A comprehensive analysis algorithm for ablation, temperature fields, and thermal stresses of carbonbased nosetip materials
Abstract
This paper provides the principles for calculations of ablation, conduction, and thermal stresses of flight vehicles in a reentry environment, as well as a few techniques beyond these principles. In regards to the chemical reactions of carbonbased material ablative surfaces, a selective calculation result is used to simplify the thermochemical ablation calculations. A spaced and nonspaced threelevel 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.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 November 1985
 Bibcode:
 1985STIN...8623879H
 Keywords:

 Ablative Materials;
 Ablative Nose Cones;
 Carbonaceous Materials;
 Temperature Distribution;
 Thermal Stresses;
 Algorithms;
 Chemical Reactions;
 Difference Equations;
 Elastic Properties;
 Environments;
 Finite Element Method;
 Hypotheses;
 Linearity;
 Nose Tips;
 Pant Program;
 Potential Energy;
 Pyrolytic Graphite;
 Reentry Effects;
 Reentry Vehicles;
 Thermochemistry;
 Transient Heating;
 Variational Principles;
 Fluid Mechanics and Heat Transfer