A launch pad working condition analysis method, device and storage medium of a carrier rocket

Abstract

The application discloses a launch platform working condition analysis method and device and a storage medium, and belongs to the technical field of launch vehicle working condition analysis, comprising the following steps: classifying parts in a launch platform, formulating a modeling strategy according to part types, inputting part interface position information, modeling each part in the launch platform, generating interface nodes between each part, establishing a substructure model of a bottom support leg and a rocket body support leg, assembling a full model of the launch platform, establishing an elastic constraint, and analyzing a rocket body empty shell transfer working condition, a rocket body filling working condition and a rocket body ignition and launch platform separation working condition. The application can realize rapid working condition analysis of the launch platform under the premise of ensuring data precision.

Description

Technical Field

[0001] This invention relates to the field of launch vehicle operational condition analysis technology, and in particular to a launch vehicle launch pad operational condition analysis method, equipment, and storage medium. Background Technology

[0002] The launch platform is a ground support system that ensures the normal operation of the rocket body during the transportation, propellant loading, and launch phases. According to its function, it can be divided into structural subsystems, propellant loading and gas supply subsystems, and electrical and measurement subsystems. The structural subsystem is responsible for ensuring that the rocket body can effectively transmit force and ensure the safety of the platform structure when it is on the launch pad. The propellant loading and gas supply subsystem is responsible for pressurizing the propellant loading and related structures such as the tanks. The electrical and measurement system is responsible for powering the relevant products on the rocket and measuring the relevant parameters.

[0003] In daily practice, the existing technical solutions have been found to have the following problems: During its service life, the launch platform undergoes several typical operational conditions, including empty rocket shell transfer, rocket fueling, and rocket ignition and launch. The structural stress state varies significantly under different operational conditions. Manually modeling and analyzing each condition separately is not only inefficient but also makes it difficult to ensure the consistency of the model foundation, constraints, and analysis parameters.

[0004] Therefore, it is necessary to provide a new technical solution to solve the above problems. Summary of the Invention

[0005] To address the aforementioned technical problems, this application provides a method, equipment, and storage medium for analyzing the operational conditions of a launch pad, which enables rapid operational condition analysis of a launch pad while ensuring data accuracy.

[0006] A method for analyzing the operational conditions of a launch pad for a carrier rocket includes: S1. Classify the components in the launch platform and formulate modeling strategies according to the component types; S2. Input component interface location information; S3. Model each component in the launch platform and generate interface nodes between the components; S4. Establish substructure models of the bottom support legs and the arrow body support legs; S5. Perform full model assembly of the launch pad and establish elastic constraints; S6. Analyze the launch platform under the following conditions: empty rocket shell transfer, rocket fueling, and rocket ignition and departure from the platform.

[0007] Preferably, step S1 includes: The components in the launch platform are classified into support components, long and slender beam components, plate and shell connection components, structural connection components, and boundary and load interface components. Support components are constructed as solid elements, slender beam components as beam elements, plate and shell connection components as shell elements, and structural connection components and load interface components are constructed as reference points and Coupling constraints.

[0008] Preferably, step S2 includes: The interfaces are divided into the following locations: the connection between the fixed leg and the lower platform, the connection between the upper platform and the rocket body leg, the connection between the lower platform and the umbilical tower, the connection between the umbilical tower and the umbilical swing arm, as well as the lower surface of the fixed leg and the upper surface of the rocket body leg. The connections between the fixed outriggers and the lower platform, the connections between the upper platform and the rocket body outriggers, the connections between the lower platform and the umbilical tower, the lower surface of the fixed outriggers, and the upper surface of the rocket body outriggers are named and the position coordinates of each connection point are set.

