ABSTRACT
Increasing of velocity of gases inside solid rocket motors with low port-to-throat area
ratios, leading to increased occurrence and severity of burning rate augmentation
due to flow of propellant products across burning propellant surfaces (erosive
burring), erosive burning of high energy composite propellant was investigated to
supply rocket motor design criteria and to supplement knowledge of combustion
phenomena, pressure, burning rate and high velocity of gases all of these are
parameters affect on erosive burning, the used motor in the tests is 2 inch motor,
and a modified one with different grain dimensions, the tests show the pressure time
curve and the erosive burning phenomena.