Numerical Analysis of Solid Rocket Motor InstabilitiesudWith AP Composite Propellants

摘要

A non-steady model for the combustion of ammoniumudperchlorate composite propellants has been developedudin order to be incorporated into a comprehensive gasdynamicsudmodel of solid rocket motor flow fields. Theudmodel including the heterogeneous combustion and turbulenceudmechanisms is applied to nonlinear combustionudinstability analyses. This paper describes the essentialudmechanisms and features of the model and discusses theudmethodology of non-steady calculations of the combustionudinstabilities of solid rocket motors.