Automatic generation method and device for structural dynamic model of carrier rocket, and storage medium

Abstract

The invention discloses an automatic generation method and device for a dynamic model of a carrier rocket structure and a storage medium, and belongs to the technical field of carrier rocket model generation, and the method comprises the steps: describing the carrier rocket structure through carrier rocket parameters; reading and storing the edited parameter information of the carrier rocket; and automatically generating a carrier rocket structure dynamic model by using the stored carrier rocket parameters. According to the method, the carrier rocket is subjected to height parameterization description, the method can be combined with a secondary development function of commercial finite element software, rapid and automatic generation and rapid analysis of the model are achieved, and the method has the advantage of being easy to debug.

Description

Technical Field

[0001] The present invention relates to the technical field of launch vehicle model generation, and in particular to a launch vehicle structure dynamics model automatic generation method, device and storage medium. Background Art

[0002] The launch vehicle structural dynamics model plays a connecting role in the development process of launch vehicle products. Designers build the launch vehicle structural dynamics model and perform modal analysis based on the aerodynamic shape, mass distribution, structural form and other data in the initial data of the launch vehicle. The results of the modal analysis are used for: static and dynamic load calculation of the launch vehicle, elastic vibration control design of the launch vehicle, satellite-rocket coupling analysis and prediction of the modal test results of the launch vehicle.

[0003] Traditional launch vehicle structural dynamics modeling often requires designers to manually build a full rocket dynamics model. The problem with this method is that manual modeling takes a lot of time and is prone to errors.

[0004] In addition, when the initial data of the launch vehicle changes, designers need to model the changed parts. When the changes are large, they even need to remodel the entire rocket.

[0005] Therefore, the existing launch vehicle structural dynamics modeling is not suitable for the needs of rapid analysis, rapid iteration, and rapid development of products in the commercial aerospace era. In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the invention

[0006] In order to solve the above technical problems, the present application provides a method, device and storage medium for automatically generating a launch vehicle structural dynamics model. By highly parameterizing the launch vehicle and combining the secondary development function of commercial finite element software, the model can be quickly and automatically generated and analyzed, and it is easy to check for errors.

[0007] A method for automatically generating a launch vehicle structural dynamics model, comprising:

[0008] The launch vehicle structure is described by the launch vehicle parameters;

[0009] Read and save the edited launch vehicle parameter information;

[0010] Automatically generate the launch vehicle structural dynamics model using the saved launch vehicle parameters;

[0011] Among them, the launch vehicle parameters include launch vehicle site information, launch vehicle mass information, launch vehicle beam section information, launch vehicle rigid constraint information and launch vehicle elastic constraint information.

[0012] Preferably, the launch vehicle site information includes the number of sites, the geometric coordinates of the sites, the section number where the sites are located, and the site number of the section where the sites are located;

[0013] The launch vehicle station mass information includes station mass and station inertia;

[0014] The carrier rocket beam cross-section information includes the number of cross-sections, the beam front end face radius, the beam front end face thickness, the beam rear end face radius, the beam rear end face thickness, the beam section number and the beam section number;

[0015] The launch vehicle rigid constraint information includes: the number of rigid constraints, the site number of the first rigid constraint point, the site number of the second rigid constraint point and the rigid constraint type;

[0016] The launch vehicle elastic constraint information includes: the number of elastic constraints, the site number of the first elastic constraint point, the site number of the second elastic constraint point and the six-direction stiffness coefficients of the elastic constraints.

[0017] Preferably, the description of the launch vehicle structure by launch vehicle parameters includes:

[0018] Divide the solid-propellant launch vehicle into different sections and assign a section number to each section;

[0019] Each section is divided into different stations, and the stations are numbered in the section according to the order of the stations, and line segments are formed between the stations;

[0020] The mass and inertia of the segment when divided into segments are equivalent to the mass point as the site mass and site inertia;

[0021] The surface where the front end point of the line segment is located is taken as the front end surface, and the surface where the rear end point of the line segment is located is taken as the rear end surface. Both the front and rear end surfaces describe the cross-sectional information of the launch vehicle beam through the cross-sectional radius and thickness;

[0022] The directions of the three degrees of freedom of translation between stations and the degree of freedom of rotation around the arrow axis are described as the rigid constraint information of the launch vehicle. Different types of rigid constraint type codes are set according to the connection status of different sections.

