[en] High-fidelity models have been developed in the recent years to predict the response of light-weight ablative thermal protection materials used to build heat shields of re-entry capsules. Because the main components of these ablators are typically also present in some spacecraft/satellite components, there is a growing interest in exploring the possible extension of the high-fidelity models to predict demisability of these components. A unified approach simulating the degrading composite material and the high enthalpy flow is extended to treat this type of charring dense material interesting for demise applications. The comparison in between
highly porous and dense material shows the numerical challenges to simulate the thermal response of composite carbon fibers materials using this methodology.
Disciplines :
Aerospace & aeronautics engineering
Author, co-author :
Schrooyen, Pierre; Cenaero
Hillewaert, Koen ; Université de Liège - ULiège > Département d'aérospatiale et mécanique > Design of Turbomachines
Turchi, Alessandro; von Karman Institute for Fluid Dynamics
Helber, Bernd; von Karman Institute for Fluid Dynamics
Walpot, Louis; European Space Agency
Magin, Thierry; von Karman Institute for Fluid Dynamics
Language :
English
Title :
Numerical Investigation of Charring Material Demisability in Atmospheric Entry Conditions
Publication date :
2019
Event name :
International Conference on Flight vehicles, Aerothermodynamics and Re-entry Missions and Engineering (FAR)
Event organizer :
ESA
Event place :
Monopoli, Italy
Event date :
30 September - 3 October 2019
Audience :
International
Main work title :
Proceedings of the International Conference on Flight vehicles, Aerothermodynamics and Re-entry Missions and Engineering (FAR)