Research on the simulation technology of the combined effects of transient thermal shock and a triaxial 6-DOF

During the reentry of a spacecraft, it will encounter extreme environment of transient thermal shock and a triaxial 6-DOF. Currently, there is a lack of experimental verification means. Taking a second power supply as an example, the finite element simulation model is established, and the model is v...

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Bibliographic Details
Published in:Journal of physics. Conference series 2020-09, Vol.1633 (1), p.12068
Main Authors: Yao, Zemin, Huang, Xiaokai, Huang, Shouqing, Liu, Shouwen
Format: Article
Language:English
Subjects:
Coupling
Extreme environments
Finite element method
Heat balance
High temperature
Low temperature
Mathematical models
Physics
Random vibration
Simulation
Spacecraft
Strain
Stress-strain relationships
Thermal response
Thermal shock
Thermal simulation
Verification
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Summary:During the reentry of a spacecraft, it will encounter extreme environment of transient thermal shock and a triaxial 6-DOF. Currently, there is a lack of experimental verification means. Taking a second power supply as an example, the finite element simulation model is established, and the model is verified by the heat balance test and random vibration modal test. The thermal response distribution of rapid temperature change, low-temperature holding and high-temperature holding phrases is obtained through the transient thermal shock simulation; Based on the multi-stress simulation of the workbench, the stress-strain response distribution under the triaxial 6-DOF random vibration is obtained. According to the principle of stress coupling, the thermal response distribution matrix and stress-strain response distribution matrix are applied to the finite element model of electronic products at the same time, and then the transient thermal shock and the triaxial 6-DOF coupling simulation is realized, which provides a theoretical guidance for test verification of the extreme environment during the reentry of a spacecraft.
ISSN:1742-6588
1742-6596
DOI:10.1088/1742-6596/1633/1/012068