| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 649213 | Applied Thermal Engineering | 2008 | 8 Pages |
Abstract
A transient thermal analysis is carried out to verify the base cover thermal protection system of Vega 2nd stage Solid Rocket Motor (SRM) and the flange coupling of the inter-stage 2/3. The analysis is performed with a finite element code. The work has developed suitable numerical Fortran subroutines to assign radiation and convection boundary conditions. The thermal behaviour of the structures is presented.
Related Topics
Physical Sciences and Engineering
Chemical Engineering
Fluid Flow and Transfer Processes
Authors
F. Gori, M. De Stefanis, W.M. Worek, W.J. Minkowycz,