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

Purpose - This 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/approach - The 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. Findings - It 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/implications - Only simplified motor geometry is considered but more realistic geometries can also be analyzed using a similar approach. Originality/value - This study is the first step in building a comprehensive fully coupled model for numerical simulation of the internal flow-fields of solid rocket motors. hi addition, it demonstrates how to use the steady-state results to calculate linearized pressure-coupled response of the propellant.