[0009] Preferably, step S3 includes: S31. Establish the upper and lower platform models: In the 3D modeling software, remove chamfers, small holes, bolts, and bolt holes from the upper and lower platforms that have little impact on the analysis, and extract the mid-surface of the platform structure as the feature surface of the platform geometry. The generated feature surface is divided into a surface mesh, and the thickness is assigned to the element containing the steel plate and the element containing the flange plate according to the actual thickness. For steel plates with welded relationships, common node constraints are used; for steel plates with flange constraints, ideal rigid constraints are used. Establish node interfaces with the bottom outriggers, rocket body outriggers, and umbilical tower; The generated model is checked, and the correct model is exported as the final upper and lower platform model; S32. Establish a single bottom support leg model: Considering only the length and diameter of the threaded rod, retaining the vertical ribs of the bottom support leg, and deleting the rest of the structure, the geometry of the bottom support leg is cleaned up; The bottom support leg is meshed using 3D solid elements, and material properties and element section properties are assigned to the bottom support leg. Establish interface nodes with the lower platform and the ground; The generated model is checked, and the correct model is exported as the final bottom support model; S33. Establish a single arrow body support leg model: Remove fillets, small holes, bolts, and bolt holes that have little impact on simulation analysis, and retain the main load-bearing structure of the rocket body's outriggers; The main load-bearing structure of the rocket's outriggers is divided into 3D meshes, and material properties and element section properties are assigned to it. Establish interface nodes with the upper platform and external loads; The generated model is checked, and the correct model is exported as the final rocket body and leg model. S34. Establish the model of the umbilical cord tower and umbilical cord pendulum: In the 3D modeling software, chamfers, small holes, bolts, bolt holes, and non-load-bearing structures that have little impact on the analysis of the umbilical tower are removed, and the mid-surface of the umbilical tower structure is extracted as the geometric feature surface. The generated geometric features are divided into surface meshes, and the elements containing the steel plate are assigned thickness and element cross-sectional properties according to the actual thickness. Extract the endpoint coordinates of each link of the umbilical pendulum and establish lines between the endpoint coordinates as the geometric feature lines of the umbilical pendulum. The generated geometric feature lines are divided into beam elements, and section properties, material properties, and element properties are assigned according to the actual cross-sectional geometry. Constrain the corresponding nodes between the umbilical tower and the umbilical pendulum according to the ideal rigid body type; Establish the interface node between the umbilical tower and the lower platform; The generated model is checked, and the correct model is exported as the final umbilical tower and umbilical pendulum model.

[0010] Preferably, step S5 includes: S51. Import the upper and lower platforms, umbilical tower, bottom support legs, and rocket body support legs according to the number of parts. S52. Perform translation and rotation operations on the parts according to their actual positional relationships; S53. Based on interface nodes, set elastic constraints between components.

[0011] Preferably, in step S53, the elastic constraints between components include the elastic constraints between the lower platform and the bottom support leg, the elastic constraints between the upper platform and the arrow support leg, and the elastic constraints between the lower platform and the umbilical tower.

[0012] Preferably, step S6 includes: Analysis of the transport of empty rocket casings: Loads are applied at the load interface points of the rocket body outriggers and distributed evenly to each load interface node of the rocket body outriggers. Static analysis is then used for analysis. Analysis of rocket body injection: Loads are applied at the load interface points of the rocket body outriggers and distributed evenly to each load interface node of the rocket body outriggers. Static analysis is then used for analysis. Analysis of the dynamic response of the rocket body after ignition and departure from the launch pad: Loads are applied at the load interface points of the rocket body outriggers and distributed evenly to each load interface node of the rocket body outriggers. Static analysis is then used for analysis. Based on the analysis results, without applying any load, the free response of the platform after the rocket body leaves the platform is analyzed using the modal superposition method.

[0013] According to another aspect of this application, a computing device is also provided, comprising: a processor and a memory storing a computer program, wherein the computer program, when executed by the processor, performs the aforementioned launch pad condition analysis method.

[0014] According to another aspect of this application, a computer-readable storage medium is also provided, on which computer instructions are stored, which, when executed on a computer, cause the computer to perform the aforementioned launch pad condition analysis method.

