This work describes the application of original computer graphics methods to examine the effect of inclusions within the solid rocket motor thrust chamber. The adoptance of a dynamic three-dimensional triangular mesh with a self-intersection removal algorithm, as the core of the burning surface regression module, allows the aforementioned target to be reached. Many phenomena not measurable in an analytical closed form, like different-shaped voids within the grain, can be investigated. Indeed, both local heterogeneities and surface imperfections could generate unexpected variations in the combustion chamber pressure pattern and early thermal protections exposure. The aforementioned techniques are developed and tested on a ballistic simulator developed using computer graphics methods to improve mesh handling. Simulation results are carried out and discussed.

Numerical studies intended to predict solid rocket motors anomalies are the major contributors when developing strategies to both limit expensive fire tests and to investigate and understand the physical phenomena from which anomalies can arise. This paper aims to present a mathematical–physical method to evaluate the pressure peak, namely Friedman Curl, occurring at the tail-off phase of small-scale rocket motors. Such phenomenon is linked to the grain solid particles arrangement (i.e., packing effect); indeed, those particles show a tendency to accumulate at a certain distance from the metallic case, implying a local burn rate increment and a combustion chamber pressure rise close to the tail-off phase. Comparisons between experimental and simulated combustion chamber pressure profiles are outlined to prove the effectiveness of the mathematical–physical approach. Simulations were carried out with an internal ballistic simulation tool developed by the authors of this work.