A method, device, equipment and medium for connecting rocket sections

Abstract

The present invention discloses a method, device, equipment and medium for connecting rocket sections, including: constructing a one-dimensional model of the rocket body corresponding to the target rocket body according to the target rocket body; determining the target section in the one-dimensional model of the rocket body according to the preset modal vibration mode and modal frequency; performing three-dimensional simulation on the target section, the key connection parts of the target section and the connecting parts of the key connection parts to obtain a three-dimensional model of the section corresponding to the target section; obtaining a hybrid model of the rocket body according to the one-dimensional model of the rocket body and the three-dimensional model of the section; determining the joint surface of the target section in the hybrid model of the rocket body according to the obtained target bending modal vibration mode characteristics, and the joint surface is a rigid connection surface between the target section and the adjacent section. This application starts from the target section that affects the modal of the rocket body, establishes its three-dimensional model, accurately simulates the morphological characteristics of the bending modal vibration mode, and does not need to rely on the test method for the research and development of key connection parts, thereby reducing the test cost.

Description

Technical Field

[0001] The present invention relates to the field of aerospace simulation technology, and in particular, to a method, device, equipment and medium for connecting rocket sections. Background Art

[0002] A reusable rocket refers to a rocket that, after taking off from the ground to complete a predetermined launch mission, returns in whole or in part and lands safely, and can perform another launch mission after inspection, maintenance and fuel filling. The concept of a reusable launch vehicle is relative to a single-use launch vehicle.

[0003] When developing a reusable rocket, a large number of modal tests are required. However, the cost of modal tests is relatively high, resulting in a high development cost of the reusable rocket.

[0004] In the related art, the development of a reusable rocket is mainly carried out through the means of rocket body dynamics simulation technology. However, for the research and development of key connection parts on the rocket body, it still needs to rely on modal tests to complete, resulting in a relatively high development cost of the reusable rocket. Summary of the Invention

[0005] By providing a method, device, equipment and medium for connecting rocket sections in an embodiment of the present application, the technical problem in the prior art that the research and development of key connection parts need to rely on modal tests, resulting in a high development cost of the reusable rocket, is solved, and the technical effect of relying on simulation technology to research and develop related connection parts and reducing the development cost of the reusable rocket is achieved.

[0006] In a first aspect, the present application provides a method for connecting rocket sections, the method including:

[0007] Construct a one-dimensional rocket body model corresponding to the target rocket body according to the target rocket body;

[0008] Determine the target section in the one-dimensional rocket body model according to the preset modal vibration mode and modal frequency, wherein the matching degree of the target section is not lower than the set matching degree;

[0009] Perform three-dimensional simulation on the target section, the key connection parts of the target section and the connectors of the key connection parts to obtain a three-dimensional section model corresponding to the target section;

[0010] Obtain a hybrid rocket body model according to the one-dimensional rocket body model and the three-dimensional section model;

[0011] Determine the joint surface of the target section in the hybrid rocket body model according to the obtained target bending modal vibration mode characteristics, and the joint surface is a rigid connection surface between the target section and the adjacent section.

[0012] Further, constructing a one-dimensional rocket body model corresponding to the target rocket body according to the target rocket body includes:

[0013] Construct a one-dimensional model of the rocket body corresponding to the target rocket body according to the structure of the target rocket body, the equivalent thickness, and the equivalent mechanical properties of the material ply.

[0014] Further, according to the preset modal vibration mode and modal frequency, determine the target cabin sections in the one-dimensional model of the rocket body, including:

[0015] For each cabin section in the one-dimensional model of the rocket body, adjust the material parameters and mechanical property parameters of each cabin section to determine the modal vibration mode and modal frequency of each cabin section;

[0016] Determine the target cabin sections from multiple cabin sections in the one-dimensional model of the rocket body according to the first matching degree between the modal vibration mode of each cabin section and the preset modal vibration mode, and the second matching degree between the modal frequency of each cabin section and the preset modal frequency.

[0017] Further, perform three-dimensional simulation on the target cabin sections and the key connection parts of the target cabin sections, including:

[0018] Perform three-dimensional simulation on the target cabin sections and the key connection parts of the target cabin sections according to the longitudinal load-bearing structure of the target rocket body.

