Design method and device of integrated support structure, and electronic equipment

Abstract

The present disclosure relates to a design method, device, and electronic device for an integrated support structure. The integrated support structure is applied to a satellite antenna assembly. The design method includes: designing an integrated support structure optimization template, the integrated support structure optimization template including a base optimization template and a pedestal optimization template; performing topological optimization on the integrated support structure optimization template based on static analysis and dynamic analysis until an optimization result that satisfies the optimization constraints and optimization objectives is obtained; constructing the integrated support structure based on the optimization result; adjusting the structural features of the integrated support structure, and performing static performance verification and dynamic performance verification until the static performance simulation verification and dynamic performance simulation verification of the integrated support structure meet the design requirements.

Description

Technical Field

[0001] The present disclosure relates to the field of communication technology, and in particular to a design method and device for an integrated supporting structure, and electronic equipment. Background Art

[0002] Satellite antennas are critical devices used to transmit and receive radio signals from earth stations or other satellites. As crucial supporting structures for satellite components, their pedestals and mounts must provide stable support during ground testing, launch, and on-orbit operation, while also ensuring mechanical strength, vibration resistance, and shock resistance.

[0003] However, currently, when optimizing the base and pedestal of a micro-antenna with the help of computer software, the optimization is performed independently, and the integrated performance between the optimized structures cannot be guaranteed. There is a situation where the independent design meets the design requirements, but the integrated performance after the base and pedestal are connected does not meet the design requirements. Summary of the Invention

[0004] The present disclosure provides a design method and device for an integrated support structure, and an electronic device to address deficiencies in related technologies.

[0005] According to a first aspect of an embodiment of the present disclosure, a method for designing an integrated support structure is provided. The integrated support structure is applied to a satellite antenna assembly. The design method includes:

[0006] Designing an integrated support structure optimization template, wherein the integrated support structure optimization template includes a base optimization template and a pedestal optimization template;

[0007] Based on static analysis and dynamic analysis, topology optimization is performed on the integrated support structure optimization template until an optimization result that satisfies the optimization constraints and optimization objectives is obtained;

[0008] constructing the integrated support structure based on the optimization result;

[0009] The structural features of the integrated support structure are adjusted, and static performance verification and dynamic performance verification are performed until the static performance simulation verification and dynamic performance simulation verification of the integrated support structure meet the design requirements.

[0010] Optionally, the design of an integrated support structure optimization template includes:

[0011] Design the base optimization template and pedestal optimization template separately;

[0012] Determining the non-design space of the base optimization template and the pedestal optimization template with reference to the assembly relationship in the satellite antenna assembly;

[0013] The base optimization template and the pedestal optimization template are combined into an integrated support structure optimization template.

[0014] Optionally, the mass target of the integrated support structure is used as the optimization target, and the maximization of the weighted strain energy of the integrated support structure during static analysis and the first-order natural frequency of the satellite antenna assembly being greater than or equal to a preset value are used as optimization constraints.

[0015] Optionally, based on static analysis and dynamic analysis, topology optimization is performed on the integrated support structure optimization template until an optimization result that satisfies the optimization constraints and optimization objectives is obtained, including:

[0016] Apply acceleration loads in the positive and negative directions of the X, Y, and Z axes as static working conditions, and obtain the weighted strain energy components under each static working condition.

[0017] The weighted strain energy of the integrated support structure is obtained according to the weight coefficient and weighted strain energy component under each static working condition;

[0018] Performing dynamic modal analysis on the satellite antenna assembly to obtain a first-order natural frequency;

[0019] Obtaining quality parameters of the integrated supporting structure.

[0020] Optionally, performing topology optimization on the integrated support structure optimization template based on static analysis and dynamic analysis until an optimization result that satisfies the optimization constraints and optimization objectives is obtained further includes:

[0021] The integrated support structure optimized template is used to replace the original base and the original pedestal to obtain the satellite antenna assembly;

[0022] Simplifying part of the mechanical structure of the satellite antenna assembly;

[0023] The simplified satellite antenna assembly is imported into the topology optimization software, meshed, assigned material properties, some modules are simplified into mass points, and full constraints of 6 degrees of freedom are applied to the installation surface of the integrated support structure optimization template to establish a topology optimization model.