[0023] The directions of the rotational freedom between stations around the lateral and transverse axes of the rocket body are described as the elastic constraint information of the launch vehicle. Different types of elastic constraint type codes are set according to the connection status of different sections.

[0024] Preferably, the method of automatically generating a launch vehicle structural dynamics model by using the stored launch vehicle parameters comprises:

[0025] Create corresponding parts for each section of the launch vehicle, generate sites in the corresponding parts according to the site coordinates, connect the sites in sequence to generate lines, and create a collection of sites and lines;

[0026] Add mass points containing mass and inertia to the generated sites;

[0027] Create beam sections of two different types: front and rear beam faces, assign beam sections to generated lines, assign beam section directions, and set the elastic modulus and Poisson's ratio of beam sections;

[0028] Assemble the generated parts according to the connection relationship to form a launch vehicle assembly;

[0029] Establish rigid connection constraints on the formed launch vehicle assembly;

[0030] Establish elastic connection constraints for the formed launch vehicle assembly.

[0031] Preferably, when the launch vehicle structure is described by launch vehicle parameters, corresponding parameter editing tables are generated for the launch vehicle site information, launch vehicle mass information, launch vehicle beam section information, launch vehicle rigid constraint information and launch vehicle elastic constraint information.

[0032] According to another aspect of the present application, a computing device is also provided, including: a processor and a memory storing a computer program, wherein when the computer program is executed by the processor, the method for automatically generating a launch vehicle structural dynamics model is executed.

[0033] According to another aspect of the present application, a computer-readable storage medium is also provided, on which computer instructions are stored. When the instructions are executed on a computer, the computer executes the method for automatically generating a launch vehicle structural dynamics model.

[0034] Compared with the prior art, this application has at least the following beneficial effects:

[0035] 1. The method for automatically generating a launch vehicle structural dynamics model of the present invention can avoid the time-consuming and error-prone problems of traditional manual modeling, and realize the automated modeling of the launch vehicle structural dynamics model.

[0036] 2. The method for automatically generating a launch vehicle structural dynamics model of the present invention can check whether the parameter input is correct through a parameter editing table, thereby avoiding the disadvantage that the traditional manual parameter input is prone to errors.

[0037] 3. The method for automatically generating a launch vehicle structural dynamics model of the present invention can be combined with the secondary development function of commercial finite element software. When the input parameters of the launch vehicle are changed, they can be directly modified through the parameter editing table, and the launch vehicle structural dynamics model can be automatically regenerated according to the corresponding steps, thereby improving the efficiency of model modification. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale. In the accompanying drawings:

[0039] Figure 1 It is a schematic diagram of the overall process of the method for automatically generating a launch vehicle structure dynamics model of the present invention;

[0040] Figure 2 It is a schematic diagram of the station and line segment after a certain section is divided into stations in the automatic generation method of the launch vehicle structure dynamics model;

[0041] Figure 3 The figure is a geometrical schematic diagram of the beam ring cross section in the method for automatically generating the structural dynamics model of a launch vehicle of the present invention. DETAILED DESCRIPTION

[0042] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0043] like Figure 1 As shown, a method for automatically generating a launch vehicle structural dynamics model comprises the following steps:

[0044] Step S1, describing the launch vehicle structure through launch vehicle parameters.

[0045] Among them, the launch vehicle parameters include launch vehicle site information, launch vehicle mass information, launch vehicle beam section information, launch vehicle rigid constraint information and launch vehicle elastic constraint information.

[0046] Specifically, the launch vehicle site information includes the number of sites, the geometric coordinates of the sites, the section number of the sites, and the site number of the section where the sites are located. The launch vehicle site mass information includes the site mass and the site inertia. The launch vehicle beam section information includes the number of sections, the radius of the front end face of the beam, the thickness of the front end face of the beam, the radius of the rear end face of the beam, the thickness of the rear end face of the beam, the section number of the beam, and the beam number of the section where the beam is located. The launch vehicle rigid constraint information includes: the number of rigid constraints, the site number of the first rigid constraint point, the site number of the second rigid constraint point, and the rigid constraint type. The launch vehicle elastic constraint information includes: the number of elastic constraints, the site number of the first elastic constraint point, the site number of the second elastic constraint point, and the six-direction stiffness coefficient of the elastic constraint.

