Thermal Protection for a Re-Entry Vehicle Using Heat Ablation Process

The purpose of this paper is to study the Heat management problem of a re-entry vehicle and how can it be controlled by the means of using an effective Heat ablation process. It is very important to determine the type of ablative material to be used, only then it would ensure effective heat shielding. A rocket on re-entry into the earths atmosphere depends more on friction than the rocket power to slow down and due to this it experiences very high aerodynamic heating. In order to protect the interior of the rocket, its payload and essential electrical motors from damage the rockets have two systems of heat shields-1) Ablative layer of heat shield and 2) Thermal soak. The Ablative layer is made of plastic resin to protect the outer surface which is heated using a gas which transfers the heat by convection.