[0024] Optionally, adjusting the structural features of the integrated support structure and performing static performance verification and dynamic performance verification include:

[0025] Obtaining weighted strain energy of the integrated support structure based on multiple static working conditions;

[0026] Performing dynamic modal analysis, frequency response analysis, and random vibration analysis on the integrated support structure;

[0027] When at least one of the static weighted strain energy, the modal analysis, the frequency response analysis, and the random vibration analysis does not meet design requirements, the structural characteristics of the integrated support structure are adjusted.

[0028] According to a second aspect of an embodiment of the present disclosure, a device for designing an integrated support structure is provided. The integrated support structure is applied to a satellite antenna assembly. The device includes:

[0029] A design module for designing an integrated support structure optimization template, wherein the integrated support structure optimization template includes a base optimization template and a pedestal optimization template;

[0030] A topology optimization module, which performs topology optimization on the integrated support structure optimization template based on static analysis and dynamic analysis until an optimization result that satisfies the optimization constraints and optimization objectives is obtained;

[0031] 3D construction module, which builds integrated support structures based on optimization results;

[0032] A verification module adjusts the structural characteristics of the integrated support structure and performs static performance verification and dynamic performance verification until the static performance simulation verification and dynamic performance simulation verification of the integrated support structure meet the design requirements.

[0033] According to a third aspect of an embodiment of the present disclosure, a computer-readable storage medium is provided, on which computer instructions are stored. When the instructions are executed by a processor, the design method as described in any one of the aforementioned embodiments is implemented.

[0034] According to a fourth aspect of the embodiments of the present disclosure, there is provided an electronic device, including:

[0035] processor;

[0036] a memory for storing processor-executable instructions;

[0037] The processor is configured to implement the design method as described in any one of the aforementioned embodiments.

[0038] The technical solutions provided by the embodiments of the present disclosure may have the following beneficial effects:

[0039] It can be seen from the above embodiments that the present disclosure uses the base optimization template and the base optimization template as an integrated optimization template for topology optimization. Compared with optimizing each optimization template separately, it can reduce time costs and ensure the integrated performance between the optimized structural parts, and the overall performance can be more effectively optimized. Moreover, the present disclosure comprehensively considers static performance and dynamic performance in the topology optimization process, thereby improving the accuracy and reliability of the optimization results in the working environment.

[0040] It is to be understood that the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the disclosure. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the present disclosure and, together with the description, serve to explain the principles of the present disclosure.

[0042] Figure 1 The present invention is a flowchart of a method for designing a supporting structure of a satellite antenna according to an exemplary embodiment.

[0043] Figure 2 The present invention is a flow chart showing a method for designing another supporting structure of a satellite antenna according to an exemplary embodiment.

[0044] Figure 3 is a schematic diagram of a base optimization module according to an exemplary embodiment.

[0045] Figure 4 is a schematic diagram of a base optimization module according to an exemplary embodiment.

[0046] Figure 5 is a schematic diagram of an integrated support structure optimization module according to an exemplary embodiment.

[0047] Figure 6 It is a topological cloud diagram of an integrated support structure optimization module according to an exemplary embodiment.

[0048] Figure 7 An integrated supporting structure constructed three-dimensionally according to an optimized structure is shown according to an exemplary embodiment.

[0049] Figure 8 The present invention is a block diagram of a device for designing a supporting structure of a satellite antenna according to an exemplary embodiment. DETAILED DESCRIPTION

[0050] Exemplary embodiments will be described in detail herein, with examples illustrated in the accompanying drawings. In the following description, when referring to the drawings, identical numerals in different figures represent identical or similar elements, unless otherwise indicated. The embodiments described in the following exemplary embodiments are not intended to represent all possible embodiments consistent with the present disclosure. Rather, they are merely examples of apparatus and methods consistent with certain aspects of the present disclosure, as detailed in the appended claims.

[0051] The terms used in this disclosure are for the purpose of describing specific embodiments only and are not intended to limit the disclosure. As used in this disclosure and the appended claims, the singular forms "a," "an," "the," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and / or" as used herein refers to and encompasses any and all possible combinations of one or more of the associated listed items.

[0052] It should be understood that although the terms first, second, third, etc. may be used in this disclosure to describe various information, such information should not be limited to these terms. These terms are only used to distinguish information of the same type from each other. For example, without departing from the scope of this disclosure, first information may also be referred to as second information, and similarly, second information may also be referred to as first information. Depending on the context, the word "if" as used herein may be interpreted as "at the time of" or "when" or "in response to determining."

