This work describes the application of a new three-dimensional ballistic model, named ROBOOST (ROcket BOOst Simulation Tool), developed at the Laboratory Propulsion and Mechanics of the University of Bologna (Department of Industrial Engineering), to the Vega - Zefiro 9 Solid Rocket Motor, manufactured by the Avio company in Colleferro (Rome). The code uses an original graphical approach and a point-by-point description of the propellant burning surface regression. The main purpose of the newly developed model is to investigate non homogeneous behaviors of the surface regression rate or non-isotropic characteristics of the grain. A zero-dimensional unsteady thermo-dynamic model, coupled with a mono-dimensional quasi-steady one, computes the internal fluid-dynamics of the combustion chamber and contributions by igniter, nozzle erosion and thermal protections ablation are also considered. Comparisons with reference curves and experimental data, in terms of volume and surface regression and mean pressure time evolution, have been performed and final results are presented and discussed.
Numerical Simulation of the Zefiro 9 Performance Using a New Dynamic SRM Ballistic Simulator
BERTACIN, ROBERTO;PONTI, FABRIZIO;CORTI, ENRICO;FEDELE, DOMENICO;
2013
Abstract
This work describes the application of a new three-dimensional ballistic model, named ROBOOST (ROcket BOOst Simulation Tool), developed at the Laboratory Propulsion and Mechanics of the University of Bologna (Department of Industrial Engineering), to the Vega - Zefiro 9 Solid Rocket Motor, manufactured by the Avio company in Colleferro (Rome). The code uses an original graphical approach and a point-by-point description of the propellant burning surface regression. The main purpose of the newly developed model is to investigate non homogeneous behaviors of the surface regression rate or non-isotropic characteristics of the grain. A zero-dimensional unsteady thermo-dynamic model, coupled with a mono-dimensional quasi-steady one, computes the internal fluid-dynamics of the combustion chamber and contributions by igniter, nozzle erosion and thermal protections ablation are also considered. Comparisons with reference curves and experimental data, in terms of volume and surface regression and mean pressure time evolution, have been performed and final results are presented and discussed.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