[0019] Further, perform three-dimensional simulation on the connecting parts of the key connection parts, including:

[0020] Perform three-dimensional simulation on the connecting parts of the key connection parts according to the pre-tightening torque, thread lead angle, friction angle, and diameter of the connecting parts.

[0021] Further, the connecting parts of the key connection parts include bolts.

[0022] Further, according to the obtained target bending modal vibration mode characteristics, determine the joint surfaces of the target cabin sections in the hybrid model of the rocket body, including:

[0023] Determine the compression angle range of the target cabin section according to the target bending modal vibration mode characteristics;

[0024] Determine the target compression angle from the compression angle range;

[0025] Determine the joint surface of the target cabin section according to the target compression angle.

[0026] In a second aspect, the present application provides a rocket cabin section connection device, and the device includes:

[0027] A one-dimensional construction module for constructing a one-dimensional model of the rocket body corresponding to the target rocket body according to the target rocket body;

[0028] A first determination module for determining the target cabin sections in the one-dimensional model of the rocket body according to the preset modal vibration mode and modal frequency, wherein the matching degree of the target cabin sections is not lower than the set matching degree;

[0029] A three-dimensional construction module for performing three-dimensional simulation on a target cabin section, key connection parts of the target cabin section, and connectors of the key connection parts to obtain a cabin section three-dimensional model corresponding to the target cabin section;

[0030] A second determination module for obtaining a rocket body hybrid model according to the rocket body one-dimensional model and the cabin section three-dimensional model;

[0031] A third determination module for determining a joint surface of the target cabin section in the rocket body hybrid model according to the obtained target bending mode vibration shape characteristics, where the joint surface is a rigid connection surface between the target cabin section and an adjacent cabin section.

[0032] In a third aspect, the present application provides an electronic device, including:

[0033] A processor;

[0034] A memory for storing instructions executable by the processor;

[0035] Wherein, the processor is configured to execute to implement a rocket cabin section connection method.

[0036] In a fourth aspect, the present application provides a non-transitory computer-readable storage medium, when the instructions in the storage medium are executed by the processor of the electronic device, enabling the electronic device to execute and implement a rocket cabin section connection method.

[0037] One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:

[0038] The present application first constructs a corresponding rocket body one-dimensional model according to the target rocket body, determines the target cabin section in the rocket body one-dimensional model according to the preset mode vibration shape and mode frequency, performs three-dimensional modeling on the target cabin section and its attached components to obtain a rocket body hybrid model that combines the three-dimensional model and the one-dimensional model, and determines the joint surface of the target cabin section in the rocket body hybrid model according to the obtained target bending mode vibration shape characteristics. The present application starts from the target cabin section that affects the rocket body mode, establishes its three-dimensional model, finds a reasonable angle range for rigidly connecting the cabin section joint surface, and then more accurately simulates the morphological characteristics of the bending mode vibration shape. In non-essential cases, it is not necessary to rely on experimental methods for the research and development of key connection parts, thereby reducing the experimental cost and also reducing the research and development cost of reusable rockets. Description of the Drawings

[0039] To more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the accompanying drawings required for the description of the embodiments. Obviously, the accompanying drawings in the following description are some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other accompanying drawings can be obtained based on these drawings.

[0040] Figure 1 It is a schematic flow chart of a method for connecting rocket sections provided by this application;

[0041] Figure 2 It is a schematic diagram of a bolt model provided by this application;

[0042] Figure 3 It is a schematic structural diagram of a rocket section connection device provided by this application;

[0043] Figure 4 It is a schematic structural diagram of an electronic device provided by this application. Specific Embodiments

[0044] By providing a method, device, equipment, and medium for connecting rocket sections in the embodiments of this application, the technical problem in the prior art that the research and development of key connection parts rely on modal tests, resulting in a relatively high development cost for reusable rockets, is solved.

[0045] The technical solutions of the embodiments of this application to solve the above technical problems are generally as follows:

[0046] A method for connecting rocket sections, the method includes: constructing a one-dimensional model of the rocket body corresponding to the target rocket body according to the target rocket body; determining the target section in the one-dimensional model of the rocket body according to the preset modal vibration mode and modal frequency, where the matching degree of the target section is not lower than the set matching degree; performing three-dimensional simulation on the target section, the key connection parts of the target section, and the connectors of the key connection parts to obtain a three-dimensional model of the section corresponding to the target section; obtaining a hybrid model of the rocket body according to the one-dimensional model of the rocket body and the three-dimensional model of the section; determining the joint surface of the target section in the hybrid model of the rocket body according to the obtained target bending modal vibration mode characteristics, and the joint surface is a rigid connection surface between the target section and the adjacent section.

