Investigation on the effect of ZrC additive on the combustion instability of HTPB based solid composite propellants

Combustion instability in a composite solid propellant rocket motor is a phenomenon whichcan be considered to be occurring when the actual chamber pressure observed in the rocketmotor exceeds, while operating in the manner intended, the chamber pressure for which themotor was designed, based on propellant burn rate data obtained from small motor or strandburningtests. [1] Initial stability predictions indicated the motor would be stable due to thehigh aluminum content in the formulation. But propellants with Al powder are smoky. [2] intactical rocket motors, the production of smoke is disadvantageous. The production of smokefacilitates tracking the source of the launched rocket by enemy forces. [3]In this experience, we try to investigate the effect of ZrC additive on the combustioninstability of a smokeless HTPB based propellant.