| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 4991314 | Applied Thermal Engineering | 2017 | 40 Pages |
Abstract
This article aims to describe an optimization procedure for the design of ablative heat shields. In particular, in the present work, the numerical method is applied to the ablative TPS of the hypersonic reentry capsule Stardust.
Related Topics
Physical Sciences and Engineering
Chemical Engineering
Fluid Flow and Transfer Processes
Authors
Aniello Riccio, Francesco Raimondo, Andrea Sellitto, Valerio Carandente, Roberto Scigliano, Domenico Tescione,