[0047] In this embodiment, a corresponding one-dimensional model of the rocket body is first constructed according to the target rocket body. According to the preset modal vibration mode and modal frequency, the target cabin section in the one-dimensional model of the rocket body is determined. Three-dimensional modeling is carried out on the target cabin section and its attached components to obtain a hybrid rocket body model that combines a three-dimensional model and a one-dimensional model. According to the obtained target bending modal vibration mode characteristics, the joint surface of the target cabin section in the hybrid rocket body model is determined. This embodiment starts from the target cabin section that affects the modal of the rocket body, establishes its three-dimensional model, finds a reasonable angular range for rigid connection of the cabin section joint surface, and then accurately simulates the morphological characteristics of the bending modal vibration mode. In non-essential cases, it is not necessary to rely on experimental methods for the research and development of key connection parts, thereby reducing the experimental cost and also reducing the development cost of reusable rockets.

[0048] To better understand the above technical solution, the above technical solution will be described in detail below in conjunction with the specification drawings and specific implementation manners.

[0049] First, it should be noted that the term "and / or" appearing in this article is merely a description of the association relationship of associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, A and B exist simultaneously, and B exists alone. In addition, the character " / " in this article generally represents an "or" relationship between the associated objects before and after.

[0050] This embodiment provides a Figure 1 rocket cabin section connection method as shown, and the method includes steps S11 - S15.

[0051] Step S11: Construct a one-dimensional model of the rocket body corresponding to the target rocket body according to the target rocket body.

[0052] The target rocket body can be the rocket body of a reusable rocket.

[0053] Specifically, a one-dimensional model of the rocket body corresponding to the target rocket body is constructed according to the structure, equivalent thickness, and equivalent mechanics of the material layup of the target rocket body. In essence, a dynamic analysis of the entire rocket body structure of the target rocket body is carried out. Through the equivalent principle, the stiffness and mass characteristics of the solid element of the cabin section in the target rocket body are equivalent to a one-dimensional beam element model, and the one-dimensional beam element models corresponding to each cabin section are spliced according to the actual structure of the target rocket body to obtain a one-dimensional model of the rocket body corresponding to the target rocket body.

[0054] It should be noted that all cabin section connection parts in the one-dimensional model of the rocket body are assumed to be rigid connections, and their stiffness is consistent with the corresponding cabin section without weakening treatment.

[0055] Among them, the structure of the target rocket body can be determined according to the detailed drawing of the rocket body cabin section structure. The equivalent thickness can be determined by formula (1).

[0056]

[0057] Let \(t\) denote the equivalent thickness, \(S\) i denotes the cross-sectional area of the longitudinal structural member, \(\pi\) denotes the ratio of the circumference of a circle to its diameter (generally taking the value of 3.14), and \(D\) denotes the outer diameter of the shell.

[0058] Step S12: Determine the target section in the one-dimensional model of the rocket body according to the preset modal vibration mode and modal frequency, where the matching degree of the target section is not lower than the set matching degree.

[0059] In the obtained one-dimensional model of the rocket body, the change in connection stiffness caused by assembly problems and bolt connection problems is not considered. If the modal analysis is directly carried out with the one-dimensional model of the rocket body, the accuracy of the obtained analysis results is poor. In related technologies, to solve this problem, the model of the connection part is often corrected by experimental methods, and the modal analysis of the rocket body is carried out by means of the combination of experiment and simulation technology. However, the cost of the experimental method is high, resulting in a high manufacturing cost for reusing rockets.

[0060] In order to solve the above problems in this embodiment, the key sections affecting the rocket body mode are determined from the one-dimensional model of the rocket body, that is, the target sections are identified, and the target sections are distinguished from the ordinary sections (that is, the sections that do not affect the rocket body mode, or the sections that have a small impact on the rocket body mode).

