A satellite structure design method and satellite structure

Abstract

This application provides a design method and a satellite structure. The design method includes: obtaining a main body optimization model of the main structure, an initial model of the support frame, and a first configuration size range of the support frame's optimized portion; generating an overall initial model of the satellite structure based on the main body optimization model and the initial model of the support frame; determining a first optimal configuration size of the support frame's optimized portion from the first configuration size range based on the overall initial model and its overall constraints; and generating an overall optimization model of the satellite structure based on the overall initial model and the first optimal configuration size. By optimizing the support frame based on the optimization of the main structure, the overall structure can be significantly lightweighted; the performance requirements of the overall structure are considered during the optimization process, ensuring that the optimized support frame fully matches the performance requirements of the overall structure.

Description

Technical Field

[0001] This application relates to the field of satellite design technology, and in particular to a satellite structure design method and satellite structure. Background Technology

[0002] Nanosat typically refers to satellites weighing less than 10 kg with practical functions. Driven by the development of advanced technologies and evolving demands, nanosat, with its advantages of small size, low power consumption, short development cycle, and ability to be networked and perform many complex space missions at a lower cost, plays a vital role in scientific research, defense, and commercial applications.

[0003] Satellites are typically designed using computational software (such as ABAQUS, ANSYS, MSC, etc.). The macroscopic configuration parameters of the satellite structure are input into the computational software, which then calculates its microscopic configuration parameters to ensure that the satellite meets the constraints of frequency and weight, thus obtaining an optimized model of the satellite structure.

[0004] The inventors discovered the following problems through analysis of existing satellite design methods: the overall structure is still relatively heavy, resulting in high satellite launch costs; the satellite support structure cannot fully match the performance requirements of the overall structure, affecting the overall performance of the satellite; and the software optimization process consumes a lot of computing resources, leading to high satellite design costs. Summary of the Invention

[0005] In view of the aforementioned problems, this application is made to provide a satellite structure design method and satellite structure that overcomes or at least partially solves the aforementioned problems, comprising:

[0006] A method for designing a satellite structure, the satellite structure comprising a main structure and a support connected to the main structure, the support having a portion to be optimized; the design method comprising:

[0007] Obtain the main body optimization model of the main structure, the initial support model of the support, and the first configuration size range of the support to be optimized;

[0008] Based on the main body optimization model and the initial support model, an overall initial model of the satellite structure is generated;

[0009] Based on the overall initial model and the overall constraints of the overall initial model, the first optimal configuration size of the support component to be optimized is determined from the first configuration size range;

[0010] Based on the overall initial model and the first optimal configuration dimensions, an overall optimized model of the satellite structure is generated.

[0011] Preferably, the main structure has a main part to be optimized; the design method further includes:

[0012] Obtain the initial model of the main structure and the second configuration size range of the part of the main structure to be optimized;

[0013] Based on the initial model of the main body and the main body constraints of the initial model of the main body, the second optimal configuration size of the part of the main body to be optimized is determined from the second configuration size range;

[0014] Based on the initial model of the main body and the second optimal configuration dimensions, the main body optimization model of the main body structure is generated.

[0015] Preferably, the main structure includes a plate structure and a single unit connected to the plate structure, the bracket is connected to the plate structure, and the plate structure has the main body part to be optimized; the design method further includes:

[0016] Obtain the initial model of the plate structure and the initial model of the stand-alone device;

[0017] Based on the initial model of the plate and the initial model of the single machine, the initial model of the main body is generated.

[0018] Preferably, the step of generating the main body initial model based on the plate initial model and the single-machine initial model includes:

[0019] Based on the initial single-machine model, a mass point model of the single-machine device is generated;

[0020] The mass point model is connected to the initial plate model to obtain the initial body model.

[0021] Preferably, the step of generating the mass point model of the single-machine device based on the initial single-machine model includes:

[0022] Extract the mass and centroid coordinates of the initial single-machine model;

[0023] The mass point model is generated based on the mass and the centroid coordinates.

[0024] Preferably, the plate structure is formed by a plurality of clamping plate assemblies, the clamping plate assembly including a sandwich layer and clamping plates disposed opposite to each other on both sides of the sandwich layer, the sandwich layer having the main body part to be optimized.

[0025] Preferably, the support includes a filling layer and a frame surrounding the periphery of the filling layer, and the filling layer has the portion of the support to be optimized.

[0026] Preferably, the main constraint condition is to reduce the weight of the initial model of the main body to a second proportional range and to achieve a maximum frequency.

[0027] Preferably, the overall constraint condition is to reduce the weight of the overall initial model to a first proportional range and to achieve the maximum frequency.

