539.3 Coupled modeling of high-speed aerothermodynamics and internal heat and mass transfer in composite aerospace structures

Dimitrienko Y. I. (Bauman Moscow State Technical University), Koryakov M. N. (Bauman Moscow State Technical University), Yurin Y. V. (Bauman Moscow State Technical University), Zakharov A. A. (Bauman Moscow State Technical University), Sborschikov S. V. (Bauman Moscow State Technical University), Bogdanov I. O. (Bauman Moscow State Technical University)

COUPLED PROBLEMS, AEROTHERMODYNAMICS, HEAT AND MASS TRANSFER, THERMAL DESTRUCTION, COMPOSITE MATERIALS, PORE PRESSURE, ABLATION, THERMAL PROTECTION, NUMERICAL MODELING


doi: 10.18698/2309-3684-2021-3-4261


A coupled problem of high-speed aerothermodynamics and internal heat and mass transfer in heat-shielding structures of reentry spacecraft made of ablative polymer composite materials is considered. To determine the heat fluxes in the shock layer of the reentry vehicle, the chemical composition of the atmosphere is taken into account. The mathematical formulation of the conjugate problem is formulated and an algorithm for the numerical solution is proposed. An example of the numerical solution of the problem for the reentry spacecraft Stardust is presented. It is shown that taking into account chemical reactions in the gas flow around the surface of the reentry vehicle is essential for the correct determination of the gas temperature in the boundary layer. It is also shown that the developed numerical method for solving the problem makes it possible to determine the parameters of phase transformations in a heat-shielding structure depending on the heating time, in particular, it allows calculating the pore pressure field of gaseous products of thermal decomposition of a polymer composite, which, under certain conditions, can lead to material destruction.


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