Abstract
Charring ablators remain the premium choice for space exploration missions that involve atmospheric re-entry. This type of ablative material is composed of a carbon matrix, usually made of fibers, which is then impregnated with a resin. During re-entry, the high heat flux produced by convective heating causes the material to chemically react. First, the resin pyrolyzes, and is vaporized into a gas that travels through the material, and is eventually ejected at the surface. Then, as the temperature rises, the surface of the porous matrix recess through ablative processes. For re-entry conditions typical of space exploration missions, this is mainly diffusion limited oxidation. However, recent studies have shown that oxygen from the atmosphere actually penetrates a thin layer of the porous material, oxidizing the carbon fibers from within.
This research activity presents a volume-averaged fiber-scale oxidation model, based on the one previously developed by Lachaud et al. The present model, however, solves the momentum equation as well as the energy equation. Results based on a an experimental test case are presented. The importance of solving both equations is clearly demonstrated, and a new value for carbon fiber oxidation reactivity is suggested.
Document Type
Conference Proceeding
Publication Date
6-2013
Digital Object Identifier (DOI)
http://dx.doi.org/10.2514/6.2013-2636
Repository Citation
Martin, Alexandre, "Volume Averaged Modeling of the Oxidation of Porous Carbon Fiber Material" (2013). Mechanical Engineering Faculty Publications. 13.
https://uknowledge.uky.edu/me_facpub/13
Included in
Aerodynamics and Fluid Mechanics Commons, Computer Sciences Commons, Space Vehicles Commons
Notes/Citation Information
Published in the Proceedings of the 44th AIAA Thermophysics Conference, Paper 2013-2636, p. 1-11.
Copyright © 2013 by Alexandre Martin.
The copyright holder has granted the permission for posting the article here.