Abstract
The processes of crack propagation and branching in burning solid propellants are not as yet well understood. These processes could be vitally instrumental in creating large specific-surface areas for burning, and could cause rocket motor failure. Propellant samples have been recovered from interrupted-burning experiments. Different modes of crack propagation and/or branching were observed. Depending upon the rate of pressurization, these modes are: unidirectional crack propagation; single-crack propagation accompanied by branching from various locations; and multiple branching in various directions from the initial crack-tip region. The crack-propagation problem is analyzed through the use of basic physical principles, experimental results, and Schapery's theory of crack propagation. A set of governing dimensionless parameters which control and characterize the degree of damage has been obtained. The controlling dimensionless parameter has been found to depend strongly upon the igniter strength, the chamber pressurization rate, and the fracture energy of the propellant. This set of parameters can be used to develop guidelines for safe operating conditions of rocket motors.
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