Numerical Simulation of Cook-off Characteristic of Solid Rocket Motor in Different Flame Environments

doi:10.3969/j.issn.1000-1093.2015.09.006

Abstract

Abstract: In order to study the thermal safety problems of solid rocket motor in unexpected flame environment, a two-dimensional model for cook-off of a small solid rocket motor is established, in which the composite solid propellant AP/HTPB is taken as a loading object. The cook-off characteristics of the solid rocket motor are calculated in 800 K, 1 000 K and 1 200 K flame environments, respectively. The results show that the initial ignition position of AP/HTPB is occurred in an annular region on the outer wall of propellant close to the nozzle. With the improvement of the flame temperature, the ignition delay period is shortened quickly, and the ignition temperature is gradually increased. Heat insulating effect of the insulating layer increases as the flame temperature increases. The initial slow decomposition temperature of AP component in the composite solid propellant increases with the increase in flame temperature.

Key words: ordnance science and technology, thermal safety, flame environment, cook-off, solid rocket motor, solid propellant, AP/HTPB, numerical calculation

CLC Number:

YANG Hou-wen, YU Yong-gang, YE Rui. Numerical Simulation of Cook-off Characteristic of Solid Rocket Motor in Different Flame Environments[J]. Acta Armamentarii, 2015, 36(9): 1640-1646.

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