Numerical Analysis of Solid Rocket Motor Instabilities With AP Composite Propellants

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

Analytic evaluation of finite difference methods for compressible direct and large eddy simulations

Communication to : Colloque CNES/ONERA/CNRS sur les ecoulements propulsifs dans les systemes de transport spatial, Bordeaux (France), 11-15 septembre 1995Available at INIST (FR), Document Supply Service, under shelf-number : 22419, issue : a.1995 n.128 / INIST-CNRS - Institut de l'Information Scientifique et TechniqueSIGLEFRFranc