Modeling method, device, equipment, storage medium and test piece of a test piece

Abstract

The embodiments of the present application relate to a modeling method, device, equipment, storage medium and test piece for simulating a test piece of a solar wing substrate. The above-mentioned test piece is a truss structure made of metal, and the method includes: performing finite element analysis on the solar wing substrate to be simulated to obtain mechanical analysis results; wherein, the solar wing substrate to be simulated is the solar wing substrate actually used in the spacecraft; The plane size of the solar wing substrate and the quality of the solar wing to be simulated; taking the above mechanical analysis results as the optimization target, and the plane size and quality as constraints, optimize the cross-sectional size of the components forming the truss structure and the layout style of the truss structure, so that Get the test piece. This method shortens the processing cycle of the test piece, reduces the test cost, and makes the mechanical properties of the test piece match the solar wing substrate actually used in the spacecraft, avoiding the safety risk caused by using the real solar wing substrate for testing .

Description

technical field [0001] The present application relates to the field of satellite technology, in particular to a modeling method, device, equipment, storage medium and test piece for simulating a test piece of a solar wing substrate. Background technique [0002] At present, when carrying out the solar wing deployment mechanism test or the whole star structure appraisal test, some use the real solar wing substrate structure for the test, and the real solar wing substrate structure refers to the final solar wing substrate acceptance part or the spare part for additional production. However, the real solar wing substrate is mostly a honeycomb sandwich structure in the form of carbon fiber skin-aluminum honeycomb core-carbon fiber skin, which has a long processing cycle and cannot meet the requirements of civil aerospace for the development cycle; The price is relatively expensive, and if the acceptance test is used, it may have unknown adverse effects on the structural performa...

AI Technical Summary

Problems solved by technology

However, the real solar wing substrate is mostly a honeycomb sandwich structure in the form of carbon fiber skin-aluminum honeycomb core-carbon fiber skin, which has a long processing cycle and cannot meet the requirements of civil aerospace for the development cycle; The price is relatively expensive, and if the acceptance parts are used for testing, it may have unknown adverse effects on the structural performance of the final product. If more spare parts are additionally produced, it will increase the cost of satellite design

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