[0053] Figure 1 This is a flow chart illustrating a design method for an integrated support structure according to an exemplary embodiment. This integrated support structure can be used in a satellite antenna assembly to provide support for the assembly. This design method can be applied to a terminal device, such as a computer. The design method may include the following steps:

[0054] In step 101, an integrated support structure optimization template is designed, wherein the integrated support structure optimization template includes a base optimization template and a pedestal optimization template.

[0055] In this embodiment, the integrated support structure optimization template is an integrated part of the base optimization template and the pedestal optimization template of the satellite structure. Topology optimization is performed based on the integrated support structure optimization template. Compared with optimizing each optimization template separately, it can reduce time costs and ensure the integrated performance between the optimized structural parts, so that the overall performance can be more effectively optimized.

[0056] The base optimization template and the pedestal optimization template can be designed separately. The non-design space of the base optimization template and the pedestal optimization template can be determined by referring to the assembly relationship of the integrated support structure in the satellite antenna assembly. Then, the base optimization template and the pedestal optimization template can be combined into an integrated support structure optimization template. In the process of generating the optimization template, it is necessary to refer to the assembly relationship of the structure in the satellite structure to determine the design space and non-design space of the optimization template. Under the premise of not interfering with and affecting the normal use of surrounding structures and related components such as electrical components, the design space is expanded as much as possible to provide more space for subsequent topology optimization.

[0057] In step 102, based on static analysis and dynamic analysis, topology optimization is performed on the integrated support structure optimization template until an optimization result that meets the optimization constraints and optimization objectives is obtained.

[0058] In this embodiment, the mass target of the integrated support structure can be used as the optimization objective, and the optimization constraints are the maximization of the weighted strain energy of the integrated support structure during static analysis and the first-order natural frequency of the satellite antenna assembly being greater than or equal to a preset value. Based on the static analysis, the weighted strain energy components under various static working conditions are obtained. The weighted strain energy of the integrated support structure is calculated based on the weight coefficient under each static working condition and the weighted strain energy components under the corresponding static working condition. Based on the dynamic analysis, the first-order natural frequency of the satellite antenna assembly is determined to determine whether the weighted strain energy has reached a maximum and whether the first-order natural frequency is greater than or equal to a preset value, thereby determining whether the optimization result satisfies the optimization constraints and optimization objectives. This design simultaneously considers the overall static stiffness and the first-order modal analysis of dynamics in the topology optimization process, integrating static and dynamic analysis to improve the reliability of the optimization results in the working environment.

[0059] In some embodiments, when performing static analysis, acceleration loads can be applied in the positive and negative directions of the X, Y, and Z axes as six static working conditions, respectively. Based on the weight coefficients and weighted strain energy components under each static working condition, the weighted strain energy of the integrated support structure can be obtained; the satellite antenna assembly can be dynamically analyzed to obtain the first-order natural frequency of the satellite antenna assembly, and the mass parameters of the satellite antenna assembly under each working condition can be obtained. At this time, the mass parameters can be used as optimization targets. For example, the optimization target is that the mass of the integrated support structure is less than or equal to 6 kg.

[0060] Before topological optimization of the satellite antenna assembly, the original base and pedestal must be replaced with the integrated support structure optimization template to obtain a satellite antenna assembly equipped with the integrated support structure optimization template. To improve topological optimization efficiency, some mechanical structures of the satellite antenna assembly can be simplified, such as removing some bolts, nuts, and gaskets. The simplified satellite antenna assembly is then imported into the topology optimization software, where the satellite structure ligands are meshed, material properties are assigned, and some modules are simplified to mass points. Six degrees of freedom full constraints are applied to the mounting surface of the integrated support structure optimization template to create a topological optimization model.

[0061] In step 103, the integrated support structure is constructed based on the optimization result.

[0062] In this embodiment, commercial software can be used to perform 3D reconstruction based on the optimization results to obtain an integrated support structure. If some topology optimization software supports 3D reconstruction, 3D reconstruction can be performed in the topology optimization software based on the optimization results. If other topology optimization software does not support 3D reconstruction, the optimization results can be exported and then 3D reconstruction can be performed in other commercial software that supports 3D reconstruction.

