Abstract
In the paper a general mathematical description of the flow in the internal chamber of solid rocket motors is presented. The formulation adopted take into account the multi-species and multiphase, reactive, multidimensional characteristics of the flow. The grain combustion is described by a pressure dependent law; aluminum droplet are modelled by a Lagrangian approach, coupled with the Eulerian formulation adopted for the gas phase. The mathematical model has been implemented in a simulation code and several simulations have been performed; in particular in the paper the results for two geometries are described: a simple cylindrical port-area rocket and the Zefiro 9 SRM.
Original language | English |
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Publication status | Published - 3 Nov 2009 |
Event | 6th European Symposium Aerothermodynamics for Space Vehicles - Versailles, France Duration: 3 Nov 2008 → 6 Nov 2008 |
Conference
Conference | 6th European Symposium Aerothermodynamics for Space Vehicles |
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Country/Territory | France |
City | Versailles |
Period | 3/11/08 → 6/11/08 |