[0028] A design apparatus for a satellite structure, the satellite structure including a main structure and a support connected to the main structure, the support having a portion to be optimized; the design apparatus includes:

[0029] The initial model acquisition module for the support is used to acquire the main body optimization model of the main structure, the initial model of the support, and the first configuration size range of the part of the support to be optimized.

[0030] The overall initial model generation module is used to generate an overall initial model of the satellite structure based on the main body optimization model and the support initial model;

[0031] The first configuration size determination module is used to determine the first optimal configuration size of the support component to be optimized from the first configuration size range based on the overall initial model and the overall constraints of the overall initial model.

[0032] The overall optimization model generation module is used to generate an overall optimization model of the satellite structure based on the overall initial model and the first optimal configuration size.

[0033] A satellite structure, designed by any of the above-described design methods, includes: a main structure and a support connected to the main structure, wherein the main structure has a main optimized portion and the support has a support optimized portion.

[0034] This application has the following advantages:

[0035] In the embodiments of this application, compared with the problems of large overall structural weight and insufficient performance matching between the satellite support and the overall structure in existing satellite design methods, this application provides a solution to optimize the support based on the optimization of the main structure. Specifically, it is as follows: "A satellite structure design method, the satellite structure including a main structure and a support connected to the main structure, the support having a part to be optimized; the design method includes: obtaining a main optimization model of the main structure, an initial support model of the support, and a first configuration size range of the part to be optimized; generating an overall initial model of the satellite structure based on the main optimization model and the initial support model; determining a first optimal configuration size of the part to be optimized from the first configuration size range based on the overall initial model and the overall constraints of the overall initial model; generating an overall optimization model of the satellite structure based on the overall initial model and the first optimal configuration size." By optimizing the support based on the optimization of the main structure, the overall structure can be significantly lightweighted, improving the economic efficiency of satellite launch; and the performance requirements of the overall structure are considered during the optimization process, ensuring that the optimized support fully matches the performance requirements of the overall structure, and the overall performance of the satellite is not affected. Attached Figure Description

[0036] To more clearly illustrate the technical solution of this application, the drawings used in the description of this application will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0037] Figure 1 This is a flowchart illustrating the steps of a satellite structure design method according to an embodiment of this application;

[0038] Figure 2 This is a flowchart illustrating the steps of a satellite structure design method according to another embodiment of this application;

[0039] Figure 3 This is a flowchart illustrating the steps of a satellite structure design method according to another embodiment of this application;

[0040] Figure 4 This is a flowchart illustrating the steps of a satellite structure design method according to another embodiment of this application;

[0041] Figure 5 This is a structural block diagram of a satellite structure design device provided in one embodiment of this application;

[0042] Figure 6This is a structural block diagram of a satellite structure design device provided in another embodiment of this application;

[0043] Figure 7 This is a structural block diagram of a satellite structure design device provided in another embodiment of this application;

[0044] Figure 8 This is a schematic diagram of the structure of a computer device provided in one embodiment of this application;

[0045] Figure 9 This is a schematic diagram of a satellite structure provided in one embodiment of this application;

[0046] Figure 10 This is a schematic diagram of the main structure in a satellite structure according to an embodiment of this application;

[0047] Figure 11 This is a schematic diagram of the structure of a clamping plate assembly in a satellite structure according to an embodiment of this application;

[0048] Figure 12 This is a schematic diagram of the support structure in a satellite structure according to an embodiment of this application;

[0049] Figure 13 This is a schematic diagram of a plate structure in a satellite structure according to an embodiment of this application;

[0050] Figure 14 This is a schematic diagram of the internal structure of a plate structure in a satellite structure according to an embodiment of this application;

[0051] Figure 15 This is a schematic diagram of a lattice configuration provided in an embodiment of this application;

[0052] Figure 16 This is a schematic diagram of a lattice configuration provided in another embodiment of this application.

[0053] The reference numerals in the accompanying drawings are as follows:

[0054] 12. Computer equipment; 14. Peripheral equipment; 16. Processing unit; 18. Bus; 20. Network adapter; 22. I / O interface; 24. Display; 28. Memory; 30. Random access memory; 32. Cache memory; 34. Storage system; 40. Program / utility; 42. Program module; 50. Main structure; 51. Plate structure; 510. Clamping assembly; 511. Mezzanine; 5111. Solid block; 512. Clamping plate; 520. Connector; 52. Standalone device; 60. Bracket; 61. Filling layer; 62. Frame; 63. Sub-plate. Detailed Implementation

[0055] To make the objectives, features, and advantages of this application more apparent and understandable, the application will be further described in detail below with reference to the accompanying drawings and specific embodiments. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application.

