Computer design of non-destructive thermal protection of spacecraft

Аuthors

Nenarokomov A. V.^1*, Titov D. M.^2**, Munoz Gonzalez V. ^2***

1. ,
2. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: nenarokomovav@mai.ru
**e-mail: d.titov@mai.ru
***e-mail: vivaldomg@yahoo.com.mx

Abstract

Design of distributed parameter systems, shape optimization and other free or moving boundary problems may be thought of as shape inverse problems, in which the positions of free boundaries are determined along with the solutions of field variables. In the case under consideration such conditions are constrains on the temperature values at the discrete points of the system. At presented paper algorithm for optimal design of multi-layer thermal insulation is consider. This algorithm based on a sequential quadratic programming (SQP) method. Results are presented how to apply the algorithm suggested for solving a practical problem — thickness sampling for a spacecraft thermal insulation system.

Keywords:

thermal protection, optimal design, mathematical model