Numerical Analysis of the Thermal Stress State of a Transverse Isotropic Heat Shield of the Aerospace Vehicle

Abstract

The validity of the mathematical simulation results of the thermal stress state of the aerospace vehicle heat shield depends on the reliability of the assessment of used materials thermal characteristics, as well as on the correctness of the selected mathematical models of the heat fluxes, temperature and stress fields distribution. Using the example of a transversely isotropic composite thermal protective material consisting of an isotropic matrix made of glass-carbon and inclusions of transversally isotropic pyrographite, the article discusses methods for constructing of bilateral (top and bottom) estimates of its characteristics. For calculations, a layered structure is selected, formed by alternating stages of high-temperature vapor deposition of pyrographite layers from the gas phase and deposition of glass carbon layers. Based on the finite element method, a numerical analysis of the heat stressed state of the heat protective coating of the descent vehicle returning to Earth after the completion of the Lunar expedition is carried out. The Apollo-class descent vehicle is considered as an example. To obtain an upper estimate of the intensity
of thermal loads, the descent of the spacecraft with zero angle of attack, i.e., with zero aerodynamic quality, is considered. The efficiency of using a layer of the described composite structurally sensitive material is shown in comparison with a two-layer package made up of separate layers of the same materials

This work was supported by the Ministry of Science and Higher Education of the Russian Federation (project FSFN-2024-0004)

Please cite this article in English as:

Leonov V.V., Zarubin Vl.S. Numerical analysis of the thermal stress state of a transverse isotropic heat shield of the aerospace vehicle. Herald of the Bauman Moscow State Technical University, Series Natural Sciences, 2025, no. 1 (118), pp. 30--45 (in Russ.). EDN: DBNXSB

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