[0056] Reference Figure 1 , 8 This application illustrates a satellite structure design method according to an embodiment of the present application. The satellite structure includes a main structure 50 and a support 60 connected to the main structure 50. The support 60 has a support portion to be optimized. The design method includes:

[0057] S110. Obtain the main body optimization model of the main structure 50, the initial support model of the support 60, and the first configuration size range of the support to be optimized part;

[0058] S120. Based on the main body optimization model and the support initial model, generate the overall initial model of the satellite structure;

[0059] S130. Based on the overall initial model and the overall constraints of the overall initial model, determine the first optimal configuration size of the support component to be optimized from the first configuration size range;

[0060] S140. Based on the overall initial model and the first optimal configuration size, generate an overall optimized model of the satellite structure.

[0061] In the embodiments of this application, in contrast to the problems of large overall structural weight and insufficient performance matching between the satellite support and the overall structure in existing satellite design methods, this application provides a solution for optimizing the support 60 based on the optimization of the main structure 50. Specifically, it is as follows: "A design method for a satellite structure, the satellite structure including a main structure 50 and a support 60 connected to the main structure 50, the support 60 having a support portion to be optimized; the design method includes: obtaining a main optimized model of the main structure 50, an initial support model of the support 60, and a first configuration size range of the support portion to be optimized; generating an overall initial model of the satellite structure based on the main optimized model and the initial support model; determining a first optimal configuration size of the support portion to be optimized from the first configuration size range based on the overall initial model and the overall constraints of the overall initial model; and generating an overall optimized model of the satellite structure based on the overall initial model and the first optimal configuration size." By optimizing the support structure 60 based on the optimization of the main structure 50, the overall structure can be made lighter, improving the economy of satellite launch. Furthermore, the performance requirements of the overall structure are taken into account during the optimization of the support structure 60, ensuring that the optimized support structure 60 is fully matched with the performance requirements of the overall structure, and the overall performance of the satellite is not affected.

[0062] The design method of a satellite structure in this exemplary embodiment will be further described below.

[0063] As described in steps S110 and S120, the main body optimization model of the main structure 50, the initial support model of the support 60, and the first configuration size range of the support to be optimized are obtained; based on the main body optimization model and the initial support model, the overall initial model of the satellite structure is generated.

[0064] Obtain the main body optimization model, the initial model of the support, and the first configuration size range; wherein, the main body optimization model is obtained by pre-optimizing the main body initial model of the main body structure 50; the first configuration size range is the mesoscopic configuration size range of the support to be optimized part, as an example, the support to be optimized part forms a hole configuration after optimization (including but not limited to...). Figure 11 The hole configuration shown in the figure), the size range of the first configuration can be the coordinate range, number range and aperture range of the hole configuration, etc.; connect the main body optimization model and the support initial model to obtain the overall initial model.

[0065] As described in step S130, based on the overall initial model and the overall constraints of the overall initial model, the first optimal configuration size of the support to be optimized part is determined from the first configuration size range.

[0066] The overall initial model, the overall constraints, and the first configuration size range are input into the calculation software (e.g., ABAQUS, ANSYS, MSC, etc.) to obtain the first optimal configuration size. The calculation software is used to calculate the first optimal configuration size from the first configuration size range so that the overall initial model conforms to the overall constraints. The overall constraints are constraints on the weight and frequency of the overall initial model. As an example, the overall constraints are to reduce the weight of the overall initial model to a first proportional range (e.g., 30%-50%) and achieve a maximum frequency. As another example, the overall constraints are to ensure that the frequency of the overall initial model meets a preset value (e.g., 60Hz) and the weight reaches a minimum.

[0067] As described in step S140, an overall optimized model of the satellite structure is generated based on the overall initial model and the first optimal configuration size.

[0068] The initial model of the support structure in the overall initial model is refined and filled according to the first optimal configuration size to obtain the overall optimized model.

[0069] Reference Figure 2 In one embodiment of this application, the main structure 50 has a main body part to be optimized; the design method further includes:

[0070] S030. Obtain the initial model of the main body structure 50 and the second configuration size range of the part of the main body to be optimized;

[0071] S040. Based on the initial model of the main body and the main body constraints of the initial model of the main body, determine the second optimal configuration size of the part of the main body to be optimized from the second configuration size range;

[0072] S050. Based on the initial model of the main body and the second optimal configuration size, generate the main body optimization model of the main body structure 50.

[0073] As described in steps S030 and S040, the initial model of the main body structure 50 and the second configuration size range of the part of the main body to be optimized are obtained; based on the initial model of the main body and the main body constraints of the initial model of the main body, the second optimal configuration size of the part of the main body to be optimized is determined from the second configuration size range.

