Method, device and storage medium for automatically generating a launch vehicle structural dynamics model

Abstract

The application discloses a launch vehicle structure dynamics model automatic generation method and device and a storage medium, belongs to the launch vehicle model generation technical field, and comprises the following steps: describing the launch vehicle structure by means of launch vehicle parameters; reading and saving the edited launch vehicle parameter information; and automatically generating a launch vehicle structure dynamics model by means of the saved launch vehicle parameters. The application can be combined with the secondary development function of commercial finite element software by highly parameterizing the launch vehicle, realizes the rapid automatic generation of the model, realizes rapid analysis, and has the characteristics of being easy to check errors.

Description

TECHNICAL FIELD

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

[0002] The launch vehicle structure dynamics model plays a role of connecting the upstream and downstream in the launch vehicle product development process. The designer relies on the aerodynamic shape, mass distribution, structure form and other data in the initial data of the launch vehicle to model the launch vehicle structure dynamics model and perform modal analysis. The results of the modal analysis are used for: launch vehicle static and dynamic load calculation, launch vehicle elastic vibration control design, satellite and rocket coupling analysis and launch vehicle full rocket modal test result prediction.

[0003] The traditional launch vehicle structure dynamics modeling often needs the designer to manually establish the full rocket dynamics model. The problem of this method is that the manual modeling method needs to consume more time and is prone to errors.

[0004] In addition, when the initial data of the launch vehicle changes, the designer needs to model the changed part, and when there are many changes, the designer even needs to re-model the full rocket.

[0005] Therefore, the existing launch vehicle structure dynamics modeling does not adapt to the requirements of product rapid analysis, rapid iteration and rapid development in the commercial aerospace era. Therefore, it is necessary to provide a new technical solution to solve the above problems. SUMMARY

[0006] To solve the above technical problems, the present application provides a launch vehicle structure dynamics model automatic generation method, device and storage medium. By highly parameterizing the description of the launch vehicle, the secondary development function of the commercial finite element software is combined to realize the rapid automatic generation of the model, rapid analysis and easy error checking.

[0007] A launch vehicle structure dynamics model automatic generation method, comprising:

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

[0009] The edited launch vehicle parameter information is read and saved;

[0010] The saved launch vehicle parameters are used to automatically generate a launch vehicle structure dynamics model;

[0011] The launch vehicle parameters include launch vehicle site information, launch vehicle mass information, launch vehicle beam cross-section information, launch vehicle rigid constraint information and launch vehicle elastic constraint information.

[0012] Preferably, the launch vehicle site information includes site quantity, site geometric coordinates, site section number and site section site number;

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

[0014] The launch vehicle beam cross-section information includes cross-section quantity, beam front end face radius, beam front end face thickness, beam rear end face radius, beam rear end face thickness, beam section number and beam section beam number;

[0015] The launch vehicle rigid constraint information includes rigid constraint quantity, first rigid constraint point site number, second rigid constraint point site number and rigid constraint type;

[0016] The launch vehicle elastic constraint information includes elastic constraint quantity, first elastic constraint point site number, second elastic constraint point site number and elastic constraint six-direction stiffness coefficient.

[0017] Preferably, the launch vehicle structure is described by the launch vehicle parameters, including:

[0018] The solid launch vehicle is divided into different sections, and each section is assigned a section number;

[0019] Each section is divided into different sites, and the site number in the section is assigned according to the site division order, and the site and the site form a line segment;

[0020] The mass and inertia of the section when the section is divided are equivalent to the mass and inertia of the particle as the site mass and site inertia;

[0021] The front end point of the line segment is taken as the front end face, and the rear end point of the line segment is taken as the rear end face, and the front and rear end faces are described by the cross-section radius and thickness to describe the launch vehicle beam cross-section information;

[0022] The three translational degrees of freedom between the sites and the rotational degrees of freedom around the rocket axis are described as launch vehicle rigid constraint information, and different types of rigid constraint type codes are set according to the connection state of different sections;

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

[0024] Preferably, the launch vehicle structure dynamics model is automatically generated by using the saved launch vehicle parameters, including:

[0025] A corresponding part is established for each section of the launch vehicle, a station is generated in the corresponding part according to station coordinates, a line is generated by connecting the stations in sequence, and a set of stations and lines is established;

[0026] A mass point containing mass and inertia is added to the generated station;

[0027] A beam section is created according to two different types of beam front end face and beam rear end face, the beam section is assigned to the generated line, the beam section direction is assigned, and the elastic modulus and Poisson's ratio of the beam section are set;

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

[0029] A rigid connection constraint is established for the formed launch vehicle assembly;

[0030] An elastic connection constraint is established for the formed launch vehicle assembly.