[0047] At the same time, when the launch vehicle structure is described by the launch vehicle parameters, the launch vehicle site information, launch vehicle mass information, launch vehicle beam section information, launch vehicle rigid constraint information and launch vehicle elastic constraint information all generate corresponding parameter editing tables.

[0048] In this embodiment, step S1 includes the following sub-steps:

[0049] Step 1.1, divide the launch vehicle into different sections. For example, taking a certain type of rocket as an example, divide it into fairing, instrument cabin, core second stage, interstage, core first stage and tail stage, and assign a section number to each section:

[0050] (1) Fairing: No. 1;

[0051] (2) Instrument cabin - No. 2;

[0052] (3) Core level 2 - number 3;

[0053] (4) Interstage section - number 4;

[0054] (5) Core level 1 - number 5;

[0055] (6) Last paragraph: number 6.

[0056] Furthermore, according to the structural characteristics of each launch vehicle, the locations of the station division include: the upper and lower end surfaces of the structure, the junction between the cone section and the column section of the structure, the rigidity mutation of the section wall, the slope of the vibration mode of interest, the structural support point, the branch structure connection, the binding connection, and the inside of the longer structure. Among them, the longer structure includes the first-stage oxygen tank and the fuel tank, and its structural station location is located at the dangerous working condition liquid level position.

[0057] The basis for site division in this implementation is as follows:

[0058] (1) For shorter structures such as the separation ring, front and rear short shells of the tank, and tail section, two stations can be directly set at the upper and lower end surfaces of the structure, and no stations are required inside;

[0059] (2) For longer structures such as primary oxygen tanks and fuel tanks, it is necessary to divide the internal stations, and the internal stations of the structure are located at the liquid level of the dangerous working conditions;

[0060] (3) For the fairing, a station needs to be set up at the junction of the structural cone and column sections;

[0061] (4) Stations need to be set up at the places where the rigidity of the segment wall suddenly changes;

[0062] (5) Stations should be set up at places where the inertial group, rate gyro, engine center of gravity and other places where the vibration mode slope is concerned;

[0063] (6) Stations need to be set up at structural support points and other places where concentrated force needs to be output;

[0064] (7) Sites are also required at branch structure connections, such as satellite adapter connections, engine connections, and tank front and rear short shell locations;

[0065] (8) For bundled rockets, stations need to be set up at the bundled connection points.

[0066] Different stations are divided into each section. The geometric information of each station is described by the (X, Y, Z) coordinates of its spatial position. The stations are numbered in the section according to the order of stations. For example:

[0067] (1) Station No. 1 of a section - number 1;

[0068] (2) Station No. 2 of a certain section - number 2;

[0069] (3) Station No. 3 of a certain section - number 3;

[0070] (4) Station No. 4 of a certain section - number 4;

[0071] (5) Site No. 5 of a certain section - number 5.

[0072] It should be noted that the above-mentioned section refers to any one of the fairing, instrument cabin, core stage 2, interstage section, core stage 1 and tail section.

[0073] At this time, after the launch vehicle segments are divided by the stations, line segments will be formed between the stations, such as Figure 2 shown.

[0074] For example:

[0075] (1) The line segment between station 1 and station 2 in a certain section - line segment 1;

[0076] (2) Line segment 2 between station 2 and station 3 in a certain section;

[0077] (3) Line segment 3 between station 3 and station 4 in a certain section;

[0078] (4) A selected section between station 4 and station 5 in a certain section - line segment 4;

[0079] (5) The line segment between station 5 and station 6 of a certain section - line segment 5.

[0080] The above information is combined into a launch vehicle site information table, as shown in Table 1.

[0081] Table 1 Launch vehicle station serial number information table

[0082]

[0083] Step 1.2, edit the launch vehicle site mass information: the site mass and inertia are the results of the mass and inertia of a certain section being equivalent to a particle when divided into sections, including: site mass, site inertia in three directions, forming the launch vehicle site mass information as shown in Table 2.

