Investigação dos efeitos causados na taxa de queima e no impulso específico de propelentes sólidos pela adição de óxido de ferro

Abstract

Considering the applicability of solid propellants on professional, amateur or academic rockets, it is necessary an investigation about methods to enhance these propellants’ performance. This work presents an investigation of the effects caused on the burn rate and specific impulse of four solid propellants – KNSU, KNDX, KNSB and KNXY – with the insertion of iron oxide. Therefore, burn rate tests at atmospheric pressure and static tests using a class G rocket motor were made in order to identify which percentage of iron oxide could induce an enhancement on the propellant’s performance. It was observed that the insertion of 1% or 2% of iron oxide can increase the burn rate by 43,7% and also the specific impulse by 64%.