A critical review of solid rocket propellant transient flame models

A critical review is offered of the commonly implemented flame models for computing transient burning rates and intrinsic combustion stability of solid rocket propellants. After illustrating merits and limitations of each, a new flame model is described, by means of a unified mathematical formalism, incorporatin all of the and closer agreement with experimental information is enforced. #he general feature of the new model, called ./3r, is the capability to describe spatial1 thick gas-phase flames, when necessary, allowin pressure and/or temperature depenlence of several of the relevant paramet,ers. W i t i proper care and within current limitations, the a0-y transient flame model is a p licable to both double-base and composite solid rocket ro Ilants. However, in orier to accomplish further rogress more fundamental work previous knowledge and allowing ground for further extensions. In artic 9 ar, a better t E area of characteristic gas-phase times is require$