[0074] Obtain the initial model of the main body and the second configuration size range; wherein, the second configuration size range is the mesoscopic configuration size range of the part of the main body to be optimized. As an example, the part of the main body to be optimized forms a lattice configuration after optimization (including but not limited to...). Figure 14 , 15 The first configuration size range can be the range of rod diameter, unit cell size, and overall thickness of the lattice configuration. The initial body model, the main body constraints, and the second configuration size range are input into the calculation software to obtain the second optimal configuration size. The calculation software is used to calculate the second optimal configuration size from the second configuration size range so that the initial body model meets the main body constraints. The main body constraints are constraints on the weight and frequency of the initial body model. As an example, the main body constraints are to reduce the weight of the initial body model to a second proportional range (e.g., 30%-50%) and the frequency to a maximum value. As another example, the main body constraints are to make the frequency of the initial body model meet a preset value (e.g., 60Hz) and the weight reach a minimum value.

[0075] As described in step S050, the main body optimization model of the main body structure 50 is generated based on the main body initial model and the second optimal configuration size.

[0076] The initial model of the main body is refined and filled according to the second optimal configuration size to obtain the optimized model of the main body.

[0077] Reference Figure 3 , 9 In one embodiment of this application, the main structure 50 includes a plate structure 51 and a single-unit device 52 connected to the plate structure 51, the bracket 60 is connected to the plate structure 51, and the plate structure 51 has the main body part to be optimized; the design method further includes:

[0078] S010. Obtain the initial model of the plate structure 51 and the initial model of the stand-alone device 52;

[0079] S020. Based on the initial model of the plate and the initial model of the single machine, generate the initial model of the main body structure 50.

[0080] As described in steps S010 and S020, the initial model of the plate structure 51 and the initial model of the stand-alone device 52 are obtained; based on the initial model of the plate structure and the initial model of the stand-alone device, the initial model of the main body structure 50 is generated.

[0081] Obtain the initial model of the board and the initial model of the single machine; perform conversion processing on the initial model of the single machine, and connect the converted initial model of the single machine with the initial model of the board to obtain the initial model of the main body.

[0082] In one embodiment of this application, the specific process of generating the main body initial model of the main body structure 50 based on the plate initial model and the single-machine initial model can be further described in conjunction with the following description:

[0083] Based on the initial single-machine model, the mass point model of the single-machine device 52 is generated;

[0084] The mass point model is connected to the initial plate model to obtain the initial body model.

[0085] In the embodiments of this application, by converting the initial model of the single machine into the mass point model, the computational complexity of the initial model of the main body can be reduced, avoiding the consumption of more computational resources and higher computational costs caused by directly utilizing the physical structure of the single machine device 52.

[0086] In one embodiment of this application, the specific process of generating the mass point model of the single-machine device 52 based on the initial single-machine model can be further described in conjunction with the following description:

[0087] Extract the mass and centroid coordinates of the initial single-machine model;

[0088] The mass point model is generated based on the mass and the centroid coordinates.

[0089] As an example, the mass M1 and centroid coordinates (x1, y1, z1) of the initial single-machine model are extracted, and the origin O1 of the single-machine coordinate system corresponding to the initial single-machine model is recorded; the origin O2 of the plate coordinate system corresponding to the initial plate model is recorded; the difference (Δx, Δy, Δz) between the origins of the coordinate systems corresponding to the initial single-machine model and the initial plate model is calculated using O1 and O2, thereby obtaining the coordinates (x1-Δx, y1-Δy, z1-Δz) of the mass point model in the plate coordinate system, and the mass point model with mass M1 is generated at the coordinates (x1-Δx, y1-Δy, z1-Δz) in the plate coordinate system.

[0090] Reference Figure 10In one embodiment of this application, the plate structure 51 is formed by a plurality of clamping plate assemblies 510. Each clamping plate assembly 510 includes a sandwich layer 511 and clamping plates 512 disposed opposite to each other on both sides of the sandwich layer 511. The sandwich layer 511 has the main body portion to be optimized. In this embodiment of the application, by placing the main body portion to be optimized between the two layers of clamping plates 512, the weight of the main body structure 50 can be effectively reduced, and subsequent processing can be facilitated.

[0091] Reference Figure 11 In one embodiment of this application, the bracket 60 includes a filling layer 61 and a frame 62 surrounding the filling layer 61. The filling layer 61 has the portion of the bracket to be optimized. In this embodiment, by concentrating the portion of the bracket to be optimized inside the frame 62, the weight of the bracket 60 can be effectively reduced, and subsequent processing can be facilitated.

[0092] Reference Figure 4 , 12 13. In one embodiment of this application, the design method further includes:

[0093] S150. Optimize the connection of the overall optimization model. Specifically, add connectors 520 between adjacent clamping plate assemblies 510 to ensure a stable connection between adjacent clamping plate assemblies 510; and fill the interlayer 511 with solid blocks 5111 at the positions corresponding to the stand-alone device 52 to ensure a stable connection between the plate structure 51 and the stand-alone device 52.

