An Experimental Investigation of Pressure Oscillations and Their Suppression in Subscale Hybrid Rocket Motors

摘要

Mechanisms contributing to combustion instability and methods for stabilizing combustion in hybrid rocket motors using a gaseous oxygen/hydroxyl terminated polybutadiene (HTPB) propellant system are discussed. Experimental data are presented and correlated with flow field analyses to show that the most probable cause of observed instabilities in subscale motors using gaseous oxidizers derives from inadequate flame holding, resulting in a coupling of combustion processes with the motor's first longitudinal acoustic oscillation mode.