[0015] Compared with the prior art, this application has at least the following beneficial effects: 1. This invention enables rapid operational analysis of launch pads while ensuring data accuracy.

[0016] 2. Based on a unified finite element model, this invention establishes corresponding analysis processes for different typical working conditions, which can realize the standardization, process-orientation and automation of static analysis of launch platforms under multiple working conditions.

[0017] 3. This invention integrates the various substructure models into a complete launch platform assembly-level finite element model, solving the problems of automatic assembly of multiple substructure models and generation of overall analysis models. Attached Figure Description

[0018] The following sections will describe some specific embodiments of the invention in detail by way of example and not limitation, with reference to the accompanying drawings. The same reference numerals in the drawings denote the same or similar parts or portions. Those skilled in the art should understand that these drawings are not necessarily drawn to scale. In the drawings: Figure 1 This is a schematic diagram of the overall process of the present invention. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions of this application will be clearly and completely described below in conjunction with specific embodiments and corresponding drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0020] like Figure 1 As shown, a method for analyzing the operational conditions of a launch pad for a carrier rocket includes: S1. Classify the components in the launch platform and formulate modeling strategies according to the component types.

[0021] A typical launch pad structure for a carrier rocket includes: fixed legs, upper and lower platforms, rocket body legs, umbilical tower, and umbilical swing arm.

[0022] The components in the launch platform are divided into support components, slender beam components, plate and shell connection components, structural connection components, and boundary and load interface components.

[0023] Among them, support components are constructed as solid elements, slender beam components are constructed as beam elements, plate and shell connection components are constructed as shell elements, and structural connection components and load interface components are constructed as reference points and Coupling constraints.

[0024] Component Classification and Modeling Strategy Table in Launch Platform

[0025] S2. Input component interface location information.

[0026] According to their location, the interfaces can be divided into: the connection between the fixed support leg and the lower platform, the connection between the upper platform and the rocket body support leg, the connection between the upper platform and the umbilical tower, and the connection between the umbilical tower and the umbilical swing arm.

[0027] There are 8 connection points between the fixed support legs and the lower platform, named A1, A2, ..., A8. Each connection point contains three coordinate components.

[0028] There are four connection points between the upper platform and the rocket's legs, named B1, B2, B3, and B4. Each connection point contains three coordinate components.

[0029] There is a single connection point between the lower platform and the umbilical tower, named C1. Each connection point contains three coordinate components.

[0030] There are 8 fixed points on the lower surface of the outrigger, named D1, D2, ..., D8. Each connection point contains three coordinate components.

[0031] There are four connection points on the upper surface of the rocket's outriggers, named E1, E2, E3, and E4. Each connection point contains three coordinate components.

[0032] S3. Model each component in the launch platform and generate interface nodes between the components.

[0033] 31. Establish the upper and lower platform models.

[0034] Geometry cleanup of the upper and lower platforms. In the 3D modeling software, remove chamfers, small holes, bolts, and bolt holes from the upper and lower platforms that have little impact on the analysis. Then, extract the mid-surface of the platform structure as the feature surface of the platform geometry. After extracting the feature surface, extend the mid-surfaces corresponding to the welded steel plates in the original structure. This is to ensure that the mesh at the welded joints has a common node transition when meshing.

[0035] Mesh generation and element attribute assignment. Surface meshes are generated for the generated feature faces, with the mesh type being S4R. Thickness is assigned to the elements containing the steel plate and the flange plate according to their actual thickness, along with material properties such as density of 7850 kg / m^3, elastic modulus of 210 GPa, and Poisson's ratio of 0.3. Simultaneously, the element section attribute is assigned as "SHELLSECTION".

[0036] Constraint relationships are established. Steel plates with welding relationships naturally generate common node constraints, while steel plates with flange constraints are subject to ideal rigid constraints.

