Solid Propellant Grain Configuration with Progressive Burning Obtained Through Additive Manufacturing

Abstract

Abstract In this paper, a solid propellant grain concept was defined, obtained through additive manufacturing, which combines characteristics of multilayer elements with those of tubular geometric shape. The internal ballistics model adapted for such a solid propellant grain configuration allowed the calculations and highlighted the possibility of obtaining a pressure-time curve with a slightly increasing variation (progressive burning). The case studies carried out had as their starting point the existing physical configuration of the solid rocket motor for S-5K unguided ammunition. For the latter, PRTF-100 double base propellant was replaced by a composite propellant consisting of 87.3 wt% ammonium dinitramide, 10.7 wt% polycaprolactone and 2 wt% copper oxide.