Properties of steady‐state solutions for a simulated solid rocket motor

Abstract

PurposeThis paper's aim is to propose a quasi‐steady numerical model of a solid rocket motor that includes the coupling of motor chamber gas dynamics with the composite solid propellant combustion.Design/methodology/approachThe paper considers a model problem of steady‐state burning of a pure monopropellant coupled with a quasi‐steady gas dynamic model of the combustion chamber. In order to simulate the time evolution as the propellant burns back with time, the flow‐field in the chamber, the burning rate and the linear response function parameters are calculated for three port diameters of a simple cylindrical geometry.FindingsIt is shown that the pressure‐coupled linear response function remains approximately constant along the propellant surface but can change very strongly as the chamber pressure rises due to increase in the burn surface.Research limitations/implicationsOnly simplified motor geometry is considered but more realistic geometries can also be analyzed using a similar approach.Originality/valueThis study is the first step in building a comprehensive fully coupled model for numerical simulation of the internal flow‐fields of solid rocket motors. In addition, it demonstrates how to use the steady‐state results to calculate linearized pressure‐coupled response of the propellant.