[0063] In step 104 , the structural features of the integrated support structure are adjusted, and static performance verification and dynamic performance verification are performed until the static performance simulation verification and dynamic performance simulation verification of the integrated support structure meet the design requirements.

[0064] In this embodiment, based on the integrated support structure parts three-dimensionally reconstructed by commercial software, designers can partially adjust the structural features of the integrated support structure in the commercial software according to experience, and before the integrated support structure is applied to the engineering field, the static performance check and dynamic performance check of the integrated support structure parts are performed. If both the static performance check and the dynamic performance check meet the design requirements, the integrated support structure can be applied in the engineering field. If either the static performance check or the dynamic performance check does not meet the design requirements, the three-dimensional composition of the integrated support structure parts can be partially adjusted, and the static performance check and dynamic performance check can be re-performed based on the adjusted integrated support structure parts until it meets the design requirements.

[0065] It can be seen from the above embodiments that the present disclosure uses the base optimization template and the base optimization template as an integrated optimization template for topology optimization. Compared with optimizing each optimization template separately, it can reduce time costs and ensure the integrated performance between the optimized structural parts, and the overall performance can be more effectively optimized. Moreover, the present disclosure comprehensively considers static performance and dynamic performance in the topology optimization process, thereby improving the accuracy and reliability of the optimization results in the working environment.

[0066] The following basis Figure 2 The design method of the present disclosure is described in more detail. Figure 2 As shown,

[0067] In step 201, a base optimization template, a pedestal optimization template and an integrated support structure optimization template are designed.

[0068] In this embodiment, the following can be designed: Figure 3 The base optimization template shown and Figure 4 The base optimization template shown in the figure is then obtained through integrated design. Figure 5 The integrated support structure optimization template shown. For both the base optimization template and the pedestal optimization template, the design space and non-design space of the base optimization template and the pedestal optimization template need to be determined first. The design space can be optimized in the subsequent topology optimization process, while the non-design space remains unchanged in the subsequent topology optimization process.

[0069] For example, the base optimization template can include two non-design spaces, including a pitch active interface 1 and a pitch passive interface 2. The motor can connect the base and the pitch member through the pitch active interface 1 to provide power for the rotation of the pitch member. The base can be connected to the conversion member through the pitch passive interface 2, and the conversion member is connected to the bearing, thereby realizing the pitch motion of the entire pitch member. Therefore, the pitch active interface 1 and the pitch passive interface 2 remain consistent during the topology optimization process and serve as non-design spaces. The base optimization template can include a non-design space, which is a ground bolt interface 3, through which the base optimization template is fixed.

[0070] In step 202 , the integrated support structure optimization template is imported into the satellite antenna assembly to replace the original base and the original pedestal.

[0071] In this embodiment, based on the original three-dimensional model of the satellite antenna assembly, the integrated support structure optimization template can be imported into the original three-dimensional model of the satellite antenna assembly, replacing the original base and the original base, and the following is obtained: Figure 6 Satellite antenna assembly shown with optimized template for integrated support structure.

[0072] In step 203, a portion of the mechanical structure of the satellite antenna assembly is simplified.

[0073] In this embodiment, to improve the efficiency of subsequent topology optimization, some mechanical structures of the satellite antenna assembly can be optimized. For example, mechanical structures such as bolts, screws, washers, and bearings configured in the satellite antenna assembly can be deleted. For another example, the fillets of the satellite antenna assembly can be simplified.

[0074] In step 204 , attributes are assigned to the simplified satellite antenna assembly.

[0075] In this embodiment, attributes are assigned to a satellite antenna assembly equipped with an integrated support structure optimization template. For example, the integrated support structure optimization template can be imported into topology optimization software. The satellite antenna assembly is then meshed, material attributes are assigned, other electrical modules are simplified to mass points, and a full six-degree-of-freedom constraint is applied to the mounting surface of the integrated support structure optimization template, thereby establishing a topology optimization model. The full six-degree-of-freedom constraint can include rotational degrees of freedom along the X, Y, and Z axes, as well as translational degrees of freedom. This means that the mounting surface of the integrated support structure optimization template serves as a fixed structure that secures the satellite antenna assembly to the ground.

[0076] In step 205 , the optimization goal and optimization constraints for topology optimization of the satellite antenna assembly are defined.

