Numerical Simulation of the Reactive Two-Phase Solid Rocket Motor Exhaust Plume

摘要

This study is focused on numerical simulation of the reactive two-phase flow from the end of the motor combustion chamber to the exhaust plume. The NASA computer program CEA (Chemical Equilibrium with Applications) has been used to calculate the equilibrium composition of AP/HTPB/Al composite propellant in the chamber. Then the 2D Navier-Stokes equations with additional terms describing turbulence, chemical kinetics and gas-particle (Al_2O_3) interaction have been solved for numerical simulation of plumes at an altitude of 10 km. AUSM (Advection Upstream Splitting Method) vector splitting method and a second order upwind-biased scheme are present in the calculation. The resulting diagrams of temperature and mass fraction of components in the plume and profiles on the axis are shown. The flow field structure and particle behavior in the plume is discussed. Especially, the ability of coupled computation to represent complex physics phenomena of this kind is demonstrated.