[0037] Establish node interfaces with the bottom outriggers, rocket body outriggers, and umbilical tower. Search for nodes near each interface coordinate in the following order: fixed outrigger - lower platform (A1-A8), upper platform - rocket body outriggers (B1-B4), lower platform - umbilical tower C1. Couple all nodes within the search range to the central reference point as interfaces for external load transfer. The naming convention for interface nodes is: abbreviation of the part where the interface is located_abbreviation of the connected component_serial number. For example: GDZT_XTT_1, GDZT_XTT_2, ..., GDZT_XTT_8.

[0038] The generated model is checked, and the correct model is exported as the final upper and lower platform model.

[0039] 32. Create a single bottom support leg model.

[0040] Bottom support leg geometry cleanup. The main load-bearing structure of the bottom support leg of the launch platform is a stepped hollow shaft with an adjustable threaded rod inside, used to adjust the distance between the lower platform and the ground. When modeling, only the length and diameter of the threaded rod are considered, the vertical ribs of the bottom support leg are retained, and the rest of the structure is deleted.

[0041] Mesh generation and element attribute assignment. The bottom support leg is meshed using 3D solid elements (C3D8 type). Material properties are then assigned to the bottom support leg, with a density of 7850 kg / m³. 3 The elastic modulus is 210 GPa and the Poisson's ratio is 0.3. At the same time, the element section property is assigned the name "SOLIDSECTION".

[0042] Establish interface nodes with the lower platform and the ground. Assuming the sequence number of the established bottom support leg is 1, search for nodes within the search range of coordinates A1 and D1, and couple the node group to the central reference point. For node interfaces that set external boundary conditions and loads, the naming rule for interface nodes is: part name_sequence number, for example: GDZT_1.

[0043] The generated model is checked, and the correct model is exported as the final bottom support model.

[0044] S33. Establish a single rocket body support leg model.

[0045] Geometry cleanup of the rocket body outrigger model. Remove fillets, small holes, bolts, and bolt holes that have little impact on simulation analysis, while retaining the main load-bearing structure of the rocket body outriggers.

[0046] Mesh generation and element attribute assignment: A 3D mesh was generated for the main load-bearing structure of the rocket's outriggers, using C3D8 element type. Material properties were assigned, with a density of 7850 kg / m³. 3 The elastic modulus is 210 GPa and the Poisson's ratio is 0.3. At the same time, the element section property is assigned the name "SOLIDSECTION".

[0047] Establish interface nodes with the upper platform and external loads. Assuming the serial number of the established rocket body leg is 1, search for nodes within the B1 and E1 coordinate search range, and couple the node group to the central reference point. The interface node name with the upper platform is: JTZT_STT_1, and the interface node name with the external load is: JTZT_1.

[0048] The generated model is checked, and the correct model is exported as the final rocket body and leg model.

[0049] S34. Establish models of the umbilical cord tower and umbilical cord pendulum.

[0050] Geometry cleanup of the umbilical tower. The umbilical tower structure is a closed box beam. In the 3D modeling software, chamfers, small holes, bolts, bolt holes, and non-load-bearing structures with little impact on the analysis were deleted from the umbilical tower structure. Then, the mid-surface of the umbilical tower structure was extracted as the geometric feature surface. After the feature surface was extracted, the mid-surfaces corresponding to the steel plates with welded relationships in the original structure were extended. The purpose is to ensure that the mesh at the welded joints has a common node transition when meshing. The umbilical tower is meshed and its elements are assigned attributes. The generated feature faces are then meshed using the S4R mesh type. The elements containing the steel plate are assigned a thickness, e.g., 50 mm, based on their actual thickness, and material properties are assigned, e.g., a density of 7850 kg / m³. 3 The elastic modulus is 210 GPa and the Poisson's ratio is 0.3. At the same time, the element section property is assigned as "SHELLSECTION".

