Efficiency assessment of glassy-carbon application as a re-entry spacecraft multi-layer thermal-protective coating protection

Аuthors

Zarubin V. S.^*, Leonov V. V.^**

Bauman Moscow State Technical University, MSTU, 5, bldg. 1, 2-nd Baumanskaya str., Moscow, 105005, Russia

*e-mail: vszarubin@gmail.com
**e-mail: lv-05@mail.ru

Abstract

In this paper crucial information of thermal protection coating outer surface heat transfer conditions for spherical space vehicle descending from orbit is provided. Thermal protection coating is made of materials with high degree of anisotropy of thermal conductivity with purpose to create more uniform distribution of thermal energy, applied to coating surface. Additionally, thermophysical properties of used materials are provided. With this data, quantitative analysis of multilayered thermal protection coating is conducted. Analysis results confirm possibility of creation non-destructible thermal protection coating, that could be re-used multiple times during descent of space vehicle from orbit, with usage of existing materials.

Keywords:

heat transfer conditions of thermal protection coating, anisotropic material, thermal protection coating, ballistic capsule

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