A comprehensive analysis algorithm for ablation, temperature fields, and thermal stresses of carbon-based nosetip materials

This paper provides the principles for calculations of ablation, conduction, and thermal stresses of flight vehicles in a re-entry environment, as well as a few techniques beyond these principles. In regards to the chemical reactions of carbon-based material ablative surfaces, a selective calculation result is used to simplify the thermochemical ablation calculations. A spaced and non-spaced three-level explicit difference scheme was chosen for use in the calculation of temperature fields. Thermal stresses were calculated using the finite element method within the hypothesis of linear elasticity, based on the incomplete principles of variational potential energy, wherein it is possible to calculate the influences of many different types of displacement boundary conditions. During compilation of these comprehensive analysis procedures, an automated mesh dividing technique was found which has application in selective calculations.