[0077] In this embodiment, the mass target of the integrated support structure assembly can be defined as the optimization objective. For example, this optimization target can be 6 kg. Optimization constraints include maximizing the weighted strain energy of the integrated support structure during static analysis and ensuring that the first-order natural frequency of the satellite antenna assembly is greater than or equal to a preset value. Furthermore, related optimization settings, such as optimization output items and minimum optimization dimensions, can be configured to achieve a more optimal structure.

[0078] In step 206, the integrated support structure optimization template is optimized.

[0079] In step 207 , based on the static analysis and the dynamic analysis, it is determined whether the optimization objectives and optimization constraints are satisfied.

[0080] In this embodiment, if the optimization objective and optimization constraints are satisfied based on the static and dynamic analyses, the process proceeds to step 208. If the optimization objective and optimization constraints are not satisfied based on the static and dynamic analyses, the process proceeds to step 206. The static and dynamic analyses can be performed in commercial topology optimization software.

[0081] When an optimized structure that meets the optimization objectives and optimization constraints cannot be obtained based on static analysis and dynamic analysis, the integrated support structure optimization template can be adjusted and optimized according to the analysis results, and then step 208 is executed again until the optimization result can reach an optimized structure that meets the optimization objectives and optimization constraints.

[0082] As shown in Table 1, during the static analysis, acceleration loads need to be applied in the positive and negative directions of the X, Y, and Z axes, respectively, to obtain the weighted strain energy components under six static working conditions. Based on the weight coefficients of the six static working conditions, the weighted strain energy of the integrated support structure can be obtained.

[0083] Table 1

[0084]

[0085] In step 208 , an optimization result for the integrated support structure is obtained.

[0086] In this embodiment, the optimization result can be obtained by obtaining an optimized structure that satisfies the optimization goal and optimization constraints. For example, Figure 6 As shown, a cloud diagram of the topology optimization results can be obtained.

[0087] In step 209 , commercial software is used to construct an integrated support structure in three dimensions based on the optimization results.

[0088] In this embodiment, commercial software for surface and solid modeling can be used to construct an integrated support structure in three dimensions based on the optimization results, so as to efficiently complete the reconstruction of the surface entity. For example, in the structural reconstruction phase, the one-click PolyNURBS function in Altair.Inspire can be used to efficiently complete the reconstruction of the surface entity. The combination of PolyNURBS polygon modeling and NURBS modeling also ensures the innovation of the reconstructed three-dimensional structure. For example, the following can be obtained: Figure 7 The integrated support structure shown in the figure can also be topologically optimized using Altair Inspire software.

[0089] In step 210 , the three-dimensional model of the integrated support structure is locally adjusted.

[0090] In this embodiment, based on the designer's experience and practice, the three-dimensional model of the integrated support structure can be partially adjusted to obtain a more optimized integrated support structure.

[0091] In step 211 , static performance verification and dynamic performance verification are performed on the integrated supporting structure.

[0092] In this embodiment, when the static performance check and the dynamic performance check of the integrated support structure meet the design requirements, the process proceeds to step 202. When the static performance check and the dynamic performance check of the integrated support structure do not meet the design requirements, the process proceeds to step 210.

[0093] Among them, the static performance verification of the integrated support structure can be performed based on the static working condition, wherein the static working condition can be the same as the static working condition described in step 207, and the stress distribution and maximum displacement of the satellite antenna assembly are obtained through the static performance verification. When the maximum stress is less than the allowable stress of the material and the maximum displacement meets the upper limit of the displacement limit, it is considered that the static performance verification result meets the design requirements.

[0094] The satellite antenna assembly also needs to be checked for its dynamic performance. Based on the actual needs of engineering applications, in addition to modal analysis, frequency response analysis and random vibration analysis are also required for the satellite antenna assembly.

[0095] During the static performance verification and the dynamic performance verification, it can be completed through commercial software or through calculation. If any analysis result in the static performance verification and the dynamic performance verification does not meet the design requirements, it can be transferred to step 210 to readjust the integrated support structure.

[0096] In step 212, end.

[0097] Corresponding to the aforementioned embodiment of the method for designing a supporting structure of a satellite antenna, the present disclosure also provides an embodiment of an apparatus for designing a supporting structure of a satellite antenna.