[0031] Preferably, when the launch vehicle structure is described by parameters, the launch vehicle station 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 are all generated into corresponding parameter editing tables.

[0032] According to another aspect of the present application, a computing device is also provided, comprising a processor and a memory storing a computer program, which, when executed by the processor, performs the launch vehicle structure dynamics model automatic generation method.

[0033] According to another aspect of the present application, a computer readable storage medium is also provided, which stores computer instructions, which, when executed on a computer, cause the computer to perform the launch vehicle structure dynamics model automatic generation method.

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

[0035] 1. The launch vehicle structure dynamics model automatic generation method of the present application can avoid the problems of time-consuming and easy-to-make mistakes in traditional manual modeling, and realizes automatic modeling of the launch vehicle structure dynamics model.

[0036] 2. The launch vehicle structure dynamics model automatic generation method of the present application can check whether the parameter input is correct through the parameter editing table, and avoids the defect that traditional manual parameter input is easy to make mistakes.

[0037] 3. The automatic generation method for the 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. Attached Figure Description

[0038] 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:

[0039] Figure 1 This is a schematic diagram of the overall process of the automatic generation method for the structural dynamics model of a launch vehicle according to the present invention;

[0040] Figure 2 This is a schematic diagram of the stations and line segments after the substation of a certain section in the automatic generation method of the structural dynamics model of a launch vehicle;

[0041] Figure 3 This is a geometric schematic diagram of the circular cross-section of a beam in the automatic generation method of the launch vehicle structural dynamics model of the present invention. Detailed Implementation

[0042] 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.

[0043] like Figure 1 As shown, an automatic generation method for a launch vehicle structural dynamics model includes the following steps:

[0044] Step S1: Describe the structure of the launch vehicle using launch vehicle parameters.

[0045] The launch vehicle parameters include launch vehicle site information, launch vehicle mass information, launch vehicle beam cross-section information, launch vehicle rigid constraint information, and launch vehicle elastic constraint information.

[0046] Specifically, the launch vehicle station information includes station quantity, station geometric coordinates, station section number and station section station number. The launch vehicle station mass information includes station mass and station inertia. The launch vehicle beam section information includes section number, beam front end face radius, beam front end face thickness, beam rear end face radius, beam rear end face thickness, beam section number and beam section beam number. The launch vehicle rigid constraint information includes: rigid constraint quantity, first rigid constraint point station number, second rigid constraint point station number and rigid constraint type. The launch vehicle elastic constraint information includes: elastic constraint quantity, first elastic constraint point station number, second elastic constraint point station number and elastic constraint six-direction stiffness coefficient.

[0047] Meanwhile, when the launch vehicle structure is described by means of launch vehicle parameters, the launch vehicle station information, launch vehicle mass information, launch vehicle beam section information, launch vehicle rigid constraint information and launch vehicle elastic constraint information are all generated into corresponding parameter editing tables.

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

[0049] Step 1.1, different sections of the launch vehicle are divided, for example, a certain type of rocket is divided into a fairing, an instrument cabin, a core second stage, an interstage section, a core first stage and a tail section, and each section is assigned a section number:

[0050] (1) the fairing is numbered 1;

[0051] (2) the instrument cabin is numbered 2;

[0052] (3) the core second stage is numbered 3;

[0053] (4) the interstage section is numbered 4;

[0054] (5) the core first stage is numbered 5;

[0055] (6) the tail section is numbered 6.

[0056] Further, according to the structural characteristics of each launch vehicle, the station division positions include: upper and lower end faces of the structure, junctions of structure conical sections and column sections, section wall face rigid mutation positions, interested mode shape slope positions, structure support and suspension points, branch structure connection positions, binding connection positions and inside positions of longer structures. Among them, the longer structures include the first stage oxygen tank and the fuel tank, and the structure station positions of the longer structures are located at the dangerous working condition liquid level positions.