[0084] Table 2 Launch vehicle site mass information table

[0085] Site number Site quality <![CDATA[Site inertia I xx > <![CDATA[Station inertia I yy > <![CDATA[Station inertia I zz > 1 <![CDATA[m1]]> <![CDATA[I xx1 ]]> <![CDATA[I yy1 ]]> <![CDATA[I zz1 ]]> 2 <![CDATA[m2]]> <![CDATA[I xx2 ]]> <![CDATA[I yy2 ]]> <![CDATA[I zz2 ]]> 3 <![CDATA[m3]]> <![CDATA[I xx3 ]]> <![CDATA[I yy3 ]]> <![CDATA[I zz3 ]]> 4 <![CDATA[m4]]> <![CDATA[I xx4 ]]> <![CDATA[I yy4 ]]> <![CDATA[I zz4 ]]> …… …… …… …… ……

[0086] Step 1.3, edit the cross-section information of the launch vehicle beam: Each line segment formed in the above process is composed of a front end point and a rear end point. Without special circumstances, the line segment close to the theoretical vertex of the rocket body is considered to be the front end point, and the line segment far from the theoretical vertex of the rocket body is considered to be the rear end point. The surface where the front end point is located is the front end surface, and the surface where the rear end point is located is the rear end surface. The front and rear end surfaces are used to describe the cross-section information of the launch vehicle beam through the cross-section radius and thickness. Each end surface is a circular cross section, and the description parameters of the circular cross section include the cross-section radius R and thickness δ, such as Figure 3 shown.

[0087] According to the substation sequence, the line segment is assigned a number in the section to which it belongs. The above information forms the launch vehicle beam cross-section information shown in Table 3.

[0088] Table 3 Launch vehicle beam cross-section information

[0089]

[0090] Step 1.4, edit the rigid constraint information of the launch vehicle: Rigid constraint means that certain degrees of freedom between stations are connected by rigidity. The rigid connection setting of the station is based on the actual connection status between the sections in the launch vehicle. For example, for the core stage section connection, it can be considered that the three translational degrees of freedom and the rotational degrees of freedom around the arrow axis between the stations are rigidly connected, while the rotational degrees of freedom around the lateral and lateral axes of the rocket body do not have a rigid connection state. According to the connection status of different sections, different types of rigid constraint type codes are set for the software to identify how to apply rigid constraints. The above information is summarized as the rigid constraint information of the launch vehicle shown in Table 4 below.

[0091] Typical launch vehicle rigid body constraint types and codes are as follows:

[0092] (1) Code 1: constrains the three translational degrees of freedom and axial rotational degrees of freedom between segments, releases the lateral and normal rotational degrees of freedom, and is mainly used for the connection between the rocket body and core stage structures;

[0093] (2) Code 2: constrains the three translational degrees of freedom between segments and releases the three rotational degrees of freedom, mainly used for ball-head and ball-socket connections in binding structures;

[0094] (3) Code 3: Constrains all six degrees of freedom between segments, mainly used for connections between welded structures.

[0095] Table 4 Launch vehicle rigid constraint information table

[0096]

[0097] Step 1.5, edit the elastic constraint information of the launch vehicle: Elastic constraint means that certain degrees of freedom between stations are connected by elasticity. The station elastic connection setting is based on the actual connection status between the sections in the launch vehicle, and sets different types of elastic constraint type codes for the software to identify how to apply elastic constraints. For example, for the core stage section connection, the rotational freedom direction between stations around the transverse and lateral axes of the rocket body can be considered as an elastic connection state, and the connection stiffness coefficient can be set arbitrarily. The directions of each degree of freedom are defined as follows:

[0098] (1) Direction 1: along the axial translation direction of the rocket body;

[0099] (2) Direction 2: along the lateral translation direction of the rocket body;

[0100] (3) Direction 3: along the lateral translation direction of the rocket body;

[0101] (4) 4th direction - the direction of rotation around the axial direction of the arrow body;

[0102] (5) 5 direction – the direction of lateral rotation around the arrow body;

[0103] (6)6 direction – the direction of lateral rotation around the arrow body;

[0104] The above information is summarized as the launch vehicle elastic constraint information shown in Table 5 below.

[0105] Table 5 Launch vehicle elastic constraint information

[0106]

[0107] Step S2: Read and save the edited launch vehicle parameter information.

[0108] When reading and saving the edited launch vehicle parameter information, the existing modeling software can be used, and it can also be combined with the secondary development function of commercial finite element software. When the launch vehicle input parameters are changed, they can be modified directly through the parameter editing table.

