Coupling and integrated simulation analysis method for thermal structure of solar battery wings

Abstract

The solar battery wing thermal structure coupling integrated simulation analysis method of the present invention is based on finite element grid division, and adopts the finite control volume method and the finite element method to respectively establish a solar battery wing on-orbit thermal analysis model and a mechanical model for structural thermal deformation analysis. The mesh division of the thermal analysis model is relatively sparse, and the scale of the model unit is controlled to realize the thermal analysis calculation. The mesh division of the mechanical model is relatively fine to meet the calculation accuracy of the thermal deformation analysis. Based on the uniform finite element mesh division method, the temperature result obtained from the thermal analysis model is smoothly mapped to the structural model as a load input by using the linear interpolation method, so that the analysis model and the structural analysis model can be organically combined.

Description

technical field [0001] The invention relates to the thermal structure coupling problem of the solar battery wing of a spacecraft, in particular to an integrated simulation analysis method for the thermal structure coupling of the solar battery wing. Background technique [0002] The solar battery wing is an important part of the spacecraft power system, and it is the main source of spacecraft energy supply. As a large-scale space structure outside the cabin, it is directly subjected to space thermal loads such as external heat flow and low temperature during the orbit, causing drastic changes in the orbital temperature of solar cell wing substrates, solar cells, and other parts. Such drastic temperature loads will cause solar The structural thermal deformation or even induced thermal vibration of each part of the solar cell wing may seriously affect the working performance of the solar cell wing and bring great challenges to the structural design of the solar cell wing and t...

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Problems solved by technology

However, in order to meet the accuracy requirements of thermal deformation analysis, the grid size of the finite element model is usually relatively large, which makes the amount of calculation and process data in the thermal analysis calculation very large, resulting in a long time for thermal calculation, and even the calculation cannot be performed. This method It is only suitable for the calculation and analysis of simple structures and small-scale mesh models. For large-scale structures such as solar cell wings, thermal-structural coupling calculations of unified finite element models cannot be performed.

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