[0057] The basis for station division in the embodiment is as follows:

[0058] (1) For the relatively short structures such as the separation ring, the short shells before and after the tank, and the tail section, two stations can be directly set at the upper and lower end faces of the structure, and no station is set inside;

[0059] (2) For the relatively long structures such as the primary oxygen tank and the fuel tank, stations need to be divided inside, and the station positions inside the structure are located at the liquid level positions under dangerous working conditions;

[0060] (3) For the fairing, stations need to be set at the junctions of the cone section and the column section;

[0061] (4) Stations need to be set at the positions where the wall surface of the section rigidly changes;

[0062] (5) Stations need to be set at the positions where the mode shape slope is concerned, such as the inertial unit, the rate gyro, and the engine gimbal;

[0063] (6) Stations need to be set at the positions where concentrated forces need to be output, such as the structure support and suspension points;

[0064] (7) Stations also need to be set at the connection positions of branch structures, such as the satellite adapter connection position, the engine connection position, and the short shell positions before and after the tank;

[0065] (8) For the bundled rocket, stations need to be set at the bundled connection positions.

[0066] Different stations are divided for each section, and the geometric information of each station is described by the (X, Y, Z) coordinates of its spatial position. According to the station division order, the stations are given numbers in the section. For example:

[0067] (1) The No. 1 station of a certain section—No. 1;

[0068] (2) The No. 2 station of a certain section—No. 2;

[0069] (3) The No. 3 station of a certain section—No. 3;

[0070] (4) The No. 4 station of a certain section—No. 4;

[0071] (5) The No. 5 station of a certain section—No. 5.

[0072] It should be noted that the above certain section refers to any one of the fairing, the instrument cabin, the core second stage, the interstage section, the core first stage, and the tail section.

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

[0074] For example:

[0075] (1) The line segment between the station 1 and the station 2 of 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 between station 3 and station 4 in a certain section—line segment 3;

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

[0079] (5) Line segment 5 between station 5 and station 6 in a certain section.

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

[0081] Table 1. Launch Vehicle Site Number Information

[0082]

[0083] Step 1.2: Edit the launch vehicle site mass information: The site mass and inertia are the equivalent results of the mass and inertia of a certain segment when dividing the segments to the mass point, including: site mass and site inertia in three directions, forming the launch vehicle site mass information as shown in Table 2.

[0084] Table 2 Quality Information of Launch Vehicle Sites

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

[0086] Step 1.3: Edit the launch vehicle beam cross-sectional information: Each line segment formed in the above process consists of a front end point and a rear end point. Unless there are special circumstances, the point closer to the theoretical apex of the rocket body is considered the front end point, and the point farther from the theoretical apex is considered the rear end point. The surface containing the front end point is called the front face, and the surface containing the rear end point is called the rear face. Both the front and rear faces are described by their cross-sectional radius and thickness. Each end face is a circular annular cross-section. The descriptive parameters of the circular annular cross-section include the cross-sectional radius R and the thickness δ, such as... Figure 3 As shown.

[0087] According to the station sequence, the line segment is assigned a number within its respective section. The above information forms the launch vehicle beam cross-section information shown in Table 3.

[0088] Table 3 Information on the cross-section of the launch vehicle beam

[0089]

[0090] Step 1.4. Editing the rigid constraint information of the launch vehicle: The rigid constraint means that some degrees of freedom between the nodes are connected by rigidity. The node rigid connection setting is based on the actual connection state between the sections in the launch vehicle, for example, for the connection of the core stage section, it is considered that the 3 translational degrees of freedom directions between the nodes and the rotational degree of freedom around the axis of the rocket are rigidly connected, while the rotational degrees of freedom around the lateral and lateral axes of the rocket body do not have the rigid connection state. According to the connection state of different sections, different types of rigid constraint type codes are set, which are used for the software to identify how to apply the rigid constraint. The above information is summarized as the rigid constraint information of the launch vehicle shown in Table 4.

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

[0092] (1) Code 1 - constraint of three translational degrees of freedom and axial rotational degree of freedom between sections, release of lateral and normal rotational degrees of freedom, mainly used for the connection between the core structure of the rocket body;

[0093] (2) Code 2 - constraint of three translational degrees of freedom between sections, release of three rotational degrees of freedom, mainly used for the ball and socket connection in the binding structure;

[0094] (3) Code 3 - constraint of all six degrees of freedom between sections, mainly used for the connection between the welded structures.

