OPTIMIZATION OF GRAIN AND NOZZLE GEOMETRY IN SOLID ROCKET BOOSTER GSLV

The project upgrades the GSLV Mk III solid booster via a high density composite propellant (65% bimodal AP, 18% spherical Al, 12% HTPB binder including 1.5% additives) augmented with 1% copper chromite, 1% lecithin, 1% TEPANOL and 2% iron oxide, achieving 1,795 kg/m³. An 8 lobed finocyl grain with tapered fins gives a large initial surface area for rapid pressurization and a progressive neutral burn over ~110-120 s; the grain is carbon fiber reinforced to withstand up to 12 MPa. A flex nozzle with 0.61 m throat, 15:1 expansion (exit Ø 2.36 m), and a carbon carbon throat coated with ZrC is optimized for sea level/vacuum. Predicted performance: 5,800 kN thrust, exhaust velocity =2,714 m/s, Isp =277 s, mass flow =2,138 kg/s.

Autorentext
Mr. Prasanth S serves as Assistant Professor of Aerospace Engineering at Agni College of Technology, Chennai, Tamil Nadu, India.Mr. Mohammed Nadhim I, Mr. Anto Cletus L, and Mr. Deepan C are final-year Aerospace Engineering students at the same institution, with strong interests in Orbital Mechanics and Aerodynamics.