Cook-off Characteristics of Solid Rocket Motor with AP/HTPE Propellant Charge

Abstract

Abstract Conducting thermal safety research on solid rocket motors is a method to effectively improve the battlefield survivability of rockets and missile weapons. Based on the AP-based cock-off reaction mechanism, a 2-D unsteady axial symmetrical model of solid rocket motor is developed. The software Fluent is used to calculate the numerical value of the rocket motor under thermal stimulation conditions of different heating rates. The results indicate that the heating rate of cook-off is negatively correlated with the ignition delay time of the motor, and there is no significant connection between ignition temperature and heating rate. But it is obvious that heating rate has a big impact on ignition position. In the slow cook-off numerical calculation, the initial ignition position appears near the propellant head. And the higher the heating rate, the closer the ignition position is to the propellant head. At rapid heating rate of 1.45K/s, the ignition position appears at the edge of the left end face of the propellant. When rapid heating rate is 1.75K/s or 1.95K/s, ignition position appears at the edge of the right end face of the propellant. At this time, the ignition position will change abruptly.