Temperature sensitivity of solid heterogeneous rocket propellant AP/HTPB/AI

Abstract

The results of research on solid heterogeneous rocket propellant (SHRP) containing: ammonium chlorate(VII) (AP) as an oxidant, a binder based on liquid synthetic rubber, i.e. hydroxylterminated polybutadiene (HTPB), aluminium (Al) and technological additives in a laboratory rocket motor (LRM) are presented to determine the thermal sensitivity of the propellant.