An Analysis of a Charring ablation Thermal Protection System
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HOUSTON TX MANNED SPACECRAFT CENTER
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An analytical model is presented for predicting the transient one-dimensional thermal performance of a charring-ablator heat-protection system when exposed to a hyperthermal environment. The heat-protection system is considered to consist of a ablation material and backup structure. The ablating material is further considered to consist of three distinct regions or zones char, reacting, and virgin material. A FORTRAN IV digital computer program STAB II utilizing an implicit finite difference formulation has been written for the IBM 70940 computer system. The program considers one ablating material and a maximum of 12 back- up materials with conduction or radiation andor convection allowed between materials. Thermal properties of all materials are temperature dependent, with the properties of the charring material also being state dependent. The governing differential equations and their implicit finite difference formulation are presented. The program input and output are described in detail. The FORTRAN program statements and nomenclature are presented. Also, the theoretical and experimental results are compared.
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