[0098] Figure 8 This is a block diagram of a design device for a supporting structure of a satellite antenna according to an exemplary embodiment. Figure 8 The device includes a design module 81, a topology optimization module 82, a three-dimensional construction module 83 and a verification module 84.

[0099] The design module 81 designs an integrated support structure optimization template, wherein the integrated support structure optimization template includes a base optimization template and a pedestal optimization template.

[0100] The topology optimization module 82 performs topology optimization on the integrated support structure optimization template based on static analysis and dynamic analysis until an optimization result that meets the optimization constraints and optimization objectives is obtained.

[0101] The three-dimensional construction module 83 constructs the integrated support structure based on the optimization result.

[0102] The verification module 84 adjusts the structural characteristics of the integrated support structure and performs static performance verification and dynamic performance verification until the static performance simulation verification and dynamic performance simulation verification of the integrated support structure meet the design requirements.

[0103] Regarding the apparatus in the above embodiment, the specific manner in which each module performs operations has been described in detail in the embodiment of the method, and will not be elaborated here.

[0104] For the device embodiments, since they basically correspond to the method embodiments, the relevant parts can be referred to the partial description of the method embodiments. The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the disclosed solution. A person of ordinary skill in the art can understand and implement it without paying any creative work.

[0105] Accordingly, the present disclosure also provides a design device for a support structure of a satellite antenna, comprising: a processor; a memory for storing processor executable instructions; wherein the processor is configured to: design an integrated support structure optimization template, the integrated support structure optimization template including a base optimization template and a pedestal optimization template; based on static analysis and dynamic analysis, perform topological optimization on the integrated support structure optimization template until an optimization result that meets the optimization constraints and optimization objectives is obtained; construct the integrated support structure based on the optimization result; adjust the structural features of the integrated support structure, and perform static performance verification and dynamic performance verification until the static performance simulation verification and dynamic performance simulation verification of the integrated support structure meet the design requirements.

[0106] Accordingly, the present disclosure also provides an electronic device, wherein the terminal includes a memory and one or more programs, wherein the one or more programs are stored in the memory and are configured to be executed by one or more processors, wherein the one or more programs include instructions for performing the following operations: designing an integrated support structure optimization template, wherein the integrated support structure optimization template includes a base optimization template and a pedestal optimization template; performing topological optimization on the integrated support structure optimization template based on static analysis and dynamic analysis until an optimization result that meets the optimization constraints and optimization objectives is obtained; constructing the integrated support structure component based on the optimization result; adjusting the structural features of the integrated support structure component, and performing static performance verification and dynamic performance verification until the static performance simulation verification and dynamic performance simulation verification of the integrated support structure component meet the design requirements.

[0107] In an exemplary embodiment, a computer-readable storage medium is further provided, on which computer instructions are stored. When the instructions are executed by a processor, the steps of the method described in any of the aforementioned embodiments are implemented. For example, the computer-readable storage medium may be a ROM, a random access memory (RAM), a CD-ROM, a magnetic tape, a floppy disk, or an optical data storage device.

[0108] Other embodiments of the present disclosure will readily occur to those skilled in the art after considering the specification and practicing the disclosure herein. This disclosure is intended to cover any variations, uses, or adaptations of the present disclosure that follow the general principles of the present disclosure and include common knowledge or customary techniques in the art not disclosed herein. The description and examples are to be considered as exemplary only, with the true scope and spirit of the present disclosure being indicated by the following claims.

[0109] It should be understood that the present disclosure is not limited to the exact structures that have been described above and shown in the drawings, and that various modifications and changes can be made without departing from the scope thereof. The scope of the present disclosure is limited only by the appended claims.

