Theoretical Modeling and Numerical Simulation Challenges of Combustion Processes of Hybrid Rockets

Abstract

Hybrid rocket technology is an exciting area of propulsion research. Multiple advantages of hybrid propulsion have been identified. However, the development of hybrid rockets is far from being complete to a technology maturation stage in terms of modeling and numerical simulation for performance prediction. This is due to the extremely complex combustion processes involved in the hybrid rocket motors. In recent years, different types of hybrid rocket engines have been proposed and partially tested. Most of these newly designed engines involve turbulent and multiphase combustion processes. This paper addresses major challenges in the theoretical modeling and numerical simulation areas. The purpose is to encourage engineers and scientists to achieve in-depth understanding of the physical and chemical processes so that suitable theoretical model and numerical solution can be established to assist the future design of this attractive propulsion system. Advancements in both theoretical model simulation and experimental diagnostics could be highly beneficial for achieving the goal of establishing a detailed comprehensive model, since validation is absolutely necessary to gain confidence in the numerical simulation of the combustion processes in hybrid rocket motors.