Abstract:
This paper describes simulations of solid rocket motors that involve coupling between the core fluid flow, the structural response of the propellant and case, and the combustion of the propellant. A predictor-corrector algorithm is employed to treat the fluid-structure interaction. The combustion rate of the propellant is coupled to the fluid flow via an empirical power law relationship. The algorithm couples the physical processes involved using a partitioned approach, enabling the use of existing codes for the bulk of the simulations. Special consideration is given to the jump conditions that hold at the fluid-structure-combustion interface, and a large-scale simulation is described that demonstrates the code's capability.
