Nitramine based solid rocket propellants have the advantages of relatively low infrared and smoke emissions from their exhaust. Although a number of studies have been directed toward chemical and physical processes in the condensed phase during heating or combustion, the understanding of gas phase chemical processes has not been developed. The objective of the studies reported here is to provide additional insight into the chemistry of reactions of gas phase species of importance in the combustion of nitramine propellants. Chemical kinetic modeling of the gas phase reactions is used to evaluate critical reaction paths and energetic and their possible influence on burn rate. Particular attention has been given to the fizz reaction near the propellant surface and the preparation and flame zones standing off the surface. The chemical kinetic modeling shows a two zone behavior which is consistent with previous suggestions about the chemistry of the fizz and flame zones. The first zone is dominated by the rapid between CH20 and NO2 while the second zone results from the slower exothermic reduction of NO.