[0051] The geometry of the umbilical cord pendulum is cleaned up. The umbilical cord pendulum structure is a truss structure, with the members connected by welding. The endpoint coordinates of each member of the umbilical cord pendulum are extracted, and lines are established between the endpoint coordinates as the geometric feature lines of the umbilical cord pendulum.

[0052] Mesh the umbilical pendulum and assign element properties. Divide the generated geometric feature lines into beam elements and assign section properties and material properties based on the actual cross-sectional geometry, such as a density of 7850 kg / m³. 3 The elastic modulus is 210 GPa, the Poisson's ratio is 0.3, and the element property is assigned the name "BEAMSECTION".

[0053] Connect the umbilical tower and the umbilical pendulum. The corresponding nodes between the umbilical tower and the umbilical pendulum are constrained according to the ideal rigid body type.

[0054] Establish the interface node between the umbilical tower and the lower platform. Couple the nodes within the search range of coordinate point C1 to the central reference point and name them QDT_XTT.

[0055] The generated model is checked, and the correct model is exported as the final umbilical tower and umbilical pendulum model.

[0056] S4. Establish substructure models for the bottom support legs and the arrow body support legs.

[0057] Since the launch pad model has a large number of bottom legs and rocket body legs, a substructure approach is suitable for modeling. In substructure modeling, the interface nodes and nodes of interest established in step S3 are retained, and the substructure is output in the form of stiffness matrix, mass matrix, and retained nodes.

[0058] S5. Assemble the launch pad using a full model and establish elastic constraints.

[0059] S51. Import the upper and lower platforms, umbilical towers, bottom legs, and rocket body legs according to the number of components. For example: the number of upper and lower platforms is 1, the number of umbilical towers is 1, the number of bottom legs is 8, and the number of rocket body legs is 4. For components with a quantity of more than 1, new interface nodes should also be created.

[0060] S52. Perform translation and rotation operations on the parts according to their actual positional relationships.

[0061] S53. Based on interface nodes, set elastic constraints between components.

[0062] Establish elastic constraints between the lower platform and the bottom support leg. Extract the interface nodes between the lower platform and the bottom support leg, and between the bottom support leg and the lower platform, and match them sequentially, for example, XTT_DBZT_1 and DBZT_XTT_1. Establish spring constraints for the rotational degrees of freedom of these two nodes, and assign stiffness parameters XTT_DBZT_K1, XTT_DBZT_K2, and XTT_DBZT_K3. Establish ideal rigid constraints for the translational degrees of freedom. Set the same constraints for the remaining 7 interface nodes in the same way.

[0063] Establish elastic constraints between the upper platform and the rocket's outriggers. Extract the interface nodes between the upper platform and the rocket's outriggers, and the nodes between the rocket's outriggers and the upper platform interface, and match them sequentially, for example, STT_JTZT_1 and JTZT_STT_1. Establish spring constraints for the rotational degrees of freedom of these two nodes, and assign stiffness parameters STT_JTZT_K1, STT_JTZT_K2, and STT_JTZT_K3. Establish ideal rigid constraints for the translational degrees of freedom. Set the same constraints for the remaining three interface nodes using the same method.

[0064] Establish elastic constraints between the lower platform and the umbilical tower. Establish constraints on the interface nodes XTT_QDT and QDT_XTT between them. Establish spring constraints for the rotational degrees of freedom and assign spring stiffnesses XTT_QDT_K1, XTT_QDT_K2, and XTT_QDT_K3. Establish ideal rigid body constraints for the translational degrees of freedom.

[0065] S6. Analyze the launch platform under the following conditions: empty rocket shell transfer, rocket fueling, and rocket ignition and departure from the platform.

