'American Institute of Aeronautics and Astronautics (AIAA)'
Abstract
A non-steady model for the combustion of ammonium
perchlorate composite propellants has been developed
in order to be incorporated into a comprehensive gasdynamics
model of solid rocket motor flow fields. The
model including the heterogeneous combustion and turbulence
mechanisms is applied to nonlinear combustion
instability analyses. This paper describes the essential
mechanisms and features of the model and discusses the
methodology of non-steady calculations of the combustion
instabilities of solid rocket motors
