Propellant Combustion and Mathematical Modeling

 My research group focuses on combustion related projects with specific application to solid propellants. We investigate and model different phases of stable, unstable, and transient combustion. We have developed theoretical models to describe the steady-state combustion of all varieties of solid propellants in use today and have performed fundamental work on diffusion flames, applying it to solid propellant configurations. We have also done extensive work in modeling two-phase flow systems relative to the deflagration-to-detonation transition for solid explosives and propellants. Currently we are involved in both experimental and theoretical research on particle combustion. Particulates such as ZrC, A, and Al₂O₃ are used typically as additives for solid propellants to suppress acoustic oscillations. The basic physical mechanisms whereby the particles burn and suppress oscillations are not well understood. Our research is directed at expanding this understanding, using a novel research tool known as the Rijke burner. The ultimate goal of this work is to provide a scientific basis for the selection of the suppression additives in solid propellants.
 
 
 

Novel Energetic Materials to Stabilize Rocket Motors
M.W. Beckstead,  Brigham Young University

Normal Motor Motor Experiencing Combustion Instability

Objectives: Establish the connections between propellant composition and combustion instabilities observed in solid rocket motor Develop a mechanistic understanding of the combustion and combustion instability characteristics of advanced solid propellants from both an experimental and theoretical perspective Conduct a unified investigation into the mutual coupling between unsteady motor internal flows and transient combustion responses of propellants Develop methods for analyzing and predicting the combustion dynamics of solid propellant rocket motors Transfer the developed science from this program to DOD labs and industry

Technical Approach: Fundamental modeling of both ingredient and propellant combustion chemistry - both steady and unsteady  Utilize advanced quantum mechanical calculations of gas phase kinetics Compare calculated results to chemical species profiles measured with advanced diagnostic experiments (quadrapole mass spectrometer and PLIF spectroscopy) Interpret unstable combustion effects in terms of fundamental chemistry Compare to measurement of propellant combustion dynamics from advanced experimental methods

Accomplishments: Establishing the kinetic mechanisms for combustion of advanced propellant ingredients (HMX, RDX, ADN, GAP, .)  Developed both steady and unsteady combustion models of basic high energy ingredients using detailed kinetic mechanisms Comparison of unsteady numerical model with standard analytical models to determine the limitation of  the analytical models. Developed a detailed, comprehensive model of aluminum combustion