[0095] Table 4. Rigid constraint information table of the launch vehicle

[0096]

[0097] Step 1.5. Editing the elastic constraint information of the launch vehicle: The elastic constraint means that some degrees of freedom between the nodes are connected by elasticity. The node elastic connection setting is based on the actual connection state between the sections in the launch vehicle, and different types of elastic constraint type codes are set, which are used for the software to identify how to apply the elastic constraint. For example, for the connection of the core stage section, it is considered that the rotational degrees of freedom around the lateral and lateral axes of the rocket body are in an elastic connection state, and the connection stiffness coefficient can be arbitrarily set. Each degree of freedom direction is defined as follows:

[0098] (1) 1 direction - translational direction along the axis of the rocket body;

[0099] (2) 2 direction - translational direction along the lateral direction of the rocket body;

[0100] (3) 3 direction - translational direction along the lateral direction of the rocket body;

[0101] (4) 4 direction - rotational direction around the axis of the rocket body;

[0102] (5) 5 direction - rotational direction around the lateral direction of the rocket body;

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

[0104] The above information is summarized as the following Table 5 shows the elastic constraint information of the launch vehicle.

[0105] Table 5 Launch vehicle elastic constraint information table

[0106]

[0107] Step S2, reading and saving the edited launch vehicle parameter information.

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

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

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

[0111] For each section of the launch vehicle, a corresponding part is established, and in the corresponding part, a site is generated according to the site coordinates, a line is generated by connecting the sites in order, and a set of sites and lines is established;

[0112] A mass point containing mass and inertia is added to the generated site;

[0113] Beam cross sections of two different types, beam front end face and beam rear end face, are created, the beam cross sections are distributed to the generated lines, the beam cross section direction is assigned, and the elastic modulus and Poisson's ratio of the beam cross section are set;

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

[0115] A rigid connection constraint is established for the formed launch vehicle assembly;

[0116] An elastic connection constraint is established for the formed launch vehicle assembly.

[0117] Step 3.1, for each section of the launch vehicle, a corresponding part is established, and each part is named. For example:

[0118] (1) fairing - part 1;

[0119] (2) instrument cabin - part 2;

[0120] (3) core second stage - part 3;

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

[0122] (5) Core primary - Part 5;

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

[0124] In the corresponding part, the station is generated according to the station coordinates, and the line segment is generated by connecting the stations in sequence, so that all stations in each part are on a straight line, and the set of stations and line segments is established.

[0125] In the corresponding part, the station is generated according to the station coordinates, and the station is named according to the station sequence.

[0126] For example:

[0127] (1) Fairing No. 1 station - Part 1 Station 1;

[0128] (2) Core secondary No. 3 station - Part 3 Station 3;

[0129] (3) Tail section No. 5 station - Part 6 Station 5.

[0130] In all parts, the line segment is generated by connecting the stations in sequence, so that all stations in each part are on a straight line, and the line segment between the stations is named:

[0131] (1) Line segment between fairing No. 1 station and No. 2 station - Part 1 Line Segment 1;

[0132] (2) Line segment between core secondary No. 3 station and No. 4 station - Part 3 Line Segment 3;

[0133] (3) Line segment between tail section No. 5 station and No. 6 station - Part 6 Line Segment 5.

[0134] The set of stations and line segments is established in this way.

[0135] Step 3.2, add mass points to the stations in step 3.1, including the mass of the point and the inertia of the point.

[0136] For example: The first station of the launch vehicle is the fairing No. 1 station, and the set name is indexed by the full serial number, and then the mass of the point is assigned as 20 kg, and the three-direction inertia is 100 kg·m2.

[0137] Step 3.3, when creating beam sections, according to the dimensions of each part of the launch vehicle and the elastic modulus and Poisson's ratio, create beam sections in two different types of beam front end and beam rear end, and the beam section is used to distribute to the line segment generated in step 3.1.

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

[0139] The elastic modulus and Poisson's ratio of the line segment are set, for example, the Young's modulus is 210 Gpa, and the Poisson's ratio is 0.3.

[0140] Step 3.4, assembling 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 only assembled between the parts, and the rigid constraint and elastic constraint between the parts are not performed.

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

[0143] For example, a rigid constraint is set between the No. 6 station of the fairing and the No. 1 station of the instrument cabin. First, index the corresponding sets of the two stations: part 1 station 6 and part 2 station 1. In the launch vehicle structure dynamics model, the spatial coordinates of the two stations are completely consistent. The 1, 2, 3 and 4 direction freedoms of the two stations are constrained, and the 5 and 6 freedoms are released.

