It is sometimes recommended to use the ablation materials for the outer skin of rocket body to protect the construction from the aerodynamic heating and also some ablation materials can be used as the heat insulation coating inside the cylinder wall of solid propellant rocket motors. General theory of ablation is very complicated, since it is the combination of the theories of both aerodynamics and heat conduction. However, in the case of laminated foil construction, which we propose in this papare, we can simplify considerably the problem, since the gasifying of the material and the existence of thermal layer in the solid phase of the material can be neglected. Test results by the torch burner method have shown a good agreement with the simplied theory shown in the report.
積層箔のアブレーション特性について
SA4135007.pdf
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