Temperature state analysis and design of thermal protection of a tourist class space shuttle wing from hybrid composite material

Аuthors

Ashikhmina E. R.^*, Ageyeva T. G., Prosuntsov P. V.^**

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

*e-mail: katrin‑katushka@yandex.ru
**e-mail: pavel.prosuntsov@mail.ru

Abstract

The article considers the issues of thermal design of a wing composite structure from polymer composite material for the suborbital tourist class space shuttle. The data on thermo‑physical characteristics of the wing covering materials were obtained by numerical modeling of heat exchange in the representative volume element of materials. Aerodynamic flow‑around modeling and determining the external heat loading, acting on the spacecraft wing and shell while its reentering, were performed with the special software. The results of temperature state analysis allowed reveal the necessity of the thermal protective layer application. The material based on aluminum silicate, called “spheroplastic”, was selected for such kind of protection. To enhance the spacecraft structural and technological perfection the problem on obtaining the spheroplastic optimal distribution over the wing surface was solved. By the thermal protection parametric optimization its rational distribution ensuring the spacecraft workability was obtained.

Keywords:

thermal design, space tourism, thermal protection

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