[0144] Step 3.6, establishing an elastic connection constraint for the assembly formed in step 3.4.

[0145] For example, an elastic constraint is set between the No. 6 station of the fairing and the No. 1 station of the instrument cabin. First, index the corresponding sets of the two stations: part 1 station 6 and part 2 station 1. In the launch vehicle structure dynamics model, the spatial coordinates of the two stations are completely consistent. Based on the consideration of the symmetry of the launch vehicle structure, the stiffness coefficients of the 5 and 6 directions of the two stations are set to 10 7 N / m.

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

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

[0148] It should be noted that the terms "first", "second", and the like, used in the description and in the claims of the present application as well as above-mentioned figures are used to distinguish similar objects and are not necessarily used to describe a specific sequential or chronological order. It is to be understood that the use of these terms here is not made with the intention of limiting scope of the embodiments of the present application described herein, but rather that the embodiments of the present application described herein are capable of functioning in other sequences, except for those explicitly described or claimed as set forth herein.

[0149] The preferred embodiments of the application are described above in detail. The application is not limited to the embodiments described above, but can be modified and changed by those skilled in the art without departing from the spirit and principle of the application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the application shall be included in the scope of the protection of the application.

Claims

1. A method for automatically generating a structural dynamics model of a launch vehicle, characterized in that, The application relates to a method for describing a launch vehicle structure through launch vehicle parameters, reading and saving edited launch vehicle parameter information, and automatically generating a launch vehicle structure dynamics model by using saved launch vehicle parameters. 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. The launch vehicle site information includes site quantity, site geometric coordinates, site section number and site section site number. The launch vehicle mass information includes site mass and site inertia. The launch vehicle beam section information includes section quantity, beam front end face radius, beam front end face thickness, beam rear end face radius, beam rear end face thickness, beam section number and beam section beam number. The launch vehicle rigid constraint information includes rigid constraint quantity, first rigid constraint point site number, second rigid constraint point site number and rigid constraint type. The launch vehicle elastic constraint information includes elastic constraint quantity, first elastic constraint point site number, second elastic constraint point site number and elastic constraint six-direction stiffness coefficient. The method comprises the following steps: The solid launch vehicle is divided into different sections, and each section is given a section number. Each section is divided into different sites, and the sites in the section are given numbers in sequence. The mass and inertia of the section are equivalent to the mass and inertia of the sites. The front end face of the line segment is taken as the front end face, and the rear end face of the line segment is taken as the rear end face. The three translational freedom directions between the sites and the rotational freedom directions around the rocket axis are described as the launch vehicle rigid constraint information. The rotational freedom directions around the rocket body transverse and lateral axes are described as the launch vehicle elastic constraint information. The method comprises the following steps: A corresponding part is established for each section of the launch vehicle. The sites are generated according to the site coordinates in the corresponding part.

2. The launch vehicle structural dynamics model automatic generation method of claim 1, wherein, The line segments are generated by connecting the sites in sequence. The mass points containing mass and inertia are added to the generated sites. The beam sections are created according to two different types of beam front end face and beam rear end face. The beam sections are distributed to the generated line segments. The beam section direction is assigned. The elastic modulus and Poisson's ratio of the beam section are set. The parts are assembled according to the connection relationship to form a launch vehicle assembly. The rigid connection constraint of the launch vehicle assembly is established. The elastic connection constraint of the launch vehicle assembly is established.

3. The launch vehicle structural dynamics model automatic generation method of claim 1, wherein, The carrying rocket structure is described by carrying rocket parameters, and the carrying rocket station information, the carrying rocket mass information, the carrying rocket beam section information, the carrying rocket rigid constraint information and the carrying rocket elastic constraint information are all generated into corresponding parameter editing tables.

4. A computing device, comprising: The application relates to a computer program product and a computer readable storage medium. The processor, the memory storing the computer program, the computer program being executed by the processor to perform the method for automatically generating a carrying rocket structure dynamics model according to any one of claims 1 to 3.

5. A computer readable storage medium, characterized in that, The computer readable storage medium stores computer instructions, and when the instructions are executed on the computer, the computer executes the method for automatically generating a carrying rocket structure dynamics model according to any one of claims 1 to 3.

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