[0061] Specifically, for each section in the one-dimensional model of the rocket body, adjust the material parameters and mechanical property parameters of each section, and determine the modal vibration mode and modal frequency of each section; according to the first matching degree between the modal vibration mode of each section and the preset modal vibration mode, and the second matching degree between the modal frequency of each section and the preset modal frequency, determine the target section from multiple sections in the one-dimensional model of the rocket body.

[0062] For example, through a self-written program in Matlab, the sensitivity analysis of the modal vibration mode and modal frequency of each section in the one-dimensional model of the rocket body can be carried out, and the corresponding material mat variable values and mechanical property mat variable values are set for each section. Usually, 10 - 12 mat variable values are initially set for a one-dimensional model of the rocket body, and the upper and lower limits of each mat variable value can be ±50% of the corresponding mat variable value. Through multiple rounds of iteration, with the set vibration mode matching degree and set frequency matching degree as the goals, for example, setting the vibration mode matching weight value to 100 and the frequency matching value to 1, the key sections affecting the rocket body mode are identified. Its essence is to change each mat variable value and find one or more sections that have the greatest impact on the vibration mode matching weight value and frequency matching value, that is, when changing the corresponding mat variable value, the sections with large fluctuations in the changes of the vibration mode matching value and frequency matching value are determined as the target sections. Usually, the number of target sections is 2 or 3.

[0063] Step S13: Perform 3D simulation on the target section, key connection parts of the target section, and connectors of the key connection parts to obtain a 3D model of the section corresponding to the target section.

[0064] After identifying the target section, 3D simulation is carried out on the target section, key connection parts of the target section, and connectors of the key connection parts, so that the parameters of components or structures related to the target section are closer to the actual parameters of the target rocket body, and the accuracy of various parameters of the target section is improved.

[0065] Specifically, 3D simulation can be carried out on the target section and key connection parts of the target section according to the longitudinal load-bearing structure of the target rocket body; 3D simulation can also be carried out on the connectors of the key connection parts according to the pre-tightening torque, thread lead angle, friction angle, and diameter of the connectors.

[0066] Generally, sections are connected by bolts, so the connectors of the key connection parts include bolts.

[0067] More specifically, when performing 3D solid modeling on the target section according to the structural detail drawing, it is necessary to pay attention to reflecting the real situation of the structure. For example, longitudinal load-bearing structures such as connecting end frames, internal longitudinal bars, longitudinal box-shaped parts, separation bolt boxes, and bolt braces should be as consistent with the actual situation as possible, so as to avoid negative impacts on the simulation effect of the bolt joint surface due to the inaccuracy of the stiffness of the section structure itself. For example, the solid model of the processed target section can contain more than 10,000 volume elements and more than 40,000 surface elements.

[0068] For example, a certain target section in the target rocket body is connected to other sections by 16 M12 bolts. A one-dimensional CBAR beam element expressing the bolt stiffness is established at the middle position of the bolt holes. Among them, the bolt pre-tightening torque M = 48 N·m, and the pre-tightening force is obtained by where θ is the thread lead angle, is the friction angle, and d is the bolt diameter. The bolt strain area is obtained through Patran / Nastran. The nodes in this area are the elements rigidly connected to the bolt beam element RBE2. The six degrees of freedom are restricted to ensure that the bolt moves and rotates together with the connected element. Among them, the bolt RBE2 connection diagram is shown in Figure 2 .

[0069] Step S14: Obtain a hybrid model of the rocket body according to the one-dimensional model of the rocket body and the 3D model of the section.

[0070] Replace the one-dimensional model of the target section in the one-dimensional model of the rocket body with the corresponding 3D model of the section to form a hybrid model of the rocket body. That is, the hybrid model of the rocket body includes a one-dimensional ordinary section model and a 3D target section model.

[0071] Step S15: Determine the joint surface of the target compartment in the rocket body hybrid model according to the obtained target bending mode shape characteristics. The joint surface is a rigid connection surface between the target compartment and the adjacent compartment.

[0072] The bending mode reflects that one side of the rocket body is in tension and the other side is in compression, and the area of the compression surface is smaller than that of the tension surface. The target bending mode shape characteristics are the bending mode shape characteristics that the rocket body is desired to achieve during design. Specifically, the compression angle range of the target compartment can be determined according to the target bending mode shape characteristics; the target compression angle can be determined from the compression angle range; and the joint surface of the target compartment can be determined according to the target compression angle.

