Certificate of Registration Media number Эл #ФС77-53688 of 17 April 2013. ISSN 2308-6033. DOI 10.18698/2308-6033
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Thermal conditions analysis of the front composite wing edge of a small-size aerospace vehicle

Published: 24.09.2018

Authors: Bodnya I.S., Timoshenko V.P.

Published in issue: #9(81)/2018

DOI: 10.18698/2308-6033-2018-9-1805

Category: Aviation and Rocket-Space Engineering | Chapter: Design, construction and production of aircraft

Heat-resistant composite materials are widely used for reusable aerospace vehicles constructions to provide effective heat protection for load-carrying structure elements. We conducted thermal analysis for one of the types of thermal-protective coating (TPC), heat-resistant porous ceramics based on Al2O3 fibre, to estimate the impact of external atmospheric pressure on the temperature field inside porous TPC. We used the front wing edge of a small-size space vehicle as a simulated construction. We developed  a mathematical simulation which considers the fact that TPC heat conductivity depends on temperature and pressure during the whole faze of vehicle reentry in the atmosphere. According to the results of calculations based on this model we educed 15% difference between temperature peak levels of load-carrying structure and simulation model. Simulation model TCP heat conductivity depends on temperature under a pressure of 101.325 kPa  (1 atm). Judging by the results we concluded that external atmospheric pressure is one of the main factors which must be taken into consideration while designing porous TPC for reusable aerospace vehicles

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