[0094] S160. Perform performance verification on the overall optimization model. Specifically, verify whether the frequency of the optimized overall optimization model meets the first constraint condition and whether the strength meets the requirements.

[0095] If the conditions are met, proceed to step S170 to generate the final optimized model of the satellite structure.

[0096] If not met, then execute S180 to modify the overall constraint conditions; and re-execute S130 to determine the first optimal configuration size of the support component to be optimized from the first configuration size range based on the overall initial model and the overall constraint conditions of the overall initial model.

[0097] In one embodiment of this application, the optimized portion of the support forms a hole configuration; the design method further includes:

[0098] The overall optimization model is smoothed. Specifically, the support optimization model in the overall optimization model is smoothed by filling and deleting to ensure the continuity of the support 60 and facilitate subsequent processing.

[0099] The overall optimization model is then validated. Specifically, the frequency and weight of the smoothed overall optimization model are checked to determine whether they meet the first constraint condition. If they do, the final optimized model of the satellite structure is generated and further processed. If they do not, the overall optimization model is modified and re-validated.

[0100] In a specific implementation of this application, the satellite structure includes a main structure 50 and a support 60; the main structure 50 includes a plate structure 51 and a single-unit device 52 connected to the plate structure 51; the support 60 is connected to the plate structure 51; the plate structure 51 is formed by a plurality of clamping plate assemblies 510; each clamping plate assembly 510 includes a sandwich layer 511 and clamping plates 512 disposed opposite to each other on both sides of the sandwich layer 511; the sandwich layer 511 has a main body part to be optimized; the support 60 includes a frame 62 and a filling layer 61 disposed inside the frame 62; the filling layer 61 has a support part to be optimized; the design method includes:

[0101] S010. Obtain the initial model of the plate structure 51 and the initial model of the stand-alone device 52.

[0102] S020. Based on the initial model of the plate and the initial model of the single machine, generate the initial model of the main body structure 50.

[0103] S030. Obtain the initial model of the main body structure 50 and the second configuration size range of the part of the main body to be optimized;

[0104] S040. Based on the initial model of the main body and the main body constraints of the initial model of the main body, determine the second optimal configuration size of the part of the main body to be optimized from the second configuration size range;

[0105] S050. Based on the initial model of the main body and the second optimal configuration dimensions, generate the main body optimization model of the main body structure 50;

[0106] S110. Obtain the main body optimization model of the main structure 50, the initial support model of the support 60, and the first configuration size range of the support to be optimized part;

[0107] S120. Based on the main body optimization model and the support initial model, generate the overall initial model of the satellite structure;

[0108] S130. Based on the overall initial model and the overall constraints of the overall initial model, determine the first optimal configuration size of the support component to be optimized from the first configuration size range;

[0109] S140. Based on the overall initial model and the first optimal configuration size, generate an overall optimized model of the satellite structure.

[0110] Reference Figure 5 This application illustrates a satellite structure design apparatus according to an embodiment of the present application. The satellite structure includes a main structure 50 and a support 60 connected to the main structure 50. The support 60 has a support portion to be optimized. The design apparatus includes:

[0111] The initial model acquisition module 310 is used to acquire the main body optimization model of the main structure 50, the initial model of the support 60, and the first configuration size range of the support to be optimized part;

[0112] The overall initial model generation module 320 is used to generate an overall initial model of the satellite structure based on the main body optimization model and the support initial model;

[0113] The first configuration size determination module 330 is used to determine the first optimal configuration size of the support component to be optimized from the first configuration size range based on the overall initial model and the overall constraints of the overall initial model.

[0114] The overall optimization model generation module 340 is used to generate an overall optimization model of the satellite structure based on the overall initial model and the first optimal configuration size.

[0115] Reference Figure 6 In one embodiment of this application, the main structure 50 has a main body part to be optimized; the design device further includes:

[0116] The main body initial model acquisition module 230 is used to acquire the main body initial model of the main body structure 50 and the second configuration size range of the main body part to be optimized;

[0117] The second configuration size determination module 240 is used to determine the second optimal configuration size of the part of the main body to be optimized from the second configuration size range based on the main body initial model and the main body constraint conditions of the main body initial model;

[0118] The main body optimization model generation module 250 is used to generate the main body optimization model of the main body structure 50 based on the main body initial model and the second optimal configuration size.

[0119] Reference Figure 7In one embodiment of this application, the main structure 50 includes a plate structure 51 and a single-unit device 52 connected to the plate structure 51, the bracket 60 is connected to the plate structure 51, and the plate structure 51 has the main body part to be optimized; the design device further includes:

[0120] The initial model acquisition module 210 is used to acquire the initial model of the plate structure 51 and the initial model of the single device 52.

