A FEM APPROACH TO THE DYNAMIC MODEL OF THE VEGA SRMs

An innovative FEM-based methodology for the investigation of the dynamic behavior of a Solid Rocket Motor is presented. The work has been performed in the frame of Vega Launch Vehicle Program. The aim of this European program, sponsored by ESA, is to design and qualify a small Launch Vehicle (1.5 tons of payload in LEO). Advanced composite case (filament wounded) are developed to increase the performance of the three SRM stages. The propellant mass is the major fraction, above 95 % at ignition, of the whole motor mass. Therefore the technique adopted to model dynamically the propellant is a relevant factor for an accurate evaluation of SRM global behaviors.