This paper presents a three dimensional numerical code for the analysis of Solid Rocket Motor (SRM) pre-ignition transient. For motors with a 3D star-shaped "finocyl" region and high energy igniter, like the first three stages of the new European launcher "Vega", experimental results and preliminary quasi-1D and axisymmetric simulations show that this operative phase can be characterized by strong unsteady phenomena with the possible presence of nocive pressure oscillations inside the combustion chamber. Therefore in order to accurately design such kink of SRM the prediction capabilities of these pressure fluctuations has to be improved. A three dimensional (both cylindrical and rectangular coordinates), inviscid, compressible and multicomponent solver (named EoS) has been developed. It is based on a finite-volume Godunov-like scheme and adopts a cartesian structured grid. The code is written in Fortran 95 with Object Oriented style to ensure flexibility and easy maintenance/improvement (adding sub-models, parallelization etc). Some validation tests are presented. Also a preliminary analysis of Pre-Ignition Transient of a SRM, with a comparison between the experimental head-end pressure time-history and the numerical one, is presented.

3D Numerical Simulation of Ignition Transient in SRM / Favini, Bernardo; Zaghi, Stefano; F., Serraglia; DI GIACINTO, Maurizio. - 8:(2006), pp. 6029-6047. ((Intervento presentato al convegno AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference tenutosi a Sacramento; United States nel July 9-12, 2006.

3D Numerical Simulation of Ignition Transient in SRM

FAVINI, Bernardo;ZAGHI, STEFANO;DI GIACINTO, Maurizio
2006

Abstract

This paper presents a three dimensional numerical code for the analysis of Solid Rocket Motor (SRM) pre-ignition transient. For motors with a 3D star-shaped "finocyl" region and high energy igniter, like the first three stages of the new European launcher "Vega", experimental results and preliminary quasi-1D and axisymmetric simulations show that this operative phase can be characterized by strong unsteady phenomena with the possible presence of nocive pressure oscillations inside the combustion chamber. Therefore in order to accurately design such kink of SRM the prediction capabilities of these pressure fluctuations has to be improved. A three dimensional (both cylindrical and rectangular coordinates), inviscid, compressible and multicomponent solver (named EoS) has been developed. It is based on a finite-volume Godunov-like scheme and adopts a cartesian structured grid. The code is written in Fortran 95 with Object Oriented style to ensure flexibility and easy maintenance/improvement (adding sub-models, parallelization etc). Some validation tests are presented. Also a preliminary analysis of Pre-Ignition Transient of a SRM, with a comparison between the experimental head-end pressure time-history and the numerical one, is presented.
AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
Ignition transients; Multicomponent solvers; Solid Rocket Motor (SRM)
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
3D Numerical Simulation of Ignition Transient in SRM / Favini, Bernardo; Zaghi, Stefano; F., Serraglia; DI GIACINTO, Maurizio. - 8:(2006), pp. 6029-6047. ((Intervento presentato al convegno AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference tenutosi a Sacramento; United States nel July 9-12, 2006.
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/359247
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