1. A single solid propellant is evaluated: HTBP 1912 and this propellant consists of 19% aluminum, 12% hydroxyl terminated polybutadiene (HTBP) and 69% ammonium perchlorate (AP). The HTBP 1912 propellant is used in the P-80, Z-23 and Z-9 SRMs for the Vega launch vehicle. The thermodynamic characteristics of the propellant are calculated with NASA's Glenn Equilibrium Program (CEA).25,26For simplicity, a constant burn rate, chamber pressure and altitude thrust are assumed. From sensitivity analysis it follows that for the models used in this study a regressive burning grain did not enhance the performance of the launch vehicle. C. Geometry model
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