[0073] For example, according to the target bending mode shape characteristics, the compression angle range of the target compartment is determined to be 100° - 120°, that is, the angle of the compression surface is 100° - 120°. Within this angle range, the target compartment and the adjacent compartment are completely under compression and fit tightly together without deformation, that is, the contact surface stiffness is infinite and fully reflects the positive pressure. Then, verify the bending mode shape characteristics in each angle state one by one within 100° - 120°, and determine the angle closest to the target bending mode shape characteristics as the target compression angle. For example, the target compression angle is 120°, the compression area is the angle of 120°, and for the two compression surface nodes, a distance value h = 0.05 mm is set, and MPC rigid connection is adopted. It should be noted that within 120°, the joint surfaces are tightly fitted, so the bolt models within this range do not need to be connected to the corresponding compartments.

[0074] In summary, in this embodiment, first, a corresponding one-dimensional model of the rocket body is constructed according to the target rocket body. According to the preset mode shape and mode frequency, the target compartment in the one-dimensional model of the rocket body is determined, and three-dimensional modeling is performed on the target compartment and its attached components to obtain a rocket body hybrid model that combines the three-dimensional model and the one-dimensional model. According to the obtained target bending mode shape characteristics, the joint surface of the target compartment in the rocket body hybrid model is determined. This embodiment starts from the target compartment that affects the rocket body mode, establishes its three-dimensional model, finds a reasonable angle range for rigidly connecting the compartment joint surfaces, and then more accurately simulates the morphological characteristics of the bending mode shape. In non-essential cases, it is not necessary to rely on experimental methods for the research and development of key connection parts, thereby reducing the experimental cost and also reducing the development cost of reusable rockets.

[0075] The inventor determined the joint surface according to the method provided in this embodiment and verified it by experimental means. From the actual comparison results, the modal shape matching degree is high, the MAC value is 0.98, the modal frequency difference is -0.08 Hz, and the bending mode shape coincides with the actual change state of the rocket body, fully verifying that the joint surface angle range of about 120° determined above is reasonable.

[0076] Based on the same inventive concept, this embodiment provides asFigure 3 A rocket section connection device as shown, the device includes:

[0077] A one-dimensional construction module 31, used to construct a one-dimensional model of the rocket body corresponding to the target rocket body according to the target rocket body;

[0078] A first determination module 32, used to determine the target section in the one-dimensional model of the rocket body according to the preset modal vibration mode and modal frequency, where the matching degree of the target section is not lower than the set matching degree;

[0079] A three-dimensional construction module 33, used to perform three-dimensional simulation on the target section, the key connection parts of the target section, and the connecting parts of the key connection parts to obtain a three-dimensional model of the section corresponding to the target section;

[0080] A second determination module 34, used to obtain a hybrid model of the rocket body according to the one-dimensional model of the rocket body and the three-dimensional model of the section;

[0081] A third determination module 35, used to determine the joint surface of the target section in the hybrid model of the rocket body according to the obtained target bending modal vibration mode characteristics, and the joint surface is a rigid connection surface between the target section and the adjacent section.

[0082] Furthermore, the one-dimensional construction module 31 includes:

[0083] A one-dimensional construction sub-module, used to construct a one-dimensional model of the rocket body corresponding to the target rocket body according to the structure, equivalent thickness, and equivalent mechanical properties of the material ply of the target rocket body.

[0084] Furthermore, the first determination module 32 includes:

[0085] An adjustment sub-module, used to adjust the material parameters and mechanical property parameters of each section in the one-dimensional model of the rocket body to determine the modal vibration mode and modal frequency of each section;

[0086] A determination sub-module, used to determine the target section from multiple sections in the one-dimensional model of the rocket body according to the first matching degree between the modal vibration mode of each section and the preset modal vibration mode, and the second matching degree between the modal frequency of each section and the preset modal frequency.

[0087] Furthermore, the three-dimensional construction module 33 includes:

[0088] A three-dimensional construction sub-module, used to perform three-dimensional simulation on the target section and the key connection parts of the target section according to the longitudinal load-bearing structure of the target rocket body.

[0089] Furthermore, the three-dimensional construction sub-module is also used for:

[0090] Perform three-dimensional simulation on the connectors at the key connection parts according to the pre-tightening torque, thread lead angle, friction angle and diameter of the connectors.

