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SOLID PROPELLANT ROCKET MOTOR COMPONENTS
SAŠA ŽIVKOVIĆ Military Technical Institute, Belgrade, e-mail: sasavite@yahoo.com MILORAD SAVKOVIĆ Military Technical Institute, Belgrade, e-mail: savkovic.milorad@gmail.com NIKOLA GLIGORIJEVIĆ Military Technical Institute, Belgrade, e-mail: nikola.gligorijevic@gmail.com
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Abstract: geometric – gas dynamics method for optimal chamber pressure determination, for solid propellant rocket motor, is described. Optimization criterion is minimum initial motor weight. The method gives the motor components basic geometry parameters. This is very useful in the design initial phase. The method’s simplicity allows different concept solutions comparison. The geometry parameters mathematic models were explained in detail. Dual thrust phase and two-chamber rocket motors were calculated and compared for example.
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