[0066] Analysis of the transport of the rocket's hollow shell. Loads are applied at the load interface points of the rocket's outriggers, including the weight of the hollow shell and the tail-end bending moment caused by wind loads. These loads are evenly distributed to each outrigger load interface node, and a static analysis method is used for analysis. The analysis includes: outputting Mises stress contour maps to determine the most critical locations of structural stress; outputting maximum principal stress contour maps and maximum principal stress values ​​for fatigue life calculation; and outputting displacement contour maps to determine whether the structural bearing stiffness meets the requirements.

[0067] Rocket body loading analysis. Loads are applied at the load interface points of the rocket's outriggers, including the tail-end bending moment caused by gravity and wind loads after loading. These loads are evenly distributed to each outrigger load interface node, and a static analysis method is used for analysis. The analysis includes: outputting Mises stress contour maps to determine the most critical stress locations in the structure; outputting maximum principal stress contour maps and maximum principal stress values ​​for fatigue life calculation; and outputting displacement contour maps to determine if the structural bearing stiffness meets requirements.

[0068] Dynamic response analysis of the rocket body after ignition and launch pad. Loads are applied at the load interface points of the rocket body's outriggers, evenly distributed to each outrigger load interface node, and analyzed using static analysis methods. The analysis includes: outputting the time-domain acceleration data of the nodes at the launch pad equipment storage locations, processing them into frequency spectrum curves and power spectral density curves, for use in the analysis of launch pad structural transfer characteristics and the mechanical environmental adaptability analysis of launch pad auxiliary structures.

[0069] Based on the analysis results, without applying any load, the free response of the platform after the rocket body leaves the platform is analyzed using the modal superposition method.

[0070] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0071] It should be noted that the terms "first," "second," etc., used in the specification, claims, and accompanying drawings of this application are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of this application described herein can be implemented in sequences other than those illustrated or described herein.

[0072] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for analyzing the operational conditions of a launch pad for a carrier rocket, characterized in that, include: S1. Classify the components in the launch platform and formulate modeling strategies according to the component types; S2. Input component interface location information; S3. Model each component in the launch platform and generate interface nodes between the components; S4. Establish substructure models of the bottom support legs and the arrow body support legs; S5. Perform full model assembly of the launch pad and establish elastic constraints; S6. Analyze the launch platform under the following conditions: empty rocket shell transfer, rocket fueling, and rocket ignition and departure from the platform.

2. The method for analyzing the operational conditions of a launch pad for a carrier rocket as described in claim 1, characterized in that, Step S1 includes: The components in the launch platform are classified into support components, long and slender beam components, plate and shell connection components, structural connection components, and boundary and load interface components. Support components are constructed as solid elements, slender beam components as beam elements, plate and shell connection components as shell elements, and structural connection components and load interface components are constructed as reference points and Coupling constraints.

3. The method for analyzing the operational conditions of a launch pad for a carrier rocket as described in claim 2, characterized in that, Step S2 includes: The interfaces are divided into the following locations: the connection between the fixed leg and the lower platform, the connection between the upper platform and the rocket body leg, the connection between the lower platform and the umbilical tower, the connection between the umbilical tower and the umbilical swing arm, as well as the lower surface of the fixed leg and the upper surface of the rocket body leg. The connections between the fixed outriggers and the lower platform, the connections between the upper platform and the rocket body outriggers, the connections between the lower platform and the umbilical tower, the lower surface of the fixed outriggers, and the upper surface of the rocket body outriggers are named and the position coordinates of each connection point are set.