[0121] The main body initial model generation module 220 is used to generate the main body initial model of the main body structure 50 based on the plate initial model and the single machine initial model.

[0122] In one embodiment of this application, the subject initial model generation module 220 includes:

[0123] The mass point model generation module is used to generate the mass point model of the single machine device 52 based on the initial single machine model.

[0124] The main body initial model generation submodule is used to connect the mass point model with the plate initial model to obtain the main body initial model.

[0125] In one embodiment of this application, the mass point model generation module includes:

[0126] The single-machine initial model extraction submodule is used to extract the mass and centroid coordinates of the single-machine initial model;

[0127] The mass point model generation submodule is used to generate the mass point model based on the mass and the centroid coordinates.

[0128] As the device embodiment is basically similar to the method embodiment, the description is relatively simple, and relevant parts can be found in the description of the method embodiment.

[0129] Reference Figure 8 This illustration shows a computer device provided in an embodiment of the present application; the computer device 12 is manifested in the form of a general-purpose computing device, including: one or more processors or processing units 16, memory 28, and a bus 18 connecting different system components (including memory 28 and processing units 16).

[0130] Bus 18 represents one or more of several bus architectures, including a memory bus or memory controller, a peripheral bus, a graphics acceleration port, a processor, or a local bus using any of the various bus architectures. For example, these architectures include, but are not limited to, the Industry Standard Architecture (ISA) bus, the Micro Channel Architecture (MAC) bus, the Enhanced ISA bus, the Audio / Video Electronics Standards Association (VESA) local bus, and the Peripheral Component Interconnect (PCI) bus.

[0131] Computer device 12 typically includes a variety of computer system readable media. These media can be any available media that can be accessed by computer device 12, including volatile and non-volatile media, removable and non-removable media.

[0132] Memory 28 may include computer system readable media in the form of volatile memory, such as random access memory 30 and / or cache memory 32. Computer device 12 may further include other removable / non-removable, volatile / non-volatile computer system storage media. By way of example only, storage system 34 may be used to read and write non-removable, non-volatile magnetic media (commonly referred to as a "hard disk drive"). Figure 8 Not shown, a disk drive for reading and writing to a removable non-volatile disk (such as a "floppy disk") and an optical disk drive for reading and writing to a removable non-volatile optical disk (such as a CD-ROM, DVD-ROM, or other optical media) may be provided. In these cases, each drive may be connected to bus 18 via one or more data media interfaces. The memory may include at least one program product having a set (e.g., at least one) of program modules 42 configured to perform the functions of the embodiments of this application.

[0133] A program / utility 40 having a set (at least one) of program modules 42 may be stored, for example, in memory. Such program modules 42 include—but are not limited to—an operating system, one or more application programs, other program modules 42, and program data. Each or some combination of these examples may include an implementation of a network environment. Program modules 42 typically perform the functions and / or methods described in the embodiments of this application.

[0134] Computer device 12 can also communicate with one or more external devices 14 (e.g., keyboard, pointing device, display 24, camera, etc.), and with one or more devices that enable an operator to interact with the computer device 12, and / or with any device that enables the computer device 12 to communicate with one or more other computing devices (e.g., network card, modem, etc.). This communication can be performed through I / O interface 22. Furthermore, computer device 12 can also communicate with one or more networks (e.g., local area network (LAN)), wide area network (WAN), and / or public networks (e.g., the Internet) via network adapter 20. Figure 8 As shown, network adapter 20 communicates with other modules of computer device 12 via bus 18. It should be understood that, although... Figure 8 Not shown, it can be combined with computer device 12 to use other hardware and / or software modules, including but not limited to: microcode, device drivers, redundant processing unit 16, external disk drive array, RAID system, tape drive and data backup storage system 34, etc.

[0135] The processing unit 16 executes various functional applications and data processing by running programs stored in memory 28, such as implementing a satellite structure design method as provided in any of the above embodiments.

[0136] That is, when the processing unit 16 executes the above program, it can at least achieve the following: obtaining the main body optimization model of the main structure 50, the initial support model of the support 60, and the first configuration size range of the support to be optimized part; generating the overall initial model of the satellite structure based on the main body optimization model and the initial support model; determining the first optimal configuration size of the support to be optimized part from the first configuration size range based on the overall initial model and the overall constraints of the overall initial model; and generating the overall optimization model of the satellite structure based on the overall initial model and the first optimal configuration size.

[0137] In one embodiment of this application, a computer-readable storage medium is also provided, on which a computer program is stored, which, when executed by a processor, implements a satellite structure design method as provided in any of the above embodiments.