Claims

1. A design method for an integrated support structure, characterized in that: The integrated support structure is applied to a satellite antenna assembly, and the design method includes: Designing an integrated support structure optimization template, wherein the integrated support structure optimization template includes a base optimization template and a pedestal optimization template; Based on static analysis and dynamic analysis, topology optimization is performed on the integrated support structure optimization template until an optimization result that satisfies the optimization constraints and optimization objectives is obtained; constructing the integrated support structure based on the optimization result; Adjusting the structural features of the integrated support structure, and performing static performance verification and dynamic performance verification until the static performance simulation verification and dynamic performance simulation verification of the integrated support structure meet the design requirements; The quality target of the integrated supporting structure is used as the optimization target; Based on static analysis and dynamic analysis, topology optimization is performed on the integrated support structure optimization template until an optimization result that satisfies the optimization constraints and optimization objectives is obtained, including: Apply acceleration loads in the positive and negative directions of the X, Y, and Z axes as static working conditions, and obtain the weighted strain energy components under each static working condition. The weighted strain energy of the integrated support structure is obtained according to the weight coefficient and weighted strain energy component under each static working condition; Performing dynamic modal analysis on the satellite antenna assembly to obtain a first-order natural frequency; Obtaining quality parameters of the integrated support structure; Based on static analysis and dynamic analysis, topology optimization is performed on the optimized template of the integrated support structure until an optimization result that satisfies the optimization constraints and optimization objectives is obtained, which also includes: The integrated support structure optimized template is used to replace the original base and the original pedestal to obtain the satellite antenna assembly; Simplifying part of the mechanical structure of the satellite antenna assembly; The simplified satellite antenna assembly is imported into the topology optimization software, meshed, assigned material properties, some modules are simplified into mass points, and full constraints of 6 degrees of freedom are applied to the installation surface of the integrated support structure optimization template to establish a topology optimization model.

2. The design method according to claim 1, characterized in that: The design of the integrated support structure optimization template includes: Design the base optimization template and pedestal optimization template separately; Determining the non-design space of the base optimization template and the pedestal optimization template with reference to the assembly relationship in the satellite antenna assembly; The base optimization template and the pedestal optimization template are combined into an integrated support structure optimization template.

3. The design method according to claim 1, characterized in that: The adjusting of the structural features of the integrated support structure and the performing of static performance verification and dynamic performance verification include: Obtaining weighted strain energy of the integrated support structure based on multiple static working conditions; Performing dynamic modal analysis, frequency response analysis, and random vibration analysis on the integrated support structure; When at least one of the weighted strain energy, the modal analysis, the frequency response analysis, and the random vibration analysis does not meet design requirements, the structural characteristics of the integrated support structure are adjusted.

4. A design device for an integrated support structure, characterized in that: The integrated support structure is applied to a satellite antenna assembly, and the design device includes: A design module for designing an integrated support structure optimization template, wherein the integrated support structure optimization template includes a base optimization template and a pedestal optimization template; A topology optimization module, which performs topology optimization on the integrated support structure optimization template based on static analysis and dynamic analysis until an optimization result that satisfies the optimization constraints and optimization objectives is obtained; 3D construction module, which builds integrated support structures based on optimization results; a verification module, adjusting the structural characteristics of the integrated support structure, and performing static performance verification and dynamic performance verification until the static performance simulation verification and dynamic performance simulation verification of the integrated support structure meet the design requirements; The quality target of the integrated supporting structure is used as the optimization target; Based on static analysis and dynamic analysis, topology optimization is performed on the integrated support structure optimization template until an optimization result that satisfies the optimization constraints and optimization objectives is obtained, including: Apply acceleration loads in the positive and negative directions of the X, Y, and Z axes as static working conditions, and obtain the weighted strain energy components under each static working condition. The weighted strain energy of the integrated support structure is obtained according to the weight coefficient and weighted strain energy component under each static working condition; Performing dynamic modal analysis on the satellite antenna assembly to obtain a first-order natural frequency; Obtaining quality parameters of the integrated support structure; Based on static analysis and dynamic analysis, topology optimization is performed on the optimized template of the integrated support structure until an optimization result that satisfies the optimization constraints and optimization objectives is obtained, which also includes: The integrated support structure optimized template is used to replace the original base and the original pedestal to obtain the satellite antenna assembly; Simplifying part of the mechanical structure of the satellite antenna assembly; The simplified satellite antenna assembly is imported into the topology optimization software, meshed, assigned material properties, some modules are simplified into mass points, and full constraints of 6 degrees of freedom are applied to the installation surface of the integrated support structure optimization template to establish a topology optimization model.

5. A computer-readable storage medium having computer instructions stored thereon, characterized in that: When the instruction is executed by the processor, the design method according to any one of claims 1 to 3 is implemented.

6. An electronic device, characterized in that: include: processor; a memory for storing processor-executable instructions; The processor is configured to implement the design method according to any one of claims 1 to 3.

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