[0109] Step S3: using the saved launch vehicle parameters to automatically generate a launch vehicle structural dynamics model.

[0110] Specifically, in this embodiment, step S3 includes the following sub-steps:

[0111] Create corresponding parts for each section of the launch vehicle, generate sites in the corresponding parts according to the site coordinates, connect the sites in sequence to generate lines, and create a collection of sites and lines;

[0112] Add mass points containing mass and inertia to the generated sites;

[0113] Create beam sections of two different types: front and rear beam faces, assign beam sections to generated lines, assign beam section directions, and set the elastic modulus and Poisson's ratio of beam sections;

[0114] Assemble the generated parts according to the connection relationship to form a launch vehicle assembly;

[0115] Establish rigid connection constraints on the formed launch vehicle assembly;

[0116] Establish elastic connection constraints for the formed launch vehicle assembly.

[0117] Step 3.1: Create corresponding parts for each section of the launch vehicle and name each part. For example:

[0118] (1) Fairing - Part 1;

[0119] (2) Instrument cabin - Part 2;

[0120] (3) Core level 2 - Part 3;

[0121] (4) Interstage section - part 4;

[0122] (5) Core level 1 - Part 5;

[0123] (6) Tail section - Part 6;

[0124] Generate sites in the corresponding parts according to the site coordinates, connect the sites in sequence to generate lines, make all sites in each part on a straight line, and create a collection of sites and lines.

[0125] Generate sites in the corresponding parts according to the site coordinates and name the sites in the order of the sites.

[0126] For example:

[0127] (1) Fairing Site 1 - Part 1 Site 1;

[0128] (2) Core Level 2 Site 3 – Parts 3 Site 3;

[0129] (3) Tail section station 5 – Part 6 station 5.

[0130] In all parts, connect the stations in order to generate lines so that all stations in each part are on a straight line and name the line segments between stations:

[0131] (1) The line segment between fairing station 1 and station 2 - part 1 line segment 1;

[0132] (2) The line segment between core secondary site 3 and site 4 - part 3 line segment 3;

[0133] (3) The line segment between site 5 and site 6 in the tail section - part 6 line segment 5.

[0134] This creates a collection of sites and lines.

[0135] Step 3.2: Add a mass point to the site in step 3.1, including the mass and inertia of the point.

[0136] For example, the first station of the launch vehicle is fairing station 1. The collection name of the point is indexed through all serial numbers, and then the point is assigned a mass of 20kg and an inertia of 100kg·m2 in three directions.

[0137] Step 3.3: When creating beam sections, create beam sections of two different types: the front end face of the beam and the rear end face of the beam according to the dimensions of each part of the launch vehicle, the elastic modulus, and the Poisson's ratio. The beam sections are used to be assigned to the line segments generated in step 3.1.

[0138] For example: for the line segment between the first and second stations of the fairing, the radius of the front face of the beam corresponding to the line segment is 2m, the equivalent thickness is 10mm, the radius of the rear face section is 2m, and the equivalent thickness is 10mm. The front and rear face geometric parameters are assigned to the line segment 1 of part 1. After the beam section is assigned, the direction of the beam is assigned.

[0139] Set the elastic modulus and Poisson's ratio of the line segment, for example, Young's modulus is 210 GPa, and Poisson's ratio is 0.3.

[0140] Step 3.4: Assemble the parts generated in step 3.1 according to the connection relationship to form a launch vehicle assembly.

[0141] It should be noted that the launch vehicle assembly formed in this step is merely the assembly of various parts, and no rigid constraints and elastic constraints are imposed on the various parts.

[0142] Step 3.5: Establish a rigid connection constraint for the assembly formed in step 3.4.

[0143] For example: to set a rigid constraint between fairing site 6 and instrument cabin site 1, first index the sets corresponding to these two sites: part 1 site 6, part 2 site 1. In the launch vehicle structural dynamics model, the spatial coordinates of these two sites are exactly the same. Constrain the degrees of freedom in directions 1, 2, 3, and 4 of the two, and release degrees of freedom 5 and 6.

[0144] Step 3.6: Establish elastic connection constraints for the assembly formed in step 3.4.

[0145] For example, to set an elastic constraint between fairing station 6 and instrument cabin station 1, first index the sets corresponding to these two stations: part 1 station 6, part 2 station 1. In the launch vehicle structural dynamics model, the spatial coordinates of these two stations are exactly the same. Considering the symmetry of the launch vehicle structure, set the stiffness coefficients of the 5 and 6 directions of both to 10. 7 N / m.

