stored in Excel are read through the custom functions readply_sequence, readsec_adhesive, and readsec_honey to complete the cross-sectional property assignment.

6. A parameterized modeling method for repairing a multi-level sandwich beam according to claim 1, characterized in that: The step 4 comprises: The rotate function is used to implement the component's rotation instruction, and the instanceList function is used to define the rotation object and the rotation angle; The component translation instruction is implemented through the translate function, and the vector function defines the translation vector, which is defined by custom parameters; According to the damage location information, the patch, core replacement, and adhesive layer are assembled in the damaged area through functions such as rotate and translate.

7. A parametric modeling method for repairing multi-level sandwich beams according to claim 1, characterized in that: The step 5 comprises: Meshing includes: Determine the grid size through the seedPart function; Determine the mesh type through the setElementtype function and the setMeshControls function; Define the stacking direction through the assignStackDirection function; Setting up contact relationships includes: Bind the contact surfaces of components through the Tie function; The contact surface is located by the findAt function, and the master and slave surfaces are determined by the master and slave functions; Construct the overall contact relationship through the ContactProperty function; Applying loads includes defining boundary conditions and loads. Along the axial direction of the stiffener, one end is fixed and the other sides are free. At the other end of the fixed end, a 1N lateral compression load is applied, including: Use the ReferencePoints function to establish reference points at the fixed end and the loading end; Set the reference point as a set through the Set function; The two reference points are coupled to the fixed end and the loading end respectively through the Coupling function; The constraints on the fixed end and the application of force loads on the loading end are completed through the EncastreBC and ConcentratedForce functions.

8. The parametric modeling method for repairing a multi-level sandwich beam according to claim 1, characterized in that: The step 6 comprises: Use the custom function GetBlockPosition to locate the pointer to the relevant position in the inp file, and insert the corresponding code through the insert function to realize the buckling mode extraction function; First, calculate the Buckle analysis step through the waitForCompletion function and extract the first-order buckling mode in the result file; Create an explicit dynamics analysis step through the ExplicitDynamicsStep function, in which the history output variables and field output variables are defined through the HistoryOutputRequest function and the fieldOutputRequests function respectively; Define the displacement load through the DisplacementBC function, define the assignment curve through the SmoothStepAmplitude function, and apply the amplitude curve to the displacement load to improve the stability of the result; Use the custom function GetBlockPosition to locate the pointer to the relevant position of the inp file and introduce the buckling mode in the Buckle analysis step; The user-defined subroutine is imported through the function userSubroutine, and the stiffness degradation criteria of each material are introduced to calculate the compressive strength and failure mode of the finite element model under lateral compression load.

9. 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, a parametric modeling method for patching and repairing a multi-level sandwich beam is implemented as described in any one of claims 1-8.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that When the program is executed by a processor, a parametric modeling method for repairing a multi-level sandwich beam as described in any one of claims 1 to 8 is implemented.

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