8 research outputs found
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