[0138] That is, when the program is executed by the processor, it can at least achieve the following: obtaining the main body optimization model of the main structure 50, the initial support model of the support 60, and the first configuration size range of the support to be optimized; generating the overall initial model of the satellite structure based on the main body optimization model and the initial support model; determining the first optimal configuration size of the support to be optimized from the first configuration size range based on the overall initial model and the overall constraints of the overall initial model; and generating the overall optimization model of the satellite structure based on the overall initial model and the first optimal configuration size.

[0139] Any combination of one or more computer-readable media may be used. A computer-readable medium can be a computer-readable signal medium or a computer-readable storage medium. A computer-readable storage medium can be, for example—but not limited to—an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples (a non-exhaustive list) of computer-readable storage media include: an electrical connection having one or more wires, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof. In this document, a computer-readable storage medium can be any tangible medium that contains or stores a program that can be used by or in connection with an instruction execution system, apparatus, or device.

[0140] Computer-readable signal media may include data signals propagated in baseband or as part of a carrier wave, carrying computer-readable program code. Such propagated data signals may take various forms, including—but not limited to—electromagnetic signals, optical signals, or any suitable combination thereof. Computer-readable signal media may also be any computer-readable medium other than computer-readable storage media, capable of transmitting, propagating, or transmitting programs for use by or in connection with an instruction execution system, apparatus, or device.

[0141] Computer program code for performing the operations of this application can be written in one or more programming languages ​​or a combination thereof. These programming languages ​​include object-oriented programming languages—such as Java, Smalltalk, and C++—and conventional procedural programming languages—such as the "C" language or similar programming languages. The program code can be executed entirely on the operator's computer, partially on the operator's computer, as a standalone software package, partially on the operator's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving remote computers, the remote computer can be connected to the operator's computer via any type of network—including a local area network (LAN) or a wide area network (WAN)—or can be connected to an external computer (e.g., via the Internet using an Internet service provider). The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably.

[0142] Reference Figure 9-16 This illustration shows a satellite structure provided by an embodiment of the present application. The satellite structure is designed by the design method described in any of the above embodiments and includes: a main structure 50 and a support 60 connected to the main structure 50. The main structure 50 is provided with a main optimized part, and the support 60 is provided with a support optimized part.

[0143] In one embodiment of this application, the bracket 60 includes a filling layer 61 and a frame 62 surrounding the filling layer 61, wherein the filling layer 61 has the portion of the bracket to be optimized.

[0144] In one embodiment of this application, the main structure 50 includes a plate structure 51 and a single device 52 connected to the plate structure 51. The bracket 60 is connected to the plate structure 51. The plate structure 51 is formed by a plurality of clamping plate assemblies 510. The clamping plate assembly 510 includes a sandwich layer 511 and clamping plates 512 disposed opposite to each other on both sides of the sandwich layer 511. The sandwich layer 511 is provided with the main body optimization part.

[0145] In one embodiment of this application, the plate structure 51 further includes a connector 520; adjacent clamping plate assemblies 510 are connected via the connector 520. By providing the connector 520, a stable connection between adjacent clamping plate assemblies 510 can be achieved.

[0146] In one embodiment of this application, the interlayer 511 is further provided with a solid block 5111; the solid block 5111 corresponds to the position of the stand-alone device 52. By setting the solid block 5111, a stable connection between the plate structure 51 and the stand-alone device 52 can be achieved.

[0147] In one embodiment of this application, the bracket 60 further includes a sub-plate 63; the sub-plate 63 is connected to the frame 62. By providing the sub-plate 63, it is convenient for the bracket 60 to be connected to other devices.

[0148] In one embodiment of this application, the optimized portion of the support is a perforated configuration. Specifically, the perforated configuration includes, but is not limited to, […]. Figure 12 The hole configuration is shown in the figure.

[0149] In one embodiment of this application, the optimized main body portion is a lattice configuration. Specifically, the lattice configuration includes, but is not limited to, those described above. Figure 15 , 16 The dot matrix configuration shown in the figure.

[0150] In one embodiment of this application, a method for fabricating a satellite structure is also provided. The satellite structure is designed by the design method described in any of the above embodiments. The fabrication method includes:

[0151] The main structural entity is obtained by processing according to the main body optimization model. Specifically, the plate structure entity is obtained by processing according to the plate optimization model in the main body optimization model, and the single-machine equipment entity is connected to the plate structure entity to obtain the main structural entity.

[0152] The scaffold entity is obtained by processing according to the scaffold optimization model in the overall optimization model.

[0153] The main structural entity is connected to the support entity to obtain the satellite structural entity. Specifically, the main structural entity and the support entity are connected by means of integral molding or bolt fixing to obtain the satellite structural entity.

[0154] Although preferred embodiments of the present application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of the embodiments of the present application.

[0155] Finally, it should be noted that in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or terminal device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or terminal device. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or terminal device that includes said element.

