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 elements code. The work has developed suitable numerical Fortran subroutines to assign radiation and convection boundary conditions. The thermal behaviour of the structures is presented.
Gori, F., De Stefanis, M., Worek, W., Minkowycz, W. (2008). Transient thermal analysis of Vega launcher structures. APPLIED THERMAL ENGINEERING, 28(17-18), 2159-2166 [10.1016/j.applthermaleng.2007.12.023].
Transient thermal analysis of Vega launcher structures.
GORI, FABIO;
2008-01-01
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 elements code. The work has developed suitable numerical Fortran subroutines to assign radiation and convection boundary conditions. The thermal behaviour of the structures is presented.File in questo prodotto:
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