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Thermal Decomposition and Ablation Analysis of Solid Rocket Propulsion  

Kim, Yun-Chul (국방과학연구소 1기술연구본부 6부)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.14, no.5, 2010 , pp. 32-44 More about this Journal
Abstract
A two-dimensional thermal response and ablation analysis code for predicting charring material ablation and shape change on solid rocket nozzle is presented. The thermogravimetric analysis (TGA) techniques have been used to characterize the thermal decomposition constants for Arrhenius parameters. Two heterogeneous reactions involving carbon and the oxidizing species of $H_2O$ and $CO_2$ are considered and determined by Zvyagin's ablation model and kinetic constants. The moving boundary problem and mesh moving are solved by remeshing-rezoning method in MSC-Marc-ATAS program. The difference between the calculated and experimental value of char and ablation thickness is up to 20%. For the performance prediction of thermal protection systems, this method will be integrated with a three-dimensional finite-element thermal and structure analysis code through the real time sensing of in-depth temperature and heat flux.
Keywords
TGA; Thermal Decomposition; Ablation; Solid Rocket Nozzle;
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