Обоснование выбора материалов для крыла суборбитального многоразового космического аппарата туристического класса

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Т.Г. Агеева, К.В. Михайловский
12 Инженерный журнал: наука и инновации # 10·2016
Substantiation of the choice of materials for the wing
of tourist class suborbital reusable space vehicle
© T.G. Ageyeva, K.V. Mikhaylovskiy
Bauman Moscow State Technical University, Moscow, 105005, Russia
The article presents the results of numerical simulation of the thermal conditions of the
wing of a hybrid polymer composite material for tourist class reusable space vehicle to
fly on a suborbital trajectory.Calculations performed by finite element analysis, using the
universal software system ANSYS Workbench 16.0, provide the temperature distribution
on the surface of the wing corresponding to the stage of vehicle descentin the atmos-
phere. It became clear that thermal-protective coating must be used at the edges of the
wing and the type of coating was a result of finite element simulation classes
of polymeric matrix materials, suitable for the manufacture of hybrid composite wing skins,
and carbon composite spar were identified, and the honeycomb filling material used in the
wing skin was selected, using thermal condition numerical simulation methods.
Keywords: reusable space vehicle, thermal conditions, wing, hybrid composite material,
simulation.
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