Cast composite solid propellants with different combustion stabilizers

Abstract

The effect of four different compounds as the combustion stabilizers of composite solid propellants based on the AP/HTPB/IPDI has been presented in this paper. Except that, various total solid content, ammonium-perchlorate bimodal and trimodal combination of particle sizes ratio have been made by preparing the eleven formulations. For all of them, the burning rate law's parameters and temperature sensitivity, uniaxial mechanical characteristics, apparent viscosity of uncured propellants and physic-chemical and energetic values have been determined and compared.

Keywords

• composite solid propellant
• composite rocket propellant
• cast propellant
• combustion stability
• stabilizers
• aluminium
• zirconium carbide
• titanium oxide
• antimony oxide
• temperature sensitivity
• burning rate