[0146] By establishing rigid connection constraints and elastic connection constraints in the assembly, complete constraints between the parts of each section of the launch vehicle can be achieved, and the final launch vehicle structural dynamics model can be obtained.

[0147] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0148] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0149] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for automatically generating a launch vehicle structural dynamics model, characterized in that: include: The launch vehicle structure is described by the launch vehicle parameters; Read and save the edited launch vehicle parameter information; Automatically generate the launch vehicle structural dynamics model using the saved launch vehicle parameters; Among them, the launch vehicle parameters include launch vehicle site information, launch vehicle mass information, launch vehicle beam section information, launch vehicle rigid constraint information and launch vehicle elastic constraint information.

2. The method for automatically generating a launch vehicle structural dynamics model according to claim 1, characterized in that: The launch vehicle station information includes the number of stations, station geometric coordinates, the section number where the station is located, and the station number of the section where the station is located; The launch vehicle station mass information includes station mass and station inertia; The carrier rocket beam cross-section information includes the number of cross-sections, the beam front end face radius, the beam front end face thickness, the beam rear end face radius, the beam rear end face thickness, the beam section number and the beam section number; The launch vehicle rigid constraint information includes: the number of rigid constraints, the site number of the first rigid constraint point, the site number of the second rigid constraint point and the rigid constraint type; The launch vehicle elastic constraint information includes: the number of elastic constraints, the site number of the first elastic constraint point, the site number of the second elastic constraint point and the six-direction stiffness coefficients of the elastic constraints.

3. The method for automatically generating a launch vehicle structural dynamics model according to claim 2, characterized in that: The description of the launch vehicle structure by the launch vehicle parameters includes: Divide the solid-propellant launch vehicle into different sections and assign a section number to each section; Each section is divided into different stations, and the stations are numbered in the section according to the order of the stations, and line segments are formed between the stations; The mass and inertia of the segment when divided into segments are equivalent to the mass point as the site mass and site inertia; The surface where the front end point of the line segment is located is taken as the front end surface, and the surface where the rear end point of the line segment is located is taken as the rear end surface. Both the front and rear end surfaces describe the cross-sectional information of the launch vehicle beam through the cross-sectional radius and thickness; The directions of the three degrees of freedom of translation between stations and the degree of freedom of rotation around the arrow axis are described as the rigid constraint information of the launch vehicle. Different types of rigid constraint type codes are set according to the connection status of different sections. The directions of the rotational freedom between stations around the lateral and transverse axes of the rocket body are described as the elastic constraint information of the launch vehicle. Different types of elastic constraint type codes are set according to the connection status of different sections.

4. The method for automatically generating a launch vehicle structural dynamics model according to claim 3, characterized in that: The method of automatically generating a launch vehicle structural dynamics model by using the stored launch vehicle parameters includes: Create corresponding parts for each section of the launch vehicle, generate sites in the corresponding parts according to the site coordinates, connect the sites in sequence to generate lines, and create a collection of sites and lines; Add mass points containing mass and inertia to the generated sites; Create beam sections of two different types: front and rear beam faces, assign beam sections to generated lines, assign beam section directions, and set the elastic modulus and Poisson's ratio of beam sections; Assemble the generated parts according to the connection relationship to form a launch vehicle assembly; Establish rigid connection constraints on the formed launch vehicle assembly; Establish elastic connection constraints for the formed launch vehicle assembly.

5. The method for automatically generating a launch vehicle structural dynamics model according to claim 2, characterized in that: When the launch vehicle structure is described by the launch vehicle parameters, the launch vehicle site information, the launch vehicle mass information, the launch vehicle beam section information, the launch vehicle rigid constraint information and the launch vehicle elastic constraint information all generate corresponding parameter editing tables.

6. A computing device, characterized in that include: A processor and a memory storing a computer program, wherein when the computer program is executed by the processor, the method for automatically generating a launch vehicle structural dynamics model as described in any one of claims 1 to 5 is executed.

7. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores computer instructions, and when the instructions are executed on a computer, the computer executes the method for automatically generating a launch vehicle structural dynamics model as described in any one of claims 1 to 5.

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