This paper presents results obtained in a program designed to develop guidelines for pulsing solid propellant rocket motors to determine their susceptibility to finite amplitude disturbances. A series of motor firings was conducted in which sphetes of different sizes and materials were ejected through the nozzle to simulate inf light partial nozzle blockage due to igniter, propellant or other combustion chamber material fragments. Simple laboratory scale solld rocket motors with full and partial length grains were utilized. All of the motors tested were triggered into sustained nonlinear instability. A simple analysis was developed to calculate the velocity of the ejecta and pulse duration. Gaod ogreement between predicted and measured pulse durations was obtained. Two methods were developed for predicting initial ejecta induced pulse amplitudes: a simple model based on linear wave propagation theory and the assumption of quaslsteady nozzle behavior, and a numerical model which utillzes the quasi-steady nozzle assumption to provide a nozzle entrance boundary condition to a comprehensive combustion chamber nonlinear instability analysis. Comparisons of theoretical predictions with experimental data for both pulse amplitude and the motor response to pulsing are presented. Tht nonlinear instability analysis was found to be capable of predicting the complete range of nonlinear behavior observed in motor response to ejecta pulsing. Good agreement between measured and predicted initi pulse (amplitude and harmonic content), waveform evo ution, growth and decay rates, and DC shift was obtained. p'