[0091] The connectors at the key connection parts include bolts.

[0092] Further, the third determination module 35 is used to include:

[0093] The first determination sub-module is used to determine the compression angle range of the target cabin section according to the target bending mode vibration shape characteristics;

[0094] The second determination sub-module is used to determine the target compression angle from the compression angle range;

[0095] The third determination sub-module is used to determine the joint surface of the target cabin section according to the target compression angle.

[0096] Based on the same inventive concept, this embodiment provides an electronic device as shown in Figure 4 and includes:

[0097] A processor 41;

[0098] A memory 42 for storing executable instructions of the processor 41;

[0099] Wherein, the processor 41 is configured to execute to implement a rocket cabin section connection method.

[0100] Based on the same inventive concept, this embodiment provides a non-transitory computer-readable storage medium. When the instructions in the storage medium are executed by the processor 41 of the electronic device, the electronic device can execute to implement a rocket cabin section connection method.

[0101] Since the electronic device introduced in this embodiment is the electronic device used to implement the information processing method in the embodiments of the present application, based on the information processing method introduced in the embodiments of the present application, those skilled in the art can understand the specific implementation manners and various variations of the electronic device in this embodiment. Therefore, the specific implementation of how this electronic device implements the method in the embodiments of the present application will not be described in detail here. As long as the electronic device used by those skilled in the art to implement the information processing method in the embodiments of the present application belongs to the scope protected by the present application.

[0102] The technical solutions in the above embodiments of the present application at least have the following technical effects or advantages:

[0103] In this embodiment, first, a one-dimensional model of the rocket body is constructed according to the target rocket body. According to the preset modal vibration mode and modal frequency, the target cabin section in the one-dimensional model of the rocket body is determined. Three-dimensional modeling is performed on the target cabin section and its attached components to obtain a hybrid rocket body model that combines a three-dimensional model and a one-dimensional model. According to the obtained target bending modal vibration mode characteristics, the joint surface of the target cabin section in the hybrid rocket body model is determined. This embodiment starts from the target cabin section that affects the rocket body mode, establishes its three-dimensional model, finds a reasonable angle range for rigid connection of the cabin section joint surface, and then more accurately simulates the morphological characteristics of the bending modal vibration mode. In non-essential cases, it is not necessary to rely on experimental methods for the research and development of key connection parts, thereby reducing the experimental cost and also reducing the research and development cost of reusable rockets.

[0104] Those skilled in the art should understand that the embodiments of the present invention can be provided as a method, a system, or a computer program product. Therefore, the present invention can take the form of a complete hardware embodiment, a complete software embodiment, or an embodiment combining software and hardware aspects. Moreover, the present invention can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0105] The present invention is described with reference to the flowcharts and / or block diagrams of methods, apparatuses (systems), and computer program products according to embodiments of the present invention. It should be understood that each process and / or block in the flowchart and / or block diagram can be implemented by computer program instructions, and the combination of processes and / or blocks in the flowchart and / or block diagram can also be implemented by computer program instructions. These computer program instructions can be provided to the processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing devices to generate a machine, so that the instructions executed by the processor of the computer or other programmable data processing devices generate a device for implementing the functions specified in Figure 1 one process or multiple processes and / or blocks Figure 1 one block or multiple blocks.

[0106] These computer program instructions can also be stored in a computer-readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer-readable memory generate a manufactured article including an instruction device, and the instruction device implements the functions specified in Figure 1 one process or multiple processes and / or blocks Figure 1 one block or multiple blocks.

[0107] These computer program instructions can also be loaded onto a computer or other programmable data processing apparatus, so that a series of operation steps are executed on the computer or other programmable apparatus to produce a computer-implemented process, thereby providing instructions for implementing the steps of the function specified in one process or a plurality of processes and / or blocks Figure 1 one process or a plurality of processes and / or blocks Figure 1 steps of the function specified in one block or a plurality of blocks.

[0108] Although the preferred embodiments of the present invention have been described, additional changes and modifications can be made by those skilled in the art once they learn the basic creative concept. Therefore, the appended claims are intended to be construed to cover the preferred embodiments as well as all changes and modifications falling within the scope of the present invention.

[0109] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalent technologies, the present invention is also intended to include these modifications and variations.

