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S8 Engenharia Aeroespacial |
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Title:
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PROTEÇÃO TÉRMICA ABLATIVA NO PONTO DE ESTAGNAÇÃO EM CORPOS DE REENTRADA
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Summary :
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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
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Author :
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Campos Silva, João Batista
Diniz, Antonio João
Nagata, Carla 0
Pessoa Filho, José B.
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Paper View :
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