[0156] The above provides a detailed description of the satellite structure design method and satellite structure provided in this application. Specific examples have been used to illustrate the principles and implementation methods of this application. The description of the above embodiments is only for the purpose of helping to understand the method and core ideas of this application. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of this application. Therefore, the content of this specification should not be construed as a limitation of this application.

Claims

1. A method for designing a satellite structure, characterized in that, The satellite structure includes a main structure and a support connected to the main structure. The support has a section to be optimized, and the main structure has a section to be optimized. The main structure includes a plate structure and a single unit connected to the plate structure. The support is connected to the plate structure, and the plate structure has the section to be optimized. The design method includes: Obtain the initial model of the plate structure and the initial model of the stand-alone device; Based on the initial model of the plate and the initial model of the single machine, the initial model of the main body is generated; specifically, based on the initial model of the single machine, the mass point model of the single machine is generated; the mass point model is connected to the initial model of the plate to obtain the initial model of the main body; the step of generating the mass point model of the single machine based on the initial model of the single machine specifically includes: extracting the mass and centroid coordinates of the initial model of the single machine; generating the mass point model based on the mass and the centroid coordinates; Obtain the initial model of the main structure and the second configuration size range of the part of the main structure to be optimized; Based on the initial model of the main body and the main body constraints of the initial model of the main body, the second optimal configuration size of the part of the main body to be optimized is determined from the second configuration size range; Based on the initial model of the main body and the second optimal configuration dimensions, a main body optimization model of the main body structure is generated; Obtain the main body optimization model of the main structure, the initial support model of the support, and the first configuration size range of the support to be optimized; Based on the main body optimization model and the initial support model, an overall initial model of the satellite structure is generated; Based on the overall initial model and the overall constraints of the overall initial model, the first optimal configuration size of the support component to be optimized is determined from the first configuration size range; Based on the overall initial model and the first optimal configuration dimensions, an overall optimized model of the satellite structure is generated.

2. The design method according to claim 1, characterized in that, The plate structure is formed by several clamping plate assemblies. Each clamping plate assembly includes a sandwich layer and clamping plates disposed opposite each other on both sides of the sandwich layer. The sandwich layer contains the main body part to be optimized.

3. The design method according to claim 1, characterized in that, The support includes a filling layer and a frame surrounding the periphery of the filling layer, and the filling layer has the part of the support to be optimized.

4. The design method according to claim 1, characterized in that, The main constraint condition is to reduce the weight of the initial model of the main body to the second proportional range and to achieve the maximum frequency.

5. The design method according to claim 1, characterized in that, The overall constraint condition is to reduce the weight of the overall initial model to a first proportional range and to achieve the maximum frequency.

6. A design device for a satellite structure, characterized in that, The satellite structure includes a main structure and a support connected to the main structure. The support has a section to be optimized, and the main structure has a section to be optimized. The main structure includes a plate structure and a single unit connected to the plate structure. The support is connected to the plate structure, and the plate structure has the section to be optimized. The design device includes: The initial model acquisition module is used to acquire the initial model of the plate structure and the initial model of the single-machine device. The main body initial model generation module is used to generate the main body initial model of the main structure based on the plate initial model and the single-machine initial model; The main body initial model acquisition module is used to acquire the main body initial model of the main body structure and the second configuration size range of the main body part to be optimized. The second configuration size determination module is used to determine the second optimal configuration size of the part of the main body to be optimized from the second configuration size range based on the initial model of the main body and the main body constraints of the initial model of the main body; The main body optimization model generation module is used to generate the main body optimization model of the main body structure based on the main body initial model and the second optimal configuration size; The initial model acquisition module for the support is used to acquire the main body optimization model of the main structure, the initial model of the support, and the first configuration size range of the part of the support to be optimized. The overall initial model generation module is used to generate an overall initial model of the satellite structure based on the main body optimization model and the support initial model; The first configuration size determination module is used to determine the first optimal configuration size of the support component to be optimized from the first configuration size range based on the overall initial model and the overall constraints of the overall initial model. The overall optimization model generation module is used to generate an overall optimization model of the satellite structure based on the overall initial model and the first optimal configuration size; The main body initial model generation module includes: The mass point model generation module is used to generate the mass point model of the single machine based on the initial single machine model. The main body initial model generation submodule is used to connect the mass point model with the plate initial model to obtain the main body initial model; The mass point model generation module includes: The single-machine initial model extraction submodule is used to extract the mass and centroid coordinates of the single-machine initial model; The mass point model generation submodule is used to generate the mass point model based on the mass and the centroid coordinates.

7. A satellite structure, characterized in that, The satellite structure is designed by the design method according to any one of claims 1-5, and includes: a main structure and a support connected to the main structure, wherein the main structure has a main optimized part and the support has a support optimized part.

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