Thermal analysis of advanced ceramic coating on carbon/carbon substrates for aerospace re-entry re-usable structures
- Paper number
IAC-19,C2,8,2,x52019
- Author
Dr. Andrea Delfini, Italy, Sapienza University of Rome
- Coauthor
Prof. Oleg Alifanov, Russian Federation, Moscow Aviation Institute
- Coauthor
Prof. Aleksey V. Nenarokomov, Russian Federation, Moscow Aviation Institute
- Coauthor
Mr. Sergey Budnik, Russian Federation, Moscow Aviation Institute
- Coauthor
Dr. Alena V. Morzhukhina, Russian Federation, Moscow Aviation Institute (National Research University, MAI)
- Coauthor
Mr. Dmitry M. Titov, Russian Federation, Moscow Aviation Institute (State Technical University)
- Coauthor
Dr. Marta Albano, Italy, Agenzia Spaziale Italiana (ASI)
- Coauthor
Dr. Roberto Pastore, Italy, Sapienza University of Rome
- Coauthor
Prof. Fabio Santoni, Italy, Sapienza University of Rome
- Coauthor
Prof. Mario Marchetti, Italy, Sapienza University of Rome
- Coauthor
Mr. Paolo Marzioli, Italy, Sapienza University of Rome
- Coauthor
Mr. Andrea Gianfermo, Italy, Sapienza University of Rome
- Year
2019
- Abstract
Aim of the work is to analyze a novel coating process based on the ceramic varnish ‘Pyropaint’ applied on a TPS for re-entry application. The proposed treatment is due to preserve the thermo-mechanical properties of a Carbon/Carbon substrate from the detrimental space environment conditions, such as LEO thermal cycles, outgassing due to ultra-high vacuum, and Atomic Oxygen and UV irradiation. The first step is to analyze the coefficient of thermal expansion (CTE) by dilatometric measurement in order to evaluate the thermal stress of both the substrate and coating layer. Particular emphasis is devoted to the study of the effect of coating/substrate adhesion, which may result in anomalous mechanical behavior. Secondly, the manufactured assembly will be characterized in terms of thermal conductivity and thermal capacity by means of dedicated instrumentation. After thermal conditioning the specimens under test are investigated by full microscopy analysis using SEM/EDX techniques. The experimental results are then compared each other and with numerical simulations carried out by a mathematical modeling based on the inverse method. The present study paves the way for the future development of advanced structural spacecraft panels as well as for re-usable re-entry systems.
- Abstract document
- Manuscript document
IAC-19,C2,8,2,x52019.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.