4. The method for analyzing the operational conditions of a launch pad for a carrier rocket as described in claim 3, characterized in that, Step S3 includes: S31. Establish the upper and lower platform models: In the 3D modeling software, remove chamfers, small holes, bolts, and bolt holes from the upper and lower platforms that have little impact on the analysis, and extract the mid-surface of the platform structure as the feature surface of the platform geometry. The generated feature surface is divided into a surface mesh, and the thickness is assigned to the element containing the steel plate and the element containing the flange plate according to the actual thickness. For steel plates with welded relationships, common node constraints are used; for steel plates with flange constraints, ideal rigid constraints are used. Establish node interfaces with the bottom outriggers, rocket body outriggers, and umbilical tower; The generated model is checked, and the correct model is exported as the final upper and lower platform model; S32. Establish a single bottom support leg model: Considering only the length and diameter of the threaded rod, retaining the vertical ribs of the bottom support leg, and deleting the rest of the structure, the geometry of the bottom support leg is cleaned up; The bottom support leg is meshed using 3D solid elements, and material properties and element section properties are assigned to the bottom support leg. Establish interface nodes with the lower platform and the ground; The generated model is checked, and the correct model is exported as the final bottom support model; S33. Establish a single arrow body support leg model: Remove fillets, small holes, bolts, and bolt holes that have little impact on simulation analysis, and retain the main load-bearing structure of the rocket body's outriggers; The main load-bearing structure of the rocket's outriggers is divided into 3D meshes, and material properties and element section properties are assigned to it. Establish interface nodes with the upper platform and external loads; The generated model is checked, and the correct model is exported as the final rocket body and leg model. S34. Establish the model of the umbilical cord tower and umbilical cord pendulum: In the 3D modeling software, chamfers, small holes, bolts, bolt holes, and non-load-bearing structures that have little impact on the analysis of the umbilical tower are removed, and the mid-surface of the umbilical tower structure is extracted as the geometric feature surface. The generated geometric features are divided into surface meshes, and the elements containing the steel plate are assigned thickness and element cross-sectional properties according to the actual thickness. Extract the endpoint coordinates of each link of the umbilical pendulum and establish lines between the endpoint coordinates as the geometric feature lines of the umbilical pendulum. The generated geometric feature lines are divided into beam elements, and section properties, material properties, and element properties are assigned according to the actual cross-sectional geometry. Constrain the corresponding nodes between the umbilical tower and the umbilical pendulum according to the ideal rigid body type; Establish the interface node between the umbilical tower and the lower platform; The generated model is checked, and the correct model is exported as the final umbilical tower and umbilical pendulum model.

5. The method for analyzing the operational conditions of a launch pad for a carrier rocket as described in claim 4, characterized in that, Step S5 includes: S51. Import the upper and lower platforms, umbilical tower, bottom support legs, and rocket body support legs according to the number of parts. S52. Perform translation and rotation operations on the parts according to their actual positional relationships; S53. Based on interface nodes, set elastic constraints between components.

6. The method for analyzing the operational conditions of a launch pad for a carrier rocket as described in claim 5, characterized in that, In step S53, the elastic constraints between components include the elastic constraints between the lower platform and the bottom support leg, the elastic constraints between the upper platform and the arrow support leg, and the elastic constraints between the lower platform and the umbilical tower.

7. The method for analyzing the operational conditions of a launch pad for a carrier rocket as described in claim 6, characterized in that, Step S6 includes: Analysis of the transport of empty rocket casings: Loads are applied at the load interface points of the rocket body outriggers and distributed evenly to each load interface node of the rocket body outriggers. Static analysis is then used for analysis. Analysis of rocket body injection: Loads are applied at the load interface points of the rocket body outriggers and distributed evenly to each load interface node of the rocket body outriggers. Static analysis is then used for analysis. Analysis of the dynamic response of the rocket body after ignition and departure from the launch pad: Loads are applied at the load interface points of the rocket body outriggers and distributed evenly to each load interface node of the rocket body outriggers. Static analysis is then used for analysis. Based on the analysis results, without applying any load, the free response of the platform after the rocket body leaves the platform is analyzed using the modal superposition method.

8. A computing device, characterized in that, include: The processor and the memory storing a computer program, wherein the computer program, when executed by the processor, performs the launch pad condition analysis method as described in any one of claims 1 to 7.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer instructions that, when executed on a computer, cause the computer to perform the launch pad condition analysis method as described in any one of claims 1 to 7.

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