Claims

1. A method for connecting rocket sections, characterized in that, The method includes: Constructing a one-dimensional model of the arrow body corresponding to the target arrow body according to the target arrow body; Determining a target cabin section in the one-dimensional model of the arrow body according to preset modal vibration modes and modal frequencies, where the matching degree of the target cabin section is not lower than a set matching degree; Performing three-dimensional simulation on the target cabin section, key connection parts of the target cabin section, and connectors of the key connection parts to obtain a three-dimensional model of the cabin section corresponding to the target cabin section; Obtaining a hybrid model of the arrow body according to the one-dimensional model of the arrow body and the three-dimensional model of the cabin section; Determining a joint surface of the target cabin section in the hybrid model of the arrow body according to the obtained target bending modal vibration mode characteristics, where the joint surface is a rigid connection surface between the target cabin section and an adjacent cabin section; The determining the joint surface of the target cabin section in the hybrid model of the arrow body according to the obtained target bending modal vibration mode characteristics includes: Determining a compression angle range of the target cabin section according to the target bending modal vibration mode characteristics; Determining a target compression angle from the compression angle range; Determining the joint surface of the target cabin section according to the target compression angle.

2. The method according to claim 1, wherein The constructing a one-dimensional model of the arrow body corresponding to the target arrow body according to the target arrow body includes: Constructing a one-dimensional model of the arrow body corresponding to the target arrow body according to the structure, equivalent thickness, and equivalent mechanics of material layup of the target arrow body.

3. The method according to claim 1, wherein The determining a target cabin section in the one-dimensional model of the arrow body according to preset modal vibration modes and modal frequencies includes: For each cabin section in the one-dimensional model of the arrow body, adjusting material parameters and mechanical property parameters of each cabin section to determine the modal vibration mode and modal frequency of each cabin section; Determining the target cabin section from multiple cabin sections in the one-dimensional model of the arrow body according to a first matching degree between the modal vibration mode of each cabin section and the preset modal vibration mode, and a second matching degree between the modal frequency of each cabin section and the preset modal frequency.

4. The method according to claim 1, characterized in that, The performing three-dimensional simulation on the target cabin section and key connection parts of the target cabin section includes: Performing three-dimensional simulation on the target cabin section and key connection parts of the target cabin section according to the longitudinal load-bearing structure of the target arrow body.

5. The method according to claim 1, wherein The performing three-dimensional simulation on the connectors of the key connection parts includes: Performing three-dimensional simulation on the connectors of the key connection parts according to the pre-tightening torque, thread lead angle, friction angle, and diameter of the connectors.

6. The method according to claim 1 or 5, characterized in that, The connectors of the key connection parts include bolts.

7. A rocket section connection device, characterized in that, The device includes: A one-dimensional construction module for constructing a one-dimensional model of the arrow body corresponding to the target arrow body according to the target arrow body; A first determination module for determining a target cabin section in the one-dimensional model of the arrow body according to preset modal vibration modes and modal frequencies, where the matching degree of the target cabin section is not lower than a set matching degree; A three-dimensional construction module for performing three-dimensional simulation on the target cabin section, key connection parts of the target cabin section, and connectors of the key connection parts to obtain a three-dimensional model of the cabin section corresponding to the target cabin section; A second determination module for obtaining a hybrid model of the arrow body according to the one-dimensional model of the arrow body and the three-dimensional model of the cabin section; A third determination module, configured to determine a joint surface of the target cabin section in the rocket body hybrid model according to the obtained target bending mode vibration shape characteristics, where the joint surface is a rigid connection surface between the target cabin section and an adjacent cabin section; The third determination module includes: A first determination sub-module, configured to determine a compression angle range of the target cabin section according to the target bending mode vibration shape characteristics; A second determination sub-module, configured to determine a target compression angle from the compression angle range; A third determination sub-module, configured to determine the joint surface of the target cabin section according to the target compression angle.

8. An electronic device, characterized in that, It includes: A processor; A memory for storing executable instructions of the processor; Wherein, the processor is configured to execute to implement a rocket cabin section connection method according to any one of claims 1 to 6.

9. A non-transitory computer-readable storage medium, when the instructions in the storage medium are executed by a processor of an electronic device, enabling the electronic device to execute and implement a rocket cabin section connection method according to any one of claims 1 to 6.

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