Preliminary research of composite rocket propellants with hexogen and titanium oxide powder

Abstract

Composite solid propellants based on ammonium perchlorate/hydroxyl-terminated polybutadiene/isophorone dyisocyanate including two levels of hexogen (RDX) are presented in this paper. The mass of RDX increased in relation to oxidant, with constant bimodal fraction ratio. Combustion of the propellants was improved by adding of titanium (IV) oxide powder as stabilizer. Parameters of burning rate laws and apparent viscosity values were determined and compared for the propellants of the same total solid phase. Calculations of thermochemical parameters are also given in this research.

Keywords

• composite solid propellant
• ammonium perchlorate
• hydroxyl-terminated polybutadiene
• hexogen
• titanium (iv)oxide
• ballistic characteristics
• thermochemical parameters