ABSTRACT
The combustion behavior, flammability limits and ballistic properties, of composite
low oxygen content propellants were studied experimentally by using propellant
formulations based on hydroxy-terminated polybutadiene pre-polymer (HTPB) /
ammonium perchlorate oxidizer (AP). Higher pressures and AP contents as well as
smaller AP particle size were found to promote sustained combustion and to increase
burning rate. The addition of aluminum powder (Al) as a metallic fuel and copper
chromite (CC), burning rate accelerator, caused an increase in the burning rate. A
significant increase of burning rate was recorded when CC added to the aluminized
formulations compared with the non-aluminized of the same oxidizer solid loading
and particle size.