Solid Propellants for Propulsion System Including a Yellow Iron Oxide

Abstract

The present invention relates to a solid propellant used for propulsion machinery such as a rocket or a shell and, more specifically, to a solid propellant composition having a feature of a low pressure index value in a section where erosive combustion occurs rapidly by including 10-95 wt% of an oxidant, 0.1-20 wt% of a binder, 0.1-20 wt% of a hardener, 0.1-30 wt% of a plasticizer, 0.1-10 wt% of a binding agent, and 0.01-10 wt% of yellow iron oxide (FeOOH) as a combustion catalyst.