Finite element modeling of thermal stresses in aerospace structures from polymer composite materials

The conjugate problem of aerodynamics and heat and mass transfer in heat-shielding structures made of ablating polymer composite materials is considered. To determine the heat fluxes in the shock layer, the chemical composition of the atmosphere is taken into account. A mathematical formulation of t...

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Bibliographic Details
Published in:E3S web of conferences 2023-01, Vol.376, p.1033
Main Authors: Dimitrienko, Yuriy, Koryakov, Mikhail, Yurin, Yuriy, Sborshchikov, Sergey, Bogdanov, Ilya
Format: Article
Language:English
Subjects:
Aerodynamic heating
Aerodynamics
Algorithms
Chemical composition
Composite materials
finite element
Finite element method
Heat flux
Heat transfer
High temperature
Mass transfer
mathematical formulation
polymer composite material
Polymer matrix composites
Polymers
Reentry shielding
Spacecraft
Spacecraft shielding
Thermal stress
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Summary:The conjugate problem of aerodynamics and heat and mass transfer in heat-shielding structures made of ablating polymer composite materials is considered. To determine the heat fluxes in the shock layer, the chemical composition of the atmosphere is taken into account. A mathematical formulation of the joint problem is formulated and an algorithm for numerical solution is proposed. An example of a numerical solution of the problem for the reentry spacecraft Stardust is presented. It is shown that due to the high temperatures of aerodynamic heating of a structure made of a polymer composite material, an intense internal generation of gas appears in the structure of the material, which can lead to the destruction of the material.
ISSN:2267-1242
2555-0403
2267-1242
DOI:10.1051/e3sconf/202337601033