Burning-rate modifier effects on a modified polyvinyl chloride-based propellants

Combustion of the composite solid rocket propellants series known as Flexol ite and various additives were studied. All of the Flexolite series of prop ellants are based on ammonium perchlorate as oxidizer and modified polyviny l chloride as binder. Several burning-rate modifiers were utilized separate ly in basic propellant formulations, to determine their effects on propella nt burning rate. It was shown that burning-rate modifiers have a substantia l effect on the burning rate, increasing it in dependence of their amount i n propellant formulation. Influence of one new burning-rate modifier is sho wn on both nonaluminized and aluminized formulations and is compared with o ther standard modifiers. Also, the influence of plasticizers on propellant burning rate of nonaluminized propellant with a new burning-rate modifier i s shown. All burning rates were measured in a special test motor at differe nt pressures, using small-motor measurement method.