Test piece modeling method, device and apparatus, storage medium and test piece

Abstract

The embodiment of the invention relates to a modeling method, device and apparatus for simulating a test piece of a solar wing substrate, a storage medium and the test piece. The test piece is of a metal truss structure, and the method comprises the steps of conducting finite element analysis on a to-be-simulated solar wing substrate to acquire a mechanical analysis result; wherein the to-be-simulated solar wing substrate t is a solar wing substrate actually used in a spacecraft; obtaining the plane size of the to-be-simulated solar wing substrate and the mass of the to-be-simulated solar wing; and by taking the mechanical analysis result as an optimization target and the plane size and the quality as constraint conditions, optimizing the section size of the part forming the truss structure and the layout style of the truss structure, thereby obtaining the test piece. The processing period of the test piece is shortened, the test cost is reduced, the mechanical property of the test piece is matched with that of a solar wing substrate actually used in a spacecraft, and the safety risk caused by the fact that a real solar wing substrate is adopted for testing is avoided.

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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