Satellite single-machine dynamics finite element result batch automatic extraction method and system

Abstract

The invention discloses a batch automatic extraction method and system for satellite stand-alone dynamics finite element results, relates to the technical field of satellite structure finite elements, and aims to solve the problems that manual extraction of the satellite stand-alone dynamics finite element results is huge in workload and prone to result errors at present. Preprocessing the single-machine geometric model, the single-machine matching table, the whole-satellite assembly model, the finite element model and the first solving file respectively; based on the single machine matching table, after single machine installation point coordinates in the whole satellite assembly model are extracted, a single machine geometric model installation point coordinate table is exported; based on the first solving file, the stand-alone geometric model installation point coordinate table and the stand-alone geometric model installation points, generating a finite element model installation point node table corresponding to the stand-alone geometric model installation point coordinate table, and outputting a second solving file; and based on the finite element model installation point node table and the second solving file, generating a result, enabling the result to correspond to the single machine, and outputting a chart result.

Description

Technical Field

[0001] This invention relates to the field of finite element technology for satellite structures, and specifically to a method and system for batch automated extraction of finite element results of satellite single-unit dynamics. Background Technology

[0002] Satellites primarily consist of systems including payloads, structure and mechanisms, power supply, attitude and orbit control, telemetry and command, data transmission, data management, overall circuitry, and integrated electronics, typically involving more than 30 individual units. In structural subsystem design, dynamic finite element simulation is an effective method for evaluating the design. It generally requires extracting the sinusoidal response curves and peak values ​​and frequencies of the maximum response points, as well as the random power spectral density curves and RMS values ​​for each input point of each individual unit. Since sinusoidal and random analyses are performed in three directions (X, Y, and Z), and the results are also divided into X, Y, and Z directions, the number of curves and results to be extracted in a single structural dynamics simulation can reach hundreds. Currently, the main method for extracting satellite individual unit dynamics finite element results is manual extraction and statistical analysis, which is extremely labor-intensive and prone to errors, affecting the designer's evaluation of the design. Furthermore, changes in satellite configuration and individual unit layout require repeated statistical analysis, making it a repetitive, tedious, and error-prone task for satellite structural designers.

[0003] Therefore, there is a need for a method and system for the batch automated extraction of finite element results of satellite single-unit dynamics, so that the extraction of dynamic results of satellite structural design can be automated and accurate, reducing the repetitive workload of satellite structural designers. Summary of the Invention

[0004] This invention addresses the problems of the current method of manually extracting finite element results of satellite single-unit dynamics, which involves a huge workload and is prone to errors.

[0005] The method for batch automated extraction of satellite single-unit dynamic finite element results according to the present invention includes the following steps: Step S1: Complete the preprocessing of the single-machine geometric model, single-machine matching table, whole-satellite assembly model, finite element model and first solution file respectively; Step S2: Based on the single-unit matching table, extract the coordinates of the single-unit installation points in the whole satellite assembly model and export the single-unit geometric model installation point coordinate table. Step S3: Based on the first solution file, the coordinate table of the installation points of the single-machine geometric model, and the installation points of the single-machine geometric model, generate a finite element model installation point node table corresponding to the coordinate table of the installation points of the single-machine geometric model, and output the second solution file; Step S4: Based on the finite element model, install the node table and the second solution file, generate the results and correlate them with the single machine, and output the graph results.

[0006] Furthermore, in one embodiment of the present invention, in step S2, the step of extracting the coordinates of the individual unit installation points in the overall satellite assembly model based on the individual unit matching table and then exporting the individual unit geometric model installation point coordinate table is specifically as follows: Iterate through each individual unit in the overall satellite assembly model. If the name of each individual unit matches the individual unit matching table, then export the coordinate table of the installation points of the individual unit's geometric model.

[0007] Furthermore, in one embodiment of the present invention, step S3, based on the first solution file, the coordinate table of the installation points of the single-machine geometric model, and the installation points of the single-machine geometric model, generates a finite element model installation point node table corresponding to the coordinate table of the installation points of the single-machine geometric model, and outputs a second solution file, including the following steps: Step S301: Read the first solution file and the coordinate table of the installation points of the single-machine geometric model, and find the installation point nodes of the single machine; Step S302: Based on the installation points and node numbers of the single-machine geometric model, generate a finite element model installation point node table corresponding to the coordinate table of the single-machine geometric model installation points; Step S303: Generate a node set set2 in fem format from the node numbers of the single-machine installation points, and output the second solution file.

[0008] Furthermore, in one embodiment of the present invention, the step S301 of finding the single-machine installation point node specifically includes: The MPC unit slave node with the smallest distance from the single-machine geometric model mounting point is the single-machine mounting point node.

[0009] Furthermore, in one embodiment of the present invention, step S4, which involves generating results based on the finite element model's installation point node table and the second solution file, and corresponding them with a single machine to output chart results, includes the following steps: Step S401: Calculate the second solution file and output the pch file; Step S402: Read the pch file and the finite element model installation point node table, generate the results and correspond them with the single machine, and output the graph results.

[0010] Furthermore, in one embodiment of the present invention, the chart results include charts categorized by the direction of the results, tables categorized by the direction of the results, charts categorized by single machine, and tables categorized by single machine.

[0011] The satellite single-unit dynamics finite element result batch automated extraction system of the present invention is based on the satellite single-unit dynamics finite element result batch automated extraction method described above, and includes the following modules: Module S1 performs preprocessing on the single-machine geometric model, single-machine matching table, whole-satellite assembly model, finite element model and first solution file respectively; Module S2, based on the single-unit matching table, extracts the coordinates of the single-unit installation points in the whole satellite assembly model and then exports the single-unit geometric model installation point coordinate table. Module S3, based on the first solution file, the coordinate table of the installation points of the single-machine geometric model, and the installation points of the single-machine geometric model, generates a finite element model installation point node table corresponding to the coordinate table of the installation points of the single-machine geometric model, and outputs the second solution file; Module S4, based on the finite element model, installs the node table and the second solution file, generates results and corresponds them to the single machine, and outputs the graphical results.

[0012] This invention addresses the problems of excessive workload and susceptibility to errors in manually extracting finite element analysis results for satellite single-unit dynamics. Specific beneficial effects include: 1. The automated batch extraction method for satellite single-unit dynamic finite element results described in this invention prepares the model and extracts the coordinates of the single-unit installation points in the satellite coordinate system based on the prepared model. It then exports the coordinate table of the installation points of the single-unit geometric model, extracts the corresponding nodes of the single-unit installation points in the geometric model of the finite element model, generates a finite element solution file, and finally submits the calculation solution file, result extraction and output. This method solves the problems of huge workload and easy error in the manual extraction and statistical analysis of the location of the satellite single-unit installation points in the geometric model and the node numbers in the finite element model. 2. The automated batch extraction method for satellite single-machine dynamics finite element results described in this invention solves the problems of large workload and easy error in the statistical analysis of satellite single-machine dynamics finite element results; 3. The automated batch extraction method for satellite single-machine dynamics finite element results described in this invention improves the automation level and efficiency of satellite single-machine dynamics finite element result extraction. Attached Figure Description

[0013] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the following description of the embodiments taken in conjunction with the accompanying drawings, wherein: Figure 1 This is a flowchart of the automated batch extraction method for satellite single-unit dynamic finite element results described in Example 1; Figure 2 This is a flowchart of the automated batch extraction system for satellite single-unit dynamic finite element results described in Example 2. Detailed Implementation

[0014] Various embodiments of the present invention will now be clearly and completely described with reference to the accompanying drawings. The embodiments described with reference to the drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0015] Example 1 Currently, the main method for extracting finite element analysis results for satellite unit dynamics is manual extraction and statistics, which is extremely labor-intensive and prone to errors in result statistics, affecting designers' evaluation of the design. Moreover, changes in satellite configuration and unit layout require repeated statistics, making it a repetitive, tedious, and error-prone task for satellite structure designers.

[0016] In order to solve the technical problems existing in the current technology, such as Figure 1 As shown in the figure, this embodiment proposes a method for automated batch extraction of finite element results of satellite single-machine dynamics, including the following steps: Step S1, Model Preparation: Complete the preprocessing of the single-unit geometric model, single-unit accessory table, whole-satellite assembly model, finite element model, and first solution file. Step S101: Establish a single-machine matching table, which includes the name of the single machine. The names of the single machines should not be repeated. Single machines with the same model should be distinguished in the naming. For example, the three magnetic torquers in three directions should be named X magnetic torquer, Y magnetic torquer and Z magnetic torquer respectively. Step S102: Adjust the name of the stand-alone geometric model to match the name in the stand-alone equipment table. Step S103: Establish a geometric point at the geometric center of the through-hole mounting surface of the single-machine geometric model, and ensure that the geometric point feature in the model is only the single-machine mounting point; Step S104: Complete the whole star assembly model using the pre-processed single-machine geometric model; Step S105, finite element model and first solution file preparation: The single-machine model is equivalently modeled using MPC elements with the mass point at the center of mass as the master node and the nodes at the installation point as slave nodes. The dynamic analysis step is completed, and an output node set set1 is established. The results of the dynamic analysis step in output node set set1 are set to pch format. The dynamic analysis step is a sinusoidal analysis step, or a stochastic analysis step, or a combination of sinusoidal and stochastic analysis steps. Each analysis step establishes analysis steps in the X, Y, and Z directions, and each analysis step outputs results in the X, Y, and Z directions.

[0017] The output node set1 contains random point information, which facilitates the modification of the solution file in subsequent steps; Step S106: After completing the finite element model, output the first solution file in “.fem” format.

[0018] Step S2: Extract the coordinates of the single-unit installation points in the satellite coordinate system and export the single-unit geometric model installation point coordinate table: Run the VB program in UG software to traverse each component in the whole star assembly model. If the component name is consistent with the single machine matching table, output the coordinates of the single machine installation point to the CSV file "single machine geometric model installation point coordinates.csv". The "single machine installation point coordinates.csv" file contains the name of the single machine and the coordinate information of each installation point.

[0019] Step S3: Extract the nodes corresponding to the single-machine installation points in the finite element model: Step S301: Python program 1 reads the first solution file and the "Single Machine Geometric Model Installation Point Coordinates.csv" file, finds the single machine installation point nodes, and saves the single machine geometric model installation points and single machine installation point node numbers as "Single Machine Installation Point Node Correspondence Table.csv"; The single-machine installation point node is the node closest to the installation point of the single-machine geometric model, and it is an MPC unit slave node. The specific steps for finding the single-machine installation point node are: traverse all MPC unit slave nodes in the entire satellite (with coordinates set to (X...). n ,Y n Z n ), and the distance (X) from the installation point coordinates of the single-machine geometric model (coordinates set as (X1, Y1, Z1)) to the distance (X) n- X1) 2 +(Y n- Y1) 2 +(Z n- Z1) 2 The smallest MPC unit is the single-machine installation point node; In step S302, Python program 1 generates a node set set2 in fem format from the node numbers of the single-machine installation point, replaces set1 in the first solution file, and outputs a second solution file in ".fem" format.

[0020] Step S4: Submit the calculation solution file, extract and output the results: Step S401: Submit the second solution file to Optistruct for calculation and output the pch file; Step S402: Python program 2 reads the pch file and "Single Machine Installation Point Node Correspondence Table.csv", matches the results with the single machine, and outputs the chart results.

[0021] The chart results may include: (1) The diagrams are classified according to the direction of the results; there are 9 diagrams in total, namely X-direction X component results, X-direction Y component results, X-direction Z component results, Y-direction X component results, Y-direction Y component results, Y-direction Z component results, Z-direction X component results, Z-direction Y component results, and Z-direction Z component results. The sinusoidal frequency response curve / random PSD curve results of the direction corresponding to the single-machine installation point node are plotted in the corresponding diagrams. (2) Tables classified by the direction of the results; divided into 9 tables: X-direction X component results, X-direction Y component results, X-direction Z component results, Y-direction X component results, Y-direction Y component results, Y-direction Z component results, Z-direction X component results, Z-direction Y component results, and Z-direction Z component results. The maximum value of the sinusoidal response and the frequency point / random RMS value of the direction corresponding to the single-machine installation point node are recorded in the corresponding tables. (3) Diagrams classified by single unit; each single unit is divided into 9 diagrams: X-direction X component result, X-direction Y component result, X-direction Z component result, Y-direction X component result, Y-direction Y component result, Y-direction Z component result, Z-direction X component result, Z-direction Y component result, and Z-direction Z component result. The sinusoidal frequency response curve / random PSD result of the direction corresponding to the single unit installation point node is plotted in the corresponding diagram. (4) The table is classified by single machine. Each single machine is divided into 9 columns of results: X-direction X component result, X-direction Y component result, X-direction Z component result, Y-direction X component result, Y-direction Y component result, Y-direction Z component result, Z-direction X component result, Z-direction Y component result, and Z-direction Z component result. The maximum value of the sinusoidal response in the direction corresponding to the single machine installation point node and the frequency point / random RMS value result are recorded in the corresponding table.

[0022] Therefore, the method described in this embodiment, through model preparation, completes the preprocessing of the single-unit geometric model, single-unit accessory table, whole satellite assembly model, finite element model, and first solution file; extracts the coordinates of the single-unit installation point in the satellite coordinate system; exports the single-unit geometric model installation point coordinate table; extracts the corresponding nodes of the single-unit installation point in the geometric model in the finite element model; and generates the finite element solution file and submits the calculation solution file, result extraction, and output. This solves the problems of huge workload and easy error in manually extracting the finite element results of satellite single-unit dynamics.

[0023] Example 2 The automated batch extraction system for satellite single-unit dynamic finite element results proposed in this embodiment is based on the automated batch extraction method for satellite single-unit dynamic finite element results described in Embodiment 1. Figure 2 As shown, it includes the following modules: Module S1, Model Preparation: Complete the preprocessing of the single-machine geometric model, single-machine matching table, whole-satellite assembly model, and the first solution file of the finite element model; Module S2, submit UG secondary development program VB program 1, and get "single machine geometric model installation point coordinates.csv"; Module S3 submits Python program 1, which reads "Single Machine Geometric Model Installation Point Coordinates.csv" and the first solution file to obtain the second solution file and "Single Machine Installation Point Node Correspondence Table.csv"; Module S4 submits the Optistruct solution to the second solution file and obtains the Pch result file; Module S5, submit Python program 2, read "Single Machine Installation Point Node Correspondence Table.csv" and Pch result file, and obtain the chart results.

[0024] The above provides a detailed description of the automated batch extraction method and system for satellite single-machine dynamic finite element results proposed in this invention. Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. 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 invention. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A method for batch automated extraction of finite element results of satellite single-unit dynamics, characterized in that, Includes the following steps: Step S1: Complete the preprocessing of the single-machine geometric model, single-machine matching table, whole-satellite assembly model, finite element model and first solution file respectively; Step S2: Based on the single-unit matching table, extract the coordinates of the single-unit installation points in the whole satellite assembly model and export the single-unit geometric model installation point coordinate table. Step S3: Based on the first solution file, the coordinate table of the installation points of the single-machine geometric model, and the installation points of the single-machine geometric model, generate a finite element model installation point node table corresponding to the coordinate table of the installation points of the single-machine geometric model, and output the second solution file; Step S4: Based on the finite element model, install the node table and the second solution file, generate the results and correlate them with the single machine, and output the graph results.

2. The method for batch automated extraction of satellite single-machine dynamic finite element results according to claim 1, characterized in that, In step S2, the step of extracting the coordinates of individual unit installation points from the overall satellite assembly model based on the individual unit matching table and then exporting the individual unit geometric model installation point coordinate table is as follows: Iterate through each individual unit in the overall satellite assembly model. If the name of each individual unit matches the individual unit matching table, then export the coordinate table of the installation points of the individual unit's geometric model.

3. The method for batch automated extraction of satellite single-unit dynamic finite element results according to claim 1, characterized in that, In step S3, based on the first solution file, the coordinate table of the mounting points of the single-machine geometric model, and the mounting points of the single-machine geometric model, a finite element model mounting point node table corresponding to the coordinate table of the mounting points of the single-machine geometric model is generated, and a second solution file is output, including the following steps: Step S301: Read the first solution file and the coordinate table of the installation points of the single-machine geometric model, and find the installation point nodes of the single machine; Step S302: Based on the installation points and node numbers of the single-machine geometric model, generate a finite element model installation point node table corresponding to the coordinate table of the single-machine geometric model installation points; Step S303: Generate a node set set2 in fem format from the node numbers of the single-machine installation points, and output the second solution file.

4. The method for batch automated extraction of satellite single-unit dynamic finite element results according to claim 3, characterized in that, In step S301, finding the single-machine installation point node specifically involves: The MPC unit slave node with the smallest distance from the single-machine geometric model mounting point is the single-machine mounting point node.

5. The method for batch automated extraction of satellite single-unit dynamic finite element results according to claim 1, characterized in that, In step S4, the process of generating results based on the finite element model's installation point node table and the second solution file, and corresponding them with a single machine to output graphical results, includes the following steps: Step S401: Calculate the second solution file and output the pch file; Step S402: Read the pch file and the finite element model installation point node table, generate the results and correspond them with the single machine, and output the graph results.

6. The method for batch automated extraction of satellite single-unit dynamic finite element results according to claim 1 or 5, characterized in that, The chart results include graphs categorized by the direction of the result, tables categorized by the direction of the result, graphs categorized by single machine, and tables categorized by single machine.

7. A batch automated extraction system for finite element results of satellite single-unit dynamics, wherein the system is based on the batch automated extraction method for finite element results of satellite single-unit dynamics as described in claim 1, characterized in that... Includes the following modules: Module S1 performs preprocessing on the single-machine geometric model, single-machine matching table, whole-satellite assembly model, finite element model and first solution file respectively; Module S2, based on the single-unit matching table, extracts the coordinates of the single-unit installation points in the whole satellite assembly model and then exports the single-unit geometric model installation point coordinate table. Module S3, based on the first solution file, the coordinate table of the installation points of the single-machine geometric model, and the installation points of the single-machine geometric model, generates a finite element model installation point node table corresponding to the coordinate table of the installation points of the single-machine geometric model, and outputs the second solution file; Module S4, based on the finite element model, installs the node table and the second solution file, generates results and corresponds them to the single machine, and outputs the graphical results.

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