S8  Engenharia Aeroespacial    Titulo: PROTEÇÃO TÉRMICA ABLATIVA NO PONTO DE ESTAGNAÇÃO EM CORPOS DE REENTRADA   Resumo : ABSTRACT. ABLATIVE THERMAL PROTECTION IS MAINLY USED IN THE AEROSPACE INDUSTRY. IT´S A COMPLEX PHENOMENON INVOLVING HEAT AND MASS TRANSFER, PHASE CHANGE MOVING BOUNDARY. ITS MATHEMATICAL MODELING LEADS TO A NONLINEAR SYSTEMS OF PARTIAL DIFFERENTIAL EQUATIONS. TO SOLVE SUCH A SYSTEM WE USED THE GENERALIZED INTEGRAL TRANSFORM TECHNIQUE, GITT, FOR AN ONE-DIMENTIONAL SLAB PROBLEM. THE EIGENVALUE PROBLEM ASSOCIATED TO THE ABLATIVE PHASE, IS TRANSIENT AND SPATIALITY DEPENDENT. THE EXTERNAL BOUNDARY IS SUBJECTED TO A TRANSIENT HEAT FLUX AS AN EXPONENTIAL FUNCTION OF TIME. AFTER THE INTEGRAL TRANSFORMATION OF THE PROBLEM WE GOT A INFINITY COUPLED SYSTEM OF ORDINARY DIFFERENTIAL EQUATIONS THAT CAN BE SOLVED BY KNOWN NUMERICAL TECHNIQUES. KEYWORDS: ABLATION PROCESS, PHASE CHANGE, HIPERSONIC FLIGHT SPEED, THERMAL PROTECTION     Autores : Campos Silva, João Batista Diniz, Antonio João Nagata, Carla 0 Pessoa Filho, José B.     Trabalho Completo :   COBEM99 | Comissão  Organizadora | Palestras | Sessões Técnicas | Autor | Simpósios e Sessões Especiais | Revisores |  Título  dos  Trabalhos | Local