Open AccessAblative Heating Technology in Hypersonic Re-entry Vehicles and Cruise Aircrafts
Author(s) -
Ali Asgar*,
Sai Sarath,
Jerrin Thadathil Varghese
Publication year - 2019
Publication title -
international journal of recent technology and engineering
Language(s) - English
Resource type - Journals
ISSN - 2277-3878
DOI - 10.35940/ijrte.c4844.098319
Subject(s) - astronautics , space shuttle thermal protection system , aerospace engineering , heat shield , spacecraft , hypersonic flight , hypersonic speed , atmospheric entry , thermal protection , aerodynamic heating , aeronautics , engineering , cruise , thermal insulation , missile , materials science , physics , heat transfer , layer (electronics) , composite material , thermodynamics
The aim of researches conducted in thermal protection systems in aeronautics and astronautics field of engineering is to generally defend the craft from high heat loads during operation while operating at hypersonic regimes in air and space. The motive of the following composition is to draft a review analysis on ablative heating materials as thermal protective equipment on reusable planetary/atmospheric re-entry vehicles such as a space shuttle, an inter-continental ballistic missile, or a hypersonic cruise missile. The heat liberation can cause much damage to the aircraft/spacecraft whilst operation which is generally beyond repair. It is therefore of utmost importance to research multiple strategy to reduce the effect of shockwaves damage to spacecraft/aircraft materials. We shall initiate the analysis by mentioning some re-usable tile thermal protection system types such as high temperature reusable surface insulation tiles (H.R.S.I), fibrous refectory composite insulation tiles (F.R.C.I), low temperature reusable surface insulation tiles (L.R.S.I) and gradually move on to ablative thermal protection systems with the advent of reinforced carboncarbon’s application in astronautics and aeronautics respectively.