D. E. Glass, “Ceramic Matrix Composite (CMC) Thermal Protection Systems (TPS) and Hot Structures for Hypersonic Vehicles,” 15th AIAA Space Planes and Hypersonic Systems and Technologies Conference, Dayton, 28 April- 1 May 2008, pp. 1-36.

has been cited by the following article:

• TITLE: Ablation Properties of C Fibers and SiC Fibers Reinforced Glass Ceramic Matrix Composites Upon Oxyacetylene Torch Exposure

  AUTHORS: Julien Beaudet, Jonathan Cormier, André Dragon, Magali Rollin, Guillaume Benoit

  KEYWORDS: Fiber, Ablation, High-Temperature Properties

  JOURNAL NAME: Materials Sciences and Applications, Vol.2 No.10, October 17, 2011

  ABSTRACT: The ablation properties of two laminated composites, having both a glass ceramic matrix and different kinds of fibers (C or SiC) with the same architecture, are evaluated and compared. Ablation tests are performed using an oxyacetylene torch on samples having two different thicknesses. Mass loss and ablation depth are measured after flame exposure. The results obtained show that the decomposition of SiC fibers during thermal exposure has a significant impact on ablation behavior. Oxidation of SiC produces a liquid SiO2 film at the top of the material during ablation. This leads to an improved ablation resistance compared to the glass ceramic matrix/C composite, especially in case of successive flame exposures where the SiO2 film consumes